ALBERT

All Library Books, journals and Electronic Records Telegrafenberg

X
feed icon rss

Ihre E-Mail wurde erfolgreich gesendet. Bitte prüfen Sie Ihren Maileingang.

Leider ist ein Fehler beim E-Mail-Versand aufgetreten. Bitte versuchen Sie es erneut.

Vorgang fortführen?

Exportieren
Filter
  • AERODYNAMICS
  • Aerodynamics
  • Animals
  • Fluid Mechanics and Heat Transfer
  • 2000-2004
  • 1995-1999
  • 1970-1974  (258)
  • 1955-1959
  • 1925-1929
  • 1973  (258)
Sammlung
Schlagwörter
Erscheinungszeitraum
  • 2000-2004
  • 1995-1999
  • 1970-1974  (258)
  • 1955-1959
  • 1925-1929
Jahr
  • 101
    facet.materialart.
    Unbekannt
    Investigation of flow fields within large scale hypersonic inlet models (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Analytical and experimental investigations were conducted to determine the internal flow characteristics in model passages representative of hypersonic inlets for use at Mach numbers to about 12. The passages were large enough to permit measurements to be made in both the core flow and boundary layers. The analytical techniques for designing the internal contours and predicting the internal flow-field development accounted for coupling between the boundary layers and inviscid flow fields by means of a displacement-thickness correction. Three large-scale inlet models, each having a different internal compression ratio, were designed to provide high internal performance with an approximately uniform static-pressure distribution at the throat station. The models were tested in the Ames 3.5-Foot Hypersonic Wind Tunnel at a nominal free-stream Mach number of 7.4 and a unit free-stream Reynolds number of 8.86 X one million per meter.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TN-D-7150 , A-4274
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 102
    facet.materialart.
    Unbekannt
    Low-speed wind tunnel investigation of a semispan STOL jet transport wing body with an upper surface blown jet flap (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: An investigation of the static longitudinal aerodynamic characteristics of a semispan STOL jet transport wing-body with an upper-surface blown jet flap for lift augmentation was conducted in a low-speed wind tunnel having a 12-ft octagonal test section. The semispan swept wing had an aspect ratio of 3.92 (7.84 for the full span) and had two simulated turbofan engines mounted ahead of and above the wing in a siamese pod equipped with an exhaust deflector. The purpose of the deflector was to spread the engine exhaust into a jet sheet attached to the upper surface of the wing so that it would turn downward over the flap and provide lift augmentation. The wing also had optional boundary-layer control provided by air blowing through a thin slot over a full-span plain trailing-edge flap.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TN-D-7183 , L-8740
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 103
    facet.materialart.
    Unbekannt
    Subsonic wind-tunnel tests of a trailing-cone device for calibrating aircraft static pressure systems (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A trailing-cone device for calibrating aircraft static-pressure systems was tested in a transonic wind tunnel to investigate the pressure-sensing characteristics of the device including effects of several configuration changes. The tests were conducted at Mach numbers from 0.30 to 0.95 with Reynolds numbers from (0.9 x one million to 4.1 x one million per foot). The results of these tests indicated that the pressures sensed by the device changed slightly but consistently as the distance between the device pressure orifices and cone was varied from 4 to 10 cone diameters. Differences between such device-indicated pressures and free-stream static pressure were small, however, and corresponded to Mach number differences of less than 0.001 for device configurations with pressure orifices located 5 or 6 cone diameters ahead of the cone. Differences between device-indicated and free-stream static pressures were not greatly influenced by a protection skid at the downstream end of the pressure tube of the device nor by a 2-to-1 change in test Reynolds number.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TN-D-7217 , L-8672
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 104
    facet.materialart.
    Unbekannt
    A method for estimating static aerodynamic characteristics for slender bodies of circular and noncircular cross section alone and with lifting surfaces at angles of attack from 0 deg to 90 deg (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: An engineering-type method is presented for estimating normal-force, axial-force, and pitching-moment coefficients for slender bodies of circular and noncircular cross section alone and with lifting surfaces. Static aerodynamic characteristics computed by the method are shown to agree closely with experimental results for slender bodies of circular and elliptic cross section and for winged-circular and winged-elliptic cones. However, the present experimental results used for comparison with the method are limited to angles of attack only up to about 20 deg and Mach numbers from 2 to 4.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TN-D-7228 , A-4700
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 105
    facet.materialart.
    Unbekannt
    Results of Full-Scale Wind Tunnel Tests on the H.126 Jet Flap Aircraft (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The aerodynamic characteristics of the full-scale H.126 jet flap aircraft were studied in a 40- by 80 foot wind tunnel. The H.126 aircraft is designed for research on flight characteristics of an aircraft using the jet flap principle. Static longitudinal, lateral, and directional characteristics were measured at a Reynolds number of 2.5 to 2.7 million. The jet control power as well as the aerodynamic characteristics were measured and are presented herein with limited discussion. The primary configuration variables were flap and aileron deflection.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TN-D-7252 , A-3611
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 106
    facet.materialart.
    Unbekannt
    Low-subsonic aerodynamic characteristics of a shuttle-orbiter configuration designed for reduced length (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: An investigation has been made in a low-turbulence pressure tunnel to determine the low-subsonic aerodynamic characteristics of a 0.01875-scale model of a potential shuttle orbiter. The design has the rocket engines mounted in fairings on either side of the body on top of the wing. The wing had a leading-edge sweep of 50 and a trailing-edge sweep of minus 4. configurations investigated included engine-mounted twin dorsal tails at various rollout angles, a body-mounted center-line vertical tail, cylindrical and boattailed afterbody, and elevon and rudder at several deflections.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-X-2712 , L-8712
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 107
    facet.materialart.
    Unbekannt
    Steady, subsonic, lifting surface theory for wings with swept, partial span, trailing edge control surfaces (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A method for computing the lifting pressure distribution on a wing with partial span, swept control surfaces is presented. This method is valid within the framework of linearized, steady, potential flow theory and consists of using conventional lifting surface theory in conjuction with a flap pressure mode. The cause of a numerical instability that can occur during the quadrature of the flap pressure mode is discussed, and an efficient technique to eliminate the instability is derived. This technique is valid for both the flap pressure mode and regular pressure modes and could be used to improve existing lifting surface methods. Examples of the use of the flap pressure mode and comparisons among this method, other theoretical methods, and experiments are given. Discrepancies with experiment are indicated and candidate causes are presented. It is concluded that the method can lead to an efficient and accurate solution of the mathematical problem when a partial span, trailing edge flap is involved.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TN-D-7251 , A-4521
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 108
    facet.materialart.
    Unbekannt
    Throat-bypass bleed systems for increasing the stable airflow range of a Mach 2.50 axisymmetric inlet with 40-percent internal contraction (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The results of an experimental investigation to increase the stable airflow range of a super sonic mixed-compression inlet are presented. Various throat-bypass bleeds were located on the inlet cowl. The bleed types were distributed porous normal holes, a forward slanted slot, or distributed educated slots. Large inlet stability margins were obtained with the inlet throat bleed systems if a constant pressure was maintained in the throat-bypass bleed plenum. Stability limits were determined for steady-state and limited transient internal air flow changes. Limited unstart angle-of-attack data are presented.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-X-2779 , E-7240
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 109
    facet.materialart.
    Unbekannt
    Finite element approach to the integrated potential formulation of general unsteady supersonic aerodynamics (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Analytical formulation of the integrated potential approach for general unsteady supersonic configurations is related to numerical solution approaches using an arbitrary finite element mesh. Work remains to be done on adequate numerical handling of singular integrals, discussed in an appendix. Limited results on a planar rectangular wing are presented.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-112296
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 110
    facet.materialart.
    Unbekannt
    Overall and blade-element performance of a transonic compressor stage with multiple-circular-arc blades at tip speed of 419 meters per second (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A 50-centimeter-diameter axial-flow transonic compressor stage with multiple-circular-arc blades was designed and tested to study the effects of blade shape on efficiency and stall margin. At design speed, peak efficiency of 0.80 occurred at an equivalent weight flow of 29.0 kilograms per second. Measured total pressure ratio and total temperature ratio at peak efficiency were 1.69 and 1.20, respectively. The stall margin at design speed and an equivalent weight flow of 29.0 kilograms per second was 9 percent. The measured stall margin at design weight flow and speed was 15 percent. A comparison of rotor performance made with and without the stator showed a decrease in pressure ratio, peak efficiency, and maximum weight flow with the addition of the stator.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-X-2731 , E-6823
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 111
    facet.materialart.
    Unbekannt
    Performance of a low-pressure-ratio centrifugal compressor with four diffuser designs (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A low-pressure-ratio centrifugal compressor was tested with four different diffuser configurations. One diffuser had airfoil vanes. Two were pipe diffusers. One pipe diffuser had 7.5 deg cone diffusing passages. The other had trumpet-shaped passages designed for linear static-pressure rise from throat to exit. The fourth configuration had flat vanes with elliptical leading edges similar to those of pipe diffusers. The side walls were contoured to produce a linear pressure rise. Peak compressor efficiencies were 0.82 with the airfoil vane and conical pipe diffusers, 0.80 with the trumpet, and 0.74 with the flat-vane design. Surge margin and useful range were greater for the airfoil-vane diffuser than for the other three.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TN-D-7237 , E-7296
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 112
    facet.materialart.
    Unbekannt
    Experimental study of supersonic laminar base flow with and without suction (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Heat-transfer and pressure distributions in laminar separated flows downstream of rearward-facing steps with and without mass suction were investigated at Mach numbers around 4 for the conditions when the boundary-layer thickness was comparable to or larger than the step height. In both suction and no-suction cases, an increase of the step height resulted in a sharp drop of the base heating rates, which then gradually recovered to less than or near attached-flow values obtained with flat-plate configuration. Mass suction from the step base area increased the local heating rates; this effect, however, was relatively weak for laminar flows tested, and the competing effect of the step height clearly predominated. It was found that even removal of the entire incoming boundary layer was not sufficient to raise the poststep heating rates above the flat-plate values. The base pressure in the no-suction, solid-step case correlated reasonably well with the step height-to-boundary-layer thickness ratio and with the Reynolds number based on the step height.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal; 11; Dec. 197
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 113
    facet.materialart.
    Unbekannt
    Time-split finite-volume method for three-dimensional blunt-body flow (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: An efficient numerical method for calculating plane, axisymmetric, and fully three-dimensional blunt-body flow is presented. It is a second-order-accurate, time-dependent finite-volume procedure that solves the Euler equations in integral conservation-law form. These equations are written with respect to a Cartesian coordinate system in which an embedded mesh adjusts in time to the motion of the bow shock that is automatically captured as part of the weak solution. With such an adjusting mesh, oscillations in flow properties near the shock are shown to be virtually eliminated. The scheme uses a time-splitting concept that accelerates the convergence appreciably. Comparisons are made between computed and experimental results.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 73-133
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 114
    facet.materialart.
    Unbekannt
    Computer simulation of shock wave boundary layer interaction (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Development of a boundary layer correction for an analysis program previously used by Bauer et al. (1972) to study two-dimensional flow past transonic airfoils at off-design conditions where shocks which interact with the boundary layer appear. Using a method which combines conformal mapping with a finite-difference scheme due to Murman and Cole (1971), an analysis is made of the interaction between shock waves on a supercritical wing section and a turbulent boundary layer, assuming that the shocks are weak and that separation is insignificant. It is shown that relatively simple shock wave/boundary layer interactions of the kind envisioned in this study can be treated by determining the displacement thickness iteratively together with the flow and altering the profile accordingly. It is concluded that the proposed boundary layer correction appears to furnish an essential improvement in cases where both pronounced aft loading and a large enclosed supersonic region of flow are present.
    Schlagwort(e): AERODYNAMICS
    Materialart: Communications on Pure and Applied Mathematics; 26; Sept
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 115
    facet.materialart.
    Unbekannt
    Airfoil wake vortex characteristics in the far field (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Tangential and axial velocity profiles were measured in the far field wake vortices of several different airfoils. The results are summarized and discussed. A scanning laser velocimeter was used to obtain data up to 1000 chord lengths behind airfoils with rectangular, diamond-shaped, and swept wing planforms at several different angles of attack. The results show general agreement with wind tunnel measurements made in the near field. The results identify two separate flow regions for the dependence of vortex maximum tangential velocity on downstream distance; an inviscid region where the velocity remains constant after rollup to downstream distances of 200 chord lengths, and then a decay or viscous region that persisted to the limit of the test distance. The decay rates appear to be sensitive to both angle of attack and span loading. The maximum tangential velocity for downstream distances to 40 span lengths was reduced by a factor of 2 by changing from an elliptic (swept wing) or rectangular span loading to a triangular-like span loading (diamond-shaped planform wing). Measured axial velocity defects are shown to agree with those predicted by laminar theory.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-X-62318 , A-5262
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 116
    facet.materialart.
    Unbekannt
    A new technique for inducing a turbulent boundary layer in a supersonic flow (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: The feasibility of using slot injection to establish a turbulent boundary layer corresponding to a known Reynolds number is experimentally investigated. The basic concept consists of injecting secondary air through a slot. The air is injected at the same local static pressure and at a selected stagnation temperature to simulate a given upstream condition. The mass of the injected air can be controlled to match a desired Reynolds number. In the present experiment, secondary air was injected through a supersonic nozzle over a flat plate model. Heat transfer rates were measured at about 50 to 100 slot heights behind the slot, and the results were compared with theoretical estimates. Static pressure measurements were made over the surface in the streamwise direction. Velocity and Mach number profiles were obtained at a selected position downstream of the slot. Laminar and turbulent profiles were calculated from the Crocco method and the 1/7 power law respectively to compare with the results of measurements.
    Schlagwort(e): AERODYNAMICS
    Materialart: International Symposium on Space Technology and Science; Sep 03, 1973 - Sep 08, 1973; Tokyo; Japan
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 117
    facet.materialart.
    Unbekannt
    Some design considerations for supersonic cruise mixed compression inlets (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: A mixed compression inlet designed for supersonic cruise has very demanding requirements for high total pressure recovery and low bleed and cowl drag. However, since the optimum inlet for supersonic cruise performance may have other undesirable characteristics, it is necessary to establish trade-offs between inlet performance and other inlet characteristics. Some of these trade-offs between the amount of internal compression, aerodynamic performance and angle-of-attack tolerance are reviewed. Techniques for analysis of boundary layer control and subsonic diffuser flow are discussed.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-X-71460 , E-7756 , Propulsion Joint Specialist Conf.; Nov 05, 1973 - Nov 07, 1973; Las Vegas, NV; United States
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 118
    facet.materialart.
    Unbekannt
    Pressure fluctuations underlying attached and separated supersonic turbulent boundary layers and shock waves. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 73-996 , Aero-Acoustics Conference; Oct 15, 1973 - Oct 17, 1973; Seattle, WA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 119
    facet.materialart.
    Unbekannt
    Unsteady aerodynamic loads on slender cones at free-stream Mach numbers from 0 to 22. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: Results of an experimental study to determine the flow-induced unsteady aerodynamic loads on slender cones at very high Mach numbers. Experiments on 8-deg half-angle-cone/flat-base configurations were conducted at free-stream Mach numbers of 6 and 15 and Reynolds numbers corresponding to shuttle reentry conditions. The flow facilities used were the H-3 Hypersonic Facility (Mach 6) and the Longshot Free Piston Tunnel (Mach 15) of the Von Karman Institute for Fluid Dynamics in Rhode-St.-Genese, Belgium. With these test results and pertinent results from other research efforts, data were available at free-stream Mach numbers of 0.67, 2.5, 3, 4, 6, 15, and 22, so that empirical expressions could be developed for the Mach number dependence (1) of the overall fluctuating pressure under an attached turbulence boundary layer and (2) of the overall fluctuating base pressure.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 73-998 , Aero-Acoustics Conference; Oct 15, 1973 - Oct 17, 1973; Seattle, WA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 120
    facet.materialart.
    Unbekannt
    Measurements of the distribution of sound source intensities in turbulent jets. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: The spatial distribution of sound source intensities in jets is determined from the sound radiated into the acoustic far field by means of a concave mirror-microphone system. The mirror forms an image of the sound sources in a region far enough from the jet so that near field pressure fluctuations can be neglected. The sound intensity in the image is thus closely related to the strength of the actual sound sources in the jet. Results of measurements with jets of Mach numbers 0.7 to 1.9 emanating from circular nozzles and from slot nozzle-flap combinations demonstrate the influence of Mach number and of other parameters upon the sound source distribution.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 73-989 , Aero-Acoustics Conference; Oct 15, 1973 - Oct 17, 1973; Seattle, WA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 121
    facet.materialart.
    Unbekannt
    Surface pressure fluctuations in hypersonic turbulent boundary layers. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: The surface pressure fluctuations on a flat-plate model at hypersonic Mach numbers of 5.2, 7.4, and 10.4 with an attached turbulent boundary layer were measured using flush-mounted small piezoelectric sensors. A high-frequency resolution of the pressure field was achieved using specially designed small piezoelectric sensors. The rms pressures and nondimensional energy spectra for all above Mach numbers are presented. The convective velocities, obtained from space-time correlation considerations are equal to 0.7 of the free-stream velocity. The results indicate that the rms pressures vary from 5 to 25% of the mean static pressures. The ratios of rms pressure to dynamic pressure are less than the universally accepted subsonic value of .006. The ratio decreases in value as the Mach number or the dynamic pressure is increased.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 73-997 , Aero-Acoustics Conference; Oct 15, 1973 - Oct 17, 1973; Seattle, WA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 122
    facet.materialart.
    Unbekannt
    Study of control system effectiveness in alleviating vortex wake upsets. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: The problem of an airplane being upset by encountering the vortex wake of a large transport on takeoff or landing is currently receiving considerable attention. This paper describes the technique and results of a study to assess the effectiveness of automatic control systems in alleviating vortex wake upsets. A six-degree-of-freedom nonlinear digital simulation was used for this purpose. The analysis included establishing the disturbance input due to penetrating a vortex wake from an arbitrary position and angle. Simulations were computed for both a general aviation airplane and a commercial jet transport. Dynamic responses were obtained for the penetrating aircraft with no augmentation and with various command augmentation systems. The results of this preliminary study indicate that it is feasible to use an automatic control system to alleviate vortex encounter upsets.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 73-833 , Guidance and Control Conference; Aug 20, 1973 - Aug 22, 1973; Key Biscayne, FL
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 123
    facet.materialart.
    Unbekannt
    Application of compressibility correction to calculation of flow in inlets. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: An application of the compressibility correction developed by Lieblein and Stockman (1972) to the calculation of flow in axisymmetric inlets is described. The results with experimental data from wind tunnel model tests are compared. The configuration is a conventional subsonic inlet with a NACA series one external cowl shape and a two-to-one ellipse internal lip. It is shown that the compressibility correction gives a relatively good approximation to the internal compressible flow behavior, and thus should be useful in the design and analysis of engine nacelle inlets.
    Schlagwort(e): AERODYNAMICS
    Materialart: Application of compressibility correction to calculation of flow in inlets; Jul 01, 1973
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 124
    facet.materialart.
    Unbekannt
    Effect of downstream massive blowing on Jovian entry heating. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: An analysis for viscous radiating shock layer flow over a blunt body with massive blowing is presented. Detailed equilibrium computations for the thermodynamics and transport properties are included in the solution. Molecular band and atomic line, as well as continuum radiation are included. For a typical Jovian entry problem, a 40% reduction in total radiative flux at stagnation point, due to the injection of carbon gas, was found. The reduction increases to about 70% at about four body nose radii downstream. The increase of flux reduction indicates that most of the radiative energy is absorbed by the injected carbon gas and dumped into the wake. An examination of the spectral distribution of the surface radiative flux reveals that most of the flux reduction occurs in molecular bands of C2.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 73-717 , Thermophysics Conference; Jul 16, 1973 - Jul 18, 1973; Palm Springs, CA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 125
    facet.materialart.
    Unbekannt
    Velocity decay and acoustic characteristics of various nozzle geometries with forward velocity. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: Utilizing a static test stand, 6- by 9-foot wind tunnel and 13-inch circular free jet, aerodynamic and acoustic data were obtained with a convergent circular nozzle, bypass nozzle, 6-tube mixer nozzle, and 6-tube mixer nozzle with an ejector. The aerodynamic data consist of velocity decay surveys with and without forward velocity. The acoustic data include total sound power, directivity and frequency spectra obtained statically and with forward velocity. The relation of aerodynamic and acoustic measurements statically and in forward flight for the various nozzle configurations are discussed.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 73-629 , Fluid and Plasma Dynamics Conference; Jul 16, 1973 - Jul 18, 1973; Palm Springs, CA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 126
    facet.materialart.
    Unbekannt
    The role of jet stability in edgetone generation. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: Consideration of the role of stability of the mean jet flow of an edgetone system in the edgetone operation. A brief description of the main features of the edgetone operation and a brief review of the pertinent background are presented. This is followed by a discussion of the inadequacy of parallel flow stability considerations in explaining edgetone features. An analysis is made of the stability characteristics of a slightly nonparallel jet flow, and the role of jet stability based on these considerations in the edgetone operation is discussed. It is shown that the characteristics obtained by considering the nonparallel nature of the jet flowfield lead to a satisfactory description of the phenomenon, including a frequency selection criterion based on the concept of the most amplified disturbance frequency at each edge position.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 73-628 , Fluid and Plasma Dynamics Conference; Jul 16, 1973 - Jul 18, 1973; Palm Springs, CA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 127
    facet.materialart.
    Unbekannt
    Supersonic turbulent boundary-layer flows with tangential slot injection. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: An implicit finite-difference method has been developed for the solution of the compressible boundary-layer equations. This method is applied to tangential slot injection into supersonic turbulent boundary-layer flows. In addition, the effects induced by the interaction between the boundary-layer displacement thickness and the external pressure field are considered. Three different eddy viscosity models have been used to specify the turbulent momentum exchange. One model depends on the species concentration profile, and the species conservation equation has been included in the system of governing partial differential equations. For air injected into air, the freestream and injected gases are treated as separate species which have common fluid properties. Calculations were made and results were compared with experimental data at freestream Mach numbers of 2.4 and 6.0 and with results of another finite-difference method. Good agreement was obtained for the reduction of wall skin friction with slot injection.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 73-696 , Fluid and Plasma Dynamics Conference; Jul 16, 1973 - Jul 18, 1973; Palm Springs, CA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 128
    facet.materialart.
    Unbekannt
    Analytical investigation of compressibility and three-dimensionality on the unsteady response of an airfoil in a fluctuating flow field. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 73-683 , Fluid and Plasma Dynamics Conference; Jul 16, 1973 - Jul 18, 1973; Palm Springs, CA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 129
    facet.materialart.
    Unbekannt
    Study of the far wake vortex field generated by a rectangular airfoil in a water tank. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 73-682 , Fluid and Plasma Dynamics Conference; Jul 16, 1973 - Jul 18, 1973; Palm Springs, CA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 130
    facet.materialart.
    Unbekannt
    Numerical solution for the inviscid supersonic flow in the corner formed by two intersecting wedges. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: The inviscid, interference corner flow generated by two intersecting wedges immersed in a supersonic stream is obtained by use of a second-order, shock-capturing, finite-difference approach. The governing equations are solved iteratively in conical coordinates to yield the flow structure consisting of multiple shock and slip surfaces. The numerical results for shock wave and slip surface position and structure, pitot pressure traverses, and surface pressure distributions are compared with experimental data obtained over a wide range of Reynolds numbers. The comparisons show the best agreement with the high Reynolds number (greater than 3,000,000) results for which the boundary layer is turbulent.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 73-675 , Fluid and Plasma Dynamics Conference; Jul 16, 1973 - Jul 18, 1973; Palm Springs, CA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 131
    facet.materialart.
    Unbekannt
    Rearward-facing steps in laminar supersonic flows with and without suction. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: It was found in the experimental study conducted that, for both suction and no-suction cases, an increase in the step height caused a sharp drop in the initial heating rates which then gradually recovered to less or near the attached-flow values. The height of the step controlled the heating rates at the step base. Mass suction from the separated area increased the local heating rates, the relative increase being most significant immediately behind the step. In general, however, the effect of mass suction on heat-transfer at all laminar flows was relatively weak.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 73-667 , Fluid and Plasma Dynamics Conference; Jul 16, 1973 - Jul 18, 1973; Palm Springs, CA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 132
    facet.materialart.
    Unbekannt
    Unsteady turbulent boundary layers in two-dimensional, incompressible flow. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: The paper presents the results of some calculations aimed at studying the characteristics of turbulent boundary layers in unsteady flow. The calculations were performed using the method of Singleton and Nash, which is based on the turbulent kinetic energy equation. Emphasis is placed on the approach to zero wall stress, and the results show the extent to which onset of this condition can be delayed by the effects of time dependence. The delay is not associated merely with alleviation of the pressure gradients, and quasi-steady methods cannot readily be used to calculate this type of flow.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 73-650 , Fluid and Plasma Dynamics Conference; Jul 16, 1973 - Jul 18, 1973; Palm Springs, CA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 133
    facet.materialart.
    Unbekannt
    A kernel function method for computing steady and oscillatory supersonic aerodynamics with interference. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: The method presented uses a collocation technique with the nonplanar kernel function to solve supersonic lifting surface problems with and without interference. A set of pressure functions are developed based on conical flow theory solutions which account for discontinuities in the supersonic pressure distributions. These functions permit faster solution convergence than is possible with conventional supersonic pressure functions. An improper integral of a 3/2 power singularity along the Mach hyperbola of the nonplanar supersonic kernel function is described and treated. The method is compared with other theories and experiment for a variety of cases.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 73-670 , Fluid and Plasma Dynamics Conference; Jul 16, 1973 - Jul 18, 1973; Palm Springs, CA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 134
    facet.materialart.
    Unbekannt
    Effect of nose geometry on the aerothermodynamic environment of shuttle entry configurations. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 73-638 , Fluid and Plasma Dynamics Conference; Jul 16, 1973 - Jul 18, 1973; Palm Springs, CA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 135
    facet.materialart.
    Unbekannt
    Experimental and theoretical investigations in two-dimensional transonic flow. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: Experimental and theoretical results are presented from a study of the flow over a family of transonically scaled circular-arc bodies mounted in a solid-wall wind tunnel. Data are presented for Reynolds numbers between 30,000 and 3,600,000, based on chord. The high Reynolds number results are compared with computations based on inviscid theory, and are used to investigate transonic similarity and the behavior of the flow near choking. The results at low Reynolds number are used to demonstrate the effect of viscosity on the overall flowfield, and comparisons are made with existing laminar viscous/inviscid interaction theory.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 73-659 , Fluid and Plasma Dynamics Conference; Jul 16, 1973 - Jul 18, 1973; Palm Springs, CA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 136
    facet.materialart.
    Unbekannt
    Experiments on confined turbulent jets in cross flow. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: Results are reported of experiments on the effects of an opposite wall on the characteristics of turbulent jets injected into a cross flow, for unheated and heated jets. Longitudinal and transverse distributions of velocity and temperature are presented for single and multiple circular jets, and trajectories are presented for two-domensional jets. The opposite wall has relatively little effect on a single jet unless the ratio of jet to cross flow momentum flux is large enough for the jet to impinge on the opposite wall. For a row of jets aligned perpendicularly to the cross flow, the opposite wall exerts progressively larger influence as the spacing between jets decreases. Much of the effect of jet and wall proximity can be understood by considering the interaction of the vortex flow which is the major feature of the structure of a single jet in a cross flow. Smoke photographs are shown to elucidate some of the interaction patterns.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 73-647 , Fluid and Plasma Dynamics Conference; Jul 16, 1973 - Jul 18, 1973; Palm Springs, CA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 137
    facet.materialart.
    Unbekannt
    Three-dimensional hypersonic transitional/turbulent mean flow profiles. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: Detailed three-dimensional compressible transitional/turbulent boundary-layer profiles are presented for use as test cases in numerical and integral calculation procedures. The profiles were obtained from tests conducted in the Mach 20 leg of the Langley High Reynolds Number Helium Facility. The presented data represent an arduous test case for analytical prediction methods, since 'low Reynolds number' and precursor transition effects should probably be accounted for to accurately predict the boundary-layer growth and development.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 73-635 , Fluid and Plasma Dynamics Conference; Jul 16, 1973 - Jul 18, 1973; Palm Springs, CA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 138
    facet.materialart.
    Unbekannt
    Rotor noise due to inflow turbulence. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: The interaction of turbulent velocity fluctuations of the inflow with rotor blades and the resulting acoustic radiation is examined in terms of: dipole sources due to blade loading, monopole sources due to thickness of the rotating blades, and quadrupole sources due to velocity fluctuations in the flow region. Depending upon the length and time scales of the turbulence, sufficient number of blades may interact with a coherent eddy to radiate noise with discrete peaks at blade passing frequency and its harmonics. Theoretical estimates of acoustic radiation to on-axis points from a typical subsonic rotor are presented, and it is noted that the discrete tone noise is primarily from dipole radiation. Discrete tone noise levels observed in narrow band analysis of test data show reasonable agreement with analytical predictions.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 73-632 , Fluid and Plasma Dynamics Conference; Jul 16, 1973 - Jul 18, 1973; Palm Springs, CA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 139
    facet.materialart.
    Unbekannt
    Mean flow and turbulence measurements in a Mach 5 shear layer. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: Hot-wire study of turbulent mixing in the near field of a Mach 5 jet with extension of the results into the hypersonic range. Mean and fluctuating measurement data are given for the free shear layer of the 10.6-cm diameter jet which was contained in a 61-by-61 cm vacuum chamber and exhausted into a diffuser 44 cm downstream of the jet exit. An auxiliary air supply was used to equalize the static pressures in the chamber and the nozzle. The nozzle wall boundary layer was turbulent at the jet exit, providing measurement data at higher Reynolds numbers, which are also included.
    Schlagwort(e): AERODYNAMICS
    Materialart: Joint Meeting on Fluid mechanics of mixing; Jun 20, 1973 - Jun 22, 1973; Atlanta, GA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 140
    facet.materialart.
    Unbekannt
    Computational considerations in application of the finite element method for analysis of unsteady flow around airfoils. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: Difficulties related to the application of the finite element method for numerical solution of the Navier-Stokes equation are discussed. The unsteady flow around a stationary and oscillating NACA 0012 airfoil was analyzed. In an effort to establish the range of applicability of the developed numerical method, the accuracy and stability problems in representing unsteady flow patterns and determining pressure distribution around the airfoil were investigated. Error involved in determining the velocity field and in the numerical integration of the discretized equations were analyzed in terms of geometry of the finite element gridwork, boundary conditions for stationary and oscillating airfoils, angles of attack and flow conditions.
    Schlagwort(e): AERODYNAMICS
    Materialart: Computational Fluid Dynamics Conference; Jul 19, 1973 - Jul 20, 1973; Palm Springs, CA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 141
    facet.materialart.
    Unbekannt
    Viscous flow over spinning cones at angle of attack. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: A numerical finite-difference method is developed for evaluating the Magnus coefficients on spinning cones in laminar flow. The merged layer, the strong interaction region, and the downstream boundary layer are all considered. The numerical method is a predictor-corrector scheme developed for three-dimensional flows with or without crossflow diffusion. This method is particularly useful in problems in which a symmetry plane does not exist. Several contributions to the Magnus force and moments are considered. These include asymmetries in displacement thickness, centrifugal force and crossflow shear, and the effects of crossflow separation and vortex formation. Comparisons are made with experimental data and other analyses.
    Schlagwort(e): AERODYNAMICS
    Materialart: Computational Fluid Dynamics Conference; Jul 19, 1973 - Jul 20, 1973; Palm Springs, CA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 142
    facet.materialart.
    Unbekannt
    Numerical calculation of the three dimensional transonic flow over a yawed wing. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: Results are presented of calculations of the three dimensional steady transonic flow over a finite yawed wing. The full potential flow equation is solved in a transformed coordinate system which permits the boundary conditions to be satisfied exactly. The correct differential properties are enforced by rotating the difference scheme to conform with the flow direction, and fast convergence is assured by simulating a time dependent equation designed to settle quickly to a steady state. Computed lift drag ratios are consistent with the results of wind tunnel tests of a yawed wing conducted by R. T. Jones (1972).-
    Schlagwort(e): AERODYNAMICS
    Materialart: Computational Fluid Dynamics Conference; Jul 19, 1973 - Jul 20, 1973; Palm Springs, CA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 143
    facet.materialart.
    Unbekannt
    Relaxation solutions for inviscid axisymmetric transonic flow over blunt or pointed bodies. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: A finite-difference relaxation method is presented for numerical solution of the full potential equation and exact boundary conditions for general axisymmetric bodies is inviscid, steady transonic flow. Body-normal coordinates are used in the nose region and sheared cylindrical coordinates are used on the afterbody to accommodate corners such as boattails and flares. An improved difference scheme is used which does not require that the flow be nearly alined with a coordinate direction in supersonic regions, and which treats either subsonic or supersonic free streams. Numerical results are illustrated for some simple classical shapes such as spheres and ellipsoids, and for more practical shapes like tangent-ogives with boattails. Special attention is given to bodies which have been studied for area-rule applications. Agreement with available experimental results is good in cases where viscous effects and wind-tunnel wall interference are not important.
    Schlagwort(e): AERODYNAMICS
    Materialart: Computational Fluid Dynamics Conference; Jul 19, 1973 - Jul 20, 1973; Palm Springs, CA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 144
    facet.materialart.
    Unbekannt
    Three-dimensional flow field in rocket pump inducers. I - Measured flow field inside the rotating blade passage and at the exit. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Schlagwort(e): AERODYNAMICS
    Materialart: ASME PAPER 73-FE-33 , Applied Mechanics and Fluids Engineering Conference; Jun 20, 1973 - Jun 22, 1973; Atlanta, GA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 145
    facet.materialart.
    Unbekannt
    A method of measuring three-dimensional rotating wakes behind turbomachinery rotors. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Schlagwort(e): AERODYNAMICS
    Materialart: ASME PAPER 73-FE-31 , Applied Mechanics and Fluids Engineering Conference; Jun 20, 1973 - Jun 22, 1973; Atlanta, GA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 146
    facet.materialart.
    Unbekannt
    Experimental evaluation of the effects of a blunt leading edge on the performance of a transonic rotor. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Schlagwort(e): AERODYNAMICS
    Materialart: ASME PAPER 73-GT-60 , Gas Turbine Conference and Products Show; Apr 08, 1973 - Apr 12, 1973; Washington, DC
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 147
    facet.materialart.
    Unbekannt
    The use of a finite difference technique to predict cascade, stator, and rotor deviation angles and optimum angles of attack. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Schlagwort(e): AERODYNAMICS
    Materialart: ASME PAPER 73-GT-10 , Gas Turbine Conference and Products Show; Apr 08, 1973 - Apr 12, 1973; Washington, DC
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 148
    facet.materialart.
    Unbekannt
    Effect of rotor design tip speed on aerodynamic performance of a model VTOL lift fan under static and crossflow conditions. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Schlagwort(e): AERODYNAMICS
    Materialart: ASME PAPER 73-GT-2 , Gas Turbine Conference and Products Show; Apr 08, 1973 - Apr 12, 1973; Washington, DC
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 149
    facet.materialart.
    Unbekannt
    Externally blown flap trailing edge noise reduction by slot blowing - A preliminary study. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 73-245 , Aerospace Sciences Meeting; Jan 10, 1973 - Jan 12, 1973; Washington, DC
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 150
    facet.materialart.
    Unbekannt
    Annular truncated plug nozzle flowfield and base pressure characteristics. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: The flowfield and base pressure characteristics of an internal-external expansion, truncated plug nozzle are described over the pressure ratio range from 'open' wake to 'closed' wake conditions. The effect of plug length on these characteristics, including the process of wake 'closure' is also presented. An existing method for calculating the flowfield and base pressure, for 'closed' wake operation, is modified to include the internal shock wave generated near the shroud exit. The supersonic portion of the flow is calculated using rotational axisymmetric method of characteristics. The technique of Hartree is employed so that the downstream characteristic point locations can be chosen to fit the developing flowfield. An overexpansion technique is used to detect the internal shock wave in the vicinity of the shroud exit so that its effect on the plug base pressure could be determined. Good agreement between the analytical results and experimental data is obtained for 'closed' wake operations.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 73-137 , Aerospace Sciences Meeting; Jan 10, 1973 - Jan 12, 1973; Washington, DC
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 151
    facet.materialart.
    Unbekannt
    Unsteady transonic flow analysis for low aspect ratio, pointed wings. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: Oswatitsch and Keune's parabolic method for steady transonic flow is applied and extended to thin slender wings oscillating in the sonic flow field. The parabolic constant for the wing was determined from the equivalent body of revolution. Laplace transform methods were used to derive the asymptotic equations for pressure coefficient, and the Adams-Sears iterative procedure was employed to solve the equations. A computer program was developed to find the pressure distributions, generalized force coefficients, and stability derivatives for delta, convex, and concave wing planforms.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 73-122 , Aerospace Sciences Meeting; Jan 10, 1973 - Jan 12, 1973; Washington, DC
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 152
    facet.materialart.
    Unbekannt
    Design integration and noise studies for jet STOL aircraft. Task 7B: Wind tunnel investigation of a 14-percent-thick airfoil with upper surface blowing at high subsonic Mach numbers (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: An exploratory wind tunnel test has been conducted at Mach numbers from 0.60 to 0.80 to investigate the effects of nozzle geometry and upper surface blowing on the aerodynamic characteristics of a 14-percent-thick airfoil. Measured data included lift, drag, pitching moments, surface pressures, and nozzle thrust.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-114560 , D6-60182
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 153
    facet.materialart.
    Unbekannt
    An unsteady wake model for a hingeless rotor (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A simple nonsteady wake model derived from the unsteady moment of the momentum equation for zero advance ratio is correlated with cyclic pitch frequency response tests conducted with a small hingeless rotor model. Two and three or more bladed rotor analyses are presented.
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Aircraft; 10; Dec. 197
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 154
    facet.materialart.
    Unbekannt
    A study of methods which predict supersonic flow fields from body geometry, distance, and Mach number (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A study of seven methods for predicting flow-field pressure signatures from the parameters Mach number, body geometry, and field-path distance has been made. The methods included the method of characteristics, which served as a standard of comparison; a shock-capturing method; three Whitham theory methods; a modified characteristics method; and a bicharacteristics method. Results from each method were also compared with recently obtained wind-tunnel data for a cone-cylinder model at Mach numbers of 2.96 and 4.63 with ratios of radial distance to cone length of 2 and 5. The comparisons at a Mach number of 2.96 showed that signatures from all the methods correlated well with wind-tunnel data and with the signatures predicted by the method of characteristics. At a Mach number of 4.63, however, the agreement between the signatures obtained in the wind tunnel and those predicted by theory varied from good to poor, as did the agreement between the signatures obtained by the method of characteristics and the other six methods. It should be noted that these results and comparisons indicate pressure prediction capabilities only for the near-field flow about bodies of revolution.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TN-D-7387 , L-8940
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 155
    facet.materialart.
    Unbekannt
    Comparison of predicted and measured low-speed performance of two 51 centimeter-diameter inlets at incidence angle (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Theoretical and experimental internal flow characteristics of two 51-cm-diameter inlets are compared. Theoretical flow characteristics along the inlet surface were obtained from an axisymmetric potential flow and boundary layer analysis. The experimental data were obtained from low-speed tests of a high-bypass-ratio turbofan engine simulator. Comparisons between calculated internal surface pressure distributions and experimental data are presented for a free-system velocity of 45 m/sec and for incidence angles from 0 deg to 50 deg. Analysis of boundary layer separation on the inlet lip at incidence angle is the major emphasis of this report. Theoretical boundary layer shape factors, skin friction coefficients, and velocity profiles in the boundary layer are presented, along with the location of the transition region. Theoretical and experimental separation locations are also discussed.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-X-2937 , E-7546
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 156
    facet.materialart.
    Unbekannt
    Performance of transonic fan stage with weight flow per unit annulus area of 208 kilograms per second per square meter (42.6 (lb/sec)/sq ft) (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Performance was obtained for a 50-cm-diameter compressor designed for a high weight flow per unit annulus area of 208 (kg/sec)/sq m. Peak efficiency values of 0.83 and 0.79 were obtained for the rotor and stage, respectively. The stall margin for the stage was 23 percent, based on equivalent weight flow and total-pressure ratio at peak efficiency and stall.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-X-2903 , E-7229
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 157
    facet.materialart.
    Unbekannt
    Aeronautical Engineering: A special bibliography with indexes, supplement 32, June 1973 (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: This special bibliography lists 372 reports, articles, and other documents introduced into the NASA scientific and technical information system in May 1973.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-SP-7037(32)
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 158
    facet.materialart.
    Unbekannt
    Studies in tilt-rotor VTOL aircraft aeroelasticity, volume 1 (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Aeroelastic and dynamic studies which complement and extend various aspects of technology applicable to tilt-rotor VTOL aircraft are discussed. Particular attention is given to proprotor/pylon whirl instability, a precession-type instability akin to propeller/nacelle whirl flutter. The blade flapping and pitch-change freedoms of a proprotor are shown to lead to a fundamentally different situation as regards the manner in which the precession-generated aerodynamic forces and moments act on the pylon and induce whirl flutter relative to that of a propeller. The implication of these forces and moments with regard to their capacity for instigating a whirl instability is examined, demonstrating why a proprotor can exhibit whirl flutter in either the backward or forward directions in contrast to a propeller which is found to always whirl in the backward direction. Analytical trend studies delineating the effect of several system design parameters on proprotor/pylon stability and response are shown.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-X-69497
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 159
    facet.materialart.
    Unbekannt
    Boundary condition program for aerodynamic lifting surface theory (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Users manual for a U.S.A. FORTRAN 4 computer program which determines boundary conditions for a thin wing lifting surface program is described. This program, the geometry program, and several other programs are used together in the analysis of lifting, thin wings in steady, subsonic flow according to a kernel function lifting surface theory. The program calculates specific types of boundary conditions automatically such as those necessary to determine pitch and roll damping derivatives. The program also accepts descriptions of the camber or downwash and twist in the form of tables and/or coefficients of equations. The program performs interpolations so that tables and/or coefficients can apply at stations selected by the user and not at stations dictated by the control point locations.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-X-62323
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 160
    facet.materialart.
    Unbekannt
    Analysis of helicopter maneuver-loads and rotor-loads flight test data (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A study was conducted in which available airload and blade response data for the NH-3A and CH-53A rotors were analyzed in an attempt to provide greater insight into the sources of rotor vibratory loads in both level and maneuvering flight. Primary emphasis in the study was placed on examining and understanding causes of high-frequency rotor control loads. Secondary objectives were: (1) to examine the effect of number of rotor blades on hub vibratory shear forces and (2) to assess which of the many terms appearing in the hub vibratory shear force expression were of most significance.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-2225
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 161
    facet.materialart.
    Unbekannt
    Wind tunnel simulation of full scale vortices (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: An experimental investigation has been conducted to determine the important scaling parameters for the flow in the core region of a vortex generated by a rectangular wing tip. The effect of an unconventional planform, the ogee tip, on the tip vortex is also determined. For rectangular planform wings, the measured vortex core diameter to chord ratios, peak tangential velocity ratios, and axial velocity ratios are shown to be functions only of wing lift coefficient and elapsed time from vortex formation, and appear to be independent of both Mach number and Reynolds number. The peak tangential velocities in the diffuse vortex generated by the ogee tip are only 25 percent of those in the vortex generated by the rectangular wing.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-2180
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 162
    facet.materialart.
    Unbekannt
    Analytical parametric investigation of low pressure ratio fan noise (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The results of an analytical study are reported which shows the effect of various physical and operating parameters on noise produced by low pressure ratio propulsive fans operating at subsonic top speeds. Acoustical duct lining effects are included in the study. The concepts used to develop the noise theory used in the study, as well as the correlation between the theory and model test results are also presented. It is shown that good correlation has been established between theory and experiment. Using the theory, it is shown that good aerodynamic design, maximum acceptable fan solidity, low tip speed operation and use of few blades and vanes leads to the lowest noise levels. Typical results of the study indicate that a fan operating at 1.2 fan pressure ratio and 700 ft/second tip speed with 12 blades and 7 vanes and including modest acoustic treatment on the duct wall would produce levels allowing a 100,000 lb. STOL aircraft to meet a noise level objective of 95 PNdB at 500 ft at takeoff.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-2188 , HSER-5990
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 163
    facet.materialart.
    Unbekannt
    Comparison of the aerodynamic characteristics of an ablating and nonablating blunted conical body (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The influence of ablation on the aerodynamic characteristics of a blunted slender cone was investigated. Plastic models were launched in free flight at ablating conditions. The results were compared with results of similar tests using metal nonablating models. Ablation was found to decrease the dynamic stability and the drag, but had little effect on static stability and lift. The plastic models appeared to experience ablation-induced roll.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TN-D-7196 , A-4558
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 164
    facet.materialart.
    Unbekannt
    Generalize aerodynamic coefficient table storage, checkout and interpolation for aircraft simulation (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The set of programs described has been used for rapidly introducing, checking out and very efficiently using aerodynamic tables in complex aircraft simulations on the IBM 360. The preprocessor program reads in tables with different names and dimensions and stores then on disc storage according to the specified dimensions. The tables are read in from IBM cards in a format which is convenient to reduce the data from the original graphs. During table processing, new auxiliary tables are generated which are required for table cataloging and for efficient interpolation. In addition, DIMENSION statements for the tables as well as READ statements are punched so that they may be used in other programs for readout of the data from disc without chance of programming errors. A quick data checking graphical output for all tables is provided in a separate program.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-X-62229
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 165
    facet.materialart.
    Unbekannt
    Analytical study on a two-dimensional plane of the off-design flow properties of tandem-bladed compressor stators (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The flow characteristics of several tandem bladed compressor stators were analytically evaluated over a range of inlet incidence angles. The ratios of rear-segment to front-segment chord and camber were varied. Results were also compared to the analytical performance of a reference solid blade section. All tandem blade sections exhibited lower calculated losses than the solid stator. But no one geometric configuration exhibited clearly superior characteristics. The front segment accepts the major effect of overall incidence angle change. Rear- to front-segment camber ratios of 4 and greater appeared to be limited by boundary-layer separation from the pressure surface of the rear segment.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-X-2734 , E-7031
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 166
    facet.materialart.
    Unbekannt
    Analysis of high-aspect-ratio jet-flap wings of arbitrary geometry (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: An analytical technique to compute the performance of an arbitrary jet-flapped wing is developed. The solution technique is based on the method of Maskell and Spence in which the well-known lifting-line approach is coupled with an auxiliary equation providing the extra function needed in jet-flap theory. The present method is generalized to handle straight, uncambered wings of arbitrary planform, twist, and blowing (including unsymmetrical cases). An analytical procedure is developed for continuous variations in the above geometric data with special functions to exactly treat discontinuities in any of the geometric and blowing data. A rational theory for the effect of finite wing thickness is introduced as well as simplified concepts of effective aspect ratio for rapid estimation of performance.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-2179
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 167
    facet.materialart.
    Unbekannt
    Subsonic characteristics of a twin-jet swept-wing fighter model with maneuvering devices (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: An investigation has been conducted at Mach numbers ranging from 0.06 to 0.94 to determine the effects of various combinations of leading-edge slat devices on the static aerodynamic characteristics of a twin-jet swept-wing fighter model. The study also included a determination of the effects of wing leading-edge droop, trailing-edge chord-extensions, wing fences, and wing-planform and camber modifications. The angle-of-attack range generally extended from about minus 2 deg to 24 deg and the sideslip angles ranged from about minus 6 deg to 13 deg.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TN-D-6921 , L-8221
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 168
    facet.materialart.
    Unbekannt
    A two-dimensional, iterative solution for the jet flap (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A solution is presented for the jet-flapped wing in two dimensions. The main flow is assumed to be inviscid and incompressible. The flow inside the jet is considered irrotational and the upper and lower boundaries between the jet and free stream are assumed to behave as vortex sheets which allow no mixing. The solution is found to be in satisfactory agreement with two dimensional experimental results and other theoretical work for intermediate values of momentum coefficient, but the regions of agreement vary with jet exit angle. At small values of momentum coefficient, the trajectory for the jet, as computed by this method, has more penetration than that of other available data, while at high values of moment coefficient this solution results in less penetration of the jet into the main flow.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-2190
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 169
    facet.materialart.
    Unbekannt
    Supersonic aerodynamic characteristics of a variable-geometry spacecraft designed for high hypersonic performance (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: An investigation was made in the high Mach number test section of the Langley Unitary Plan wind tunnel on a variable-geometry high hypersonic performance spacecraft concept at Mach numbers from 2.30 to 4.63. The basic lifting body is designed for hypersonic lift-drag ratio near 3.0. The variable-geometry feature is a single-pivot two-position high wing which is deployed at subsonic speeds to improve vehicle landing characteristics. For the present investigation the wing was maintained in a stowed position, and the effects of horizontal stabilizer dihedral, elevon control effectiveness, and the addition of either a conventional single vertical tail or dorsal-fin-type vertical stabilizers on the longitudinal and lateral-directional stability and control characteristics were studied.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-X-2703 , L-8639
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 170
    facet.materialart.
    Unbekannt
    Wind-tunnel calibration and requirements for in-flight use of fixed hemispherical head angle-of-attack and angle-of-sideslip sensors (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Wind-tunnel tests were conducted with three different fixed pressure-measuring hemispherical head sensor configurations which were strut-mounted on a nose boom. The tests were performed at free-stream Mach numbers from 0.2 to 3.6. The boom-angle-of-attack range was -6 to 15 deg, and the angle-of-sideslip range was -6 to 6 deg. The test Reynolds numbers were from 3.28 million to 65.6 million per meter. The results were used to obtain angle-of-attack and angle-of-sideslip calibration curves for the configurations. Signal outputs from the hemispherical head sensor had to be specially processed to obtain accurate real-time angle-of-attack and angle-of-sideslip measurements for pilot displays or aircraft systems. Use of the fixed sensors in flight showed them to be rugged and reliable and suitable for use in a high temperature environment.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TN-D-6986 , H-702
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 171
    facet.materialart.
    Unbekannt
    Development and applications of supersonic unsteady consistent aerodynamics for interfering parallel wings (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The analytical development of unsteady supersonic aerodynamic influence coefficients for isolated and nearly parallel interfering coplanar and noncoplanar wings is described. Numerical formulations based on triangular discretizations of wings and diaphragms are handled in a kinematically consistent manner. Examples of isolated wing cases are compared with respect to aerodynamic influence coefficients and flutter boundaries. Aerodynamic influence coefficients for interfering wings are compared where corresponding results are available.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-2168
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 172
    facet.materialart.
    Unbekannt
    Theoretical and experimental internal flow characteristics of a 13.97-centimeter-diameter inlet at STOL takeoff and approach conditions (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The theoretical and experimental internal flow characteristics of a 13.97-cm-diam inlet with centerbody retracted and extended are presented at STOL takeoff and approach operating conditions. The theoretical results were obtained from incompressible potential flow corrected for compressibility and boundary layer. Comparisons between theoretical internal surface static-pressure distributions and experimental data are presented for free-stream velocities of 0, 24, 32, and 45 m/sec for a range of inlet incidence angles from 0 to 50 deg. Surface static-pressure distributions are illustrated at circumferential locations of 0, 60, 120, and 180 deg. Surface Mach number distributions from the stagnation point to the diffuser exit are presented along with turbulent boundary-layer shape factors. In general, good agreement was found between the theoretical and experimental surface static pressure distributions.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TN-D-7185 , E-7237
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 173
    facet.materialart.
    Unbekannt
    Heating and flow-field studies on a straight-wing hypersonic reentry vehicle at angles of attack from 20 to 80 deg with simulation of real-gas trends (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Data are presented from a series of phase-change heat transfer and flow visualization tests at Mach 7.4, 8, and 10.3 in air, Mach 19.5 in nitrogen, Mach 20.3 in helium, and Mach 6 in tetrafluoromethane (CF4) on the windward surface of a straight wing hypersonic reentry configuration for angles of attack from 20 deg to 80 deg. The results indicate that: (1) for hypersonic stream Mach numbers, the flow field over the straight-wing configuration is essentially independent of Mach number, (2) transition Reynolds number decreases with increasing angle of attack, (3) at some critical angle of attack, the wing-shock standoff distance is greatly increased and the stagnation line moves downstream from the wing leading edge, (4) value of the critical angle of attack is very sensitive to the flow shock density ratio or effective gamma, and (5) at angles of attack above the critical value for all gases, the nondimensional level of heat transfer to the wing is higher for the higher shock density ratio flows.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TN-D-7108 , L-7946
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 174
    facet.materialart.
    Unbekannt
    A parametric study of planform and aeroelastic effects on aerodynamic center, alpha- and q-stability derivatives (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Summarized are the aerodynamic center, alpha and q- aeroelastic effects on fighter-type aircraft in the 18,700 N gross range. The results indicate that with proper tailoring of planform (fixed or variable sweep), stiffner and elastic axis location it is possible to minimize trim requirements between selected extreme conditions. The inertial effects were found to be small for this class of aircraft.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-2117 , CRES-FRL-72-002
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 175
    facet.materialart.
    Unbekannt
    Measurements of surface-pressure fluctuations on the XB-70 airplane at local Mach numbers up to 2.45 (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Measurements of surface-pressure fluctuations were made at two locations on the XB-70 airplane for nine flight-test conditions encompassing a local Mach number range from 0.35 to 2.45. These measurements are presented in the form of estimated power spectral densities, coherence functions, and narrow-band-convection velocities. The estimated power spectral densities compared favorably with wind-tunnel data obtained by other experimenters. The coherence function and convection velocity data supported conclusions by other experimenters that low-frequency surface-pressure fluctuations consist of small-scale turbulence components with low convection velocity.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TN-D-7226 , H-714
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 176
    facet.materialart.
    Unbekannt
    A method for predicting shock shapes and pressure distributions on two dimensional airfoils at large angles of attack (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A method is presented for determining shock envelopes and pressure distributions for two-dimensional airfoils at angles of attack sufficiently large to cause shock detachment and subsonic flow over the windward surface of the airfoil. Correlation functions obtained from exact solutions are used to relate the shock standoff distance at the stagnation and sonic points of the body through a suitable choice for the shock shape. The necessary correlation functions were obtained from perfect gas solutions but may be extended to any gas flow for which the normal shock-density ratio can be specified.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TN-D-7197 , A-4564
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 177
    facet.materialart.
    Unbekannt
    Low subsonic aerodynamic characteristics of a shuttle orbiter having 35 deg trapezoidal wing and 75 deg inboard glove (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: An investigation has been made in a low-turbulence pressure tunnel to determine the subsonic aerodynamic characteristics of 0.01875-scale model of a shuttle orbiter configuration having a 35 deg swept trapezoidal wing and 75 deg swept fixed glove located ahead of the wing. Tests were made at Mach numbers below 0.30 and Reynolds numbers, based on body length, from 12.32 x one million to 24.65 x one million, with most of the tests being made at a Reynolds number of 12.32 x one million. Variables investigated included configuration components in combination, elevon deflections and rudder deflections in combination, and dorsal-tail roll-out angle.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-X-2701 , L-8674
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 178
    facet.materialart.
    Unbekannt
    Steady inviscid transonic flows over planar airfoils: A search for a simplified procedure (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A finite difference procedure based upon a system of unsteady equations in proper conservation form with either exact or small disturbance steady terms is used to calculate the steady flows over several classes of airfoils. The airfoil condition is fulfilled on a slab whose upstream extremity is a semi-circle overlaying the airfoil leading edge circle. The limitations of the small disturbance equations are demonstrated in an extreme example of a blunt-nosed, aft-cambered airfoil. The necessity of using the equations in proper conservation form to capture the shock properly is stressed. Ability of the steady relaxation procedures to capture the shock is briefly examined.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-2186
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 179
    facet.materialart.
    Unbekannt
    Some observed effects of part-span dampers on rotating blade row performance near design point (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Detailed measured radial distributions of flow parameters for eight rotors with part-span dampers are used to study the effects of dampers on rotor performance and flow parameters at near design operation. All rotors had a blade tip diameter of about 20 in. and operated at a blade tip speed of about 1400 ft/sec. Several examples demonstrate that, when the local loss variations in the damper flow region are included in an aerodynamic design or analysis procedure, the computed spanwise distributions of flow parameters compare closely with measured distributions.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-X-2696 , E-7067
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 180
    facet.materialart.
    Unbekannt
    Pressures and temperatures on the lower surfaces of an externally blown flap system during full-scale ground tests (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Full-scale ground tests of an externally blown flap system were made using the wing of an F-111B airplane and a CF700 engine. Pressure and temperature distributions were determined on the undersurface of the wing, vane, and flap for two engine exhaust nozzles (conical and daisy) at several engine power levels and engine/wing positions. The test were made with no airflow over the wing. The wing sweep angle was fixed at e6 deg; and the angle of incidence between the engine and the wing was fixed at 3 deg; and the flap was in the retracted, deflected 35 deg, and deflected 60 deg positions. The pressure load obtained by integrating the local pressures on the undersurface of the flap, F sub p was approximately three times greater at the 60 deg flap position than at the 35 deg flap position. At the 60 deg flap position, F sub p was between 40 percent and 55 percent of the engine thrust over the measured range of thrust. More than 90 percent of F sub p was contained within plus or minus 20 percent of the flap span centered around the engine exhaust centerline with both nozzle configurations. Maximum temperatures recorded on the flaps were 218 C (424 F) and 180 C (356 F) for the conical and daisy nozzles, repectively,
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TN-D-7138 , H-729
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 181
    facet.materialart.
    Unbekannt
    Prediction of static aerodynamic characteristics for space-shuttle-like and other bodies at angles of attack from 0 deg to 180 deg (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: An engineering-type procedure is presented for computing normal-force, axial-force, and pitching-moment coefficients for bodies at angles of attack from 0 deg to 180 deg. The procedure is ideally suited for estimating the aerodynamic characteristics of space shuttle booster-like bodies because of the wide range of angles of attack, Mach numbers, and Reynolds numbers to be encountered. The analytical formulas, plots, and references given are also applicable for shuttle orbiter, missile, and aircraft-like bodies of both circular and noncircular cross section. The method for computing normal-force and pitching-moment coefficients is based upon the original proposal of Allen that the crossflow or lift distribution over a body can be expressed as the sum of slender-body potential term and an empirical viscous crossflow term. Although experimental data from which to verify the procedure at very high angles of attack are extremely limited, the comparisons made thus far of computed with experimental results are good. In this report the procedure has been shown to be capable of predicting reasonably well the experimental variation of C sub N, C sub A, C sub m, and x sub ac/l with angle of attack for nine bodies of revolution at a free-stream Mach number of 2.86.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TN-D-6996 , A-4500
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 182
    facet.materialart.
    Unbekannt
    Summary of design and blade-element performance data for 12 axial-flow pump rotor configurations (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A collection of noncavitating blade-element performance data for 12 axial-flow pump rotor configurations is presented in tabular form. Rotor design philosophy, test apparatus and procedure, and data reduction and evaluation are discussed. A data storage and recall computer program is described. All but one of the rotor configurations considered were composed of double-circular-arc blade sections and were designed for high inlet relative flow angles. Hub-tip radius ranged from 0.40 to 0.90.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TN-D-7074 , E-6624
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 183
    facet.materialart.
    Unbekannt
    The effects of leading-edge serrations on reducing flow unsteadiness about airfoils, an experimental and analytical investigation (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: High frequency surface pressure measurements were obtained from wind-tunnel tests over the Reynolds number range 1.2 times one million to 6.2 times one million on a rectangular wing of NACA 63-009 airfoil section. Measurements were also obtained with a wide selection of leading-edge serrations added to the basic airfoil. Under a two-dimensional laminar bubble very close to the leading edge of the basic airfoil there is a large apatial peak in rms pressure. Frequency analysis of the pressure signals in this region show a large, high-frequency energy peak which is interpreted as an oscillation in size and position of the bubble. The serrations divide the bubble into segments and reduce the peak rms pressures. A low Reynolds number flow visualization test on a hydrofoil in water was also conducted. A von Karman vortex street was found trailing from the rear of the foil. Its frequency is at a much lower Strouhal number than in the high Reynolds number experiment, and is related to the trailing-edge and boundary-layer thicknesses.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-2344
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 184
    facet.materialart.
    Unbekannt
    Performance of transonic fan stage with weight flow per unit annulus area of 198 kilograms per second per square meter (40.6(lb/sec)/sq ft) (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The overall and blade-element performance are presented for an air compressor stage designed to study the effect of weight flow per unit annulus area on efficiency and flow range. At the design speed of 424.8 m/sec the peak efficiency of 0.81 occurred at the design weight flow and a total pressure ratio of 1.56. Design pressure ratio and weight flow were 1.57 and 29.5 kg/sec (65.0 lb/sec), respectively. Stall margin at design speed was 19 percent based on the weight flow and pressure ratio at peak efficiency and at stall.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-X-2905 , E-7205
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 185
    facet.materialart.
    Unbekannt
    FORTRAN program for predicting off-design performance of centrifugal compressors (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A FORTRAN program for calculating the off-design performance of centrifugal compressors with channel diffusers is presented. Use of the program requires complete knowledge of the overall impeller and diffuser geometries. Individual losses are computed using analytical equations and empirical correlations which relate loss levels to velocity diagram characteristics and overall geometry. On a given speed line compressor performance is calculated for a range of inlet velocity levels. At flow rates between surge and choke, individual efficiency decrements, compressor overall efficiency, and compressor total pressure ratio are tabulated. An example case of performance comparison with a compressor built by a commercial engine manufacturer is presented to demonstrate the correlation with limited experimental data.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TN-D-7487 , E-7480
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 186
    facet.materialart.
    Unbekannt
    Base pressure in laminar supersonic flow. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: An asymptotic description is proposed for supersonic laminar flow over a wedge or a backward-facing step, for large Reynolds number and for a base or step height which is small compared with the boundary-layer length. The analysis is carried out for adiabatic wall conditions and a viscosity coefficient proportional to temperature. In a particular limit corresponding to a very thick boundary layer, a similarity law is obtained for the base pressure. For a thinner boundary layer an asymptotic form for the base pressure is obtained which shows the dependence on the parameters explicitly and which permits good agreement with experiment. This latter result is based on an inviscid-flow approximation for the corner expansion and for reattachment with viscous forces important primarily in a thin sublayer about the dividing streamline. A prediction of the pressure distribution at reattachment is given and the result is compared with experimental pressure distributions.
    Schlagwort(e): AERODYNAMICS
    Materialart: AD-785786 , AROD-7324-4-E , Journal of Fluid Mechanics; 60; Sept. 18
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 187
    facet.materialart.
    Unbekannt
    The transonic aerofoil problem with embedded shocks. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The integral equation approach to the mixed flow problem of infinite wings at high subsonic speeds is adopted for non-circulatory and circulatory (lifting) flows. The solutions are determined from a system of non-linear algebraic equations and, to ensure always unique solutions, the method of differentiation with respect to a parameter has been applied. The resulting Cauchy problem is then solved with the linearised flow solution as the initial value vector. For the case of embedded shocks in the flow field, the method of steepest descent has been added to the calculation scheme. Results for subcritical and supercritical flows past aerofoils are given and compared with solutions obtained by finite-difference techniques.
    Schlagwort(e): AERODYNAMICS
    Materialart: Aeronautical Quarterly; 24; May 1973
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 188
    facet.materialart.
    Unbekannt
    Transonic flow past lifting wings. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Work conducted by Norstrud (1971) has been extended to lifting flows with the inclusion of embedded continuous supercritical regions. The approach taken follows some fundamental steps proposed for two-dimensional flows by Oswatitsch (1950). The governing integral equation is replaced by a system of nonlinear algebraic equations. The method of parametric differentiation is applied to the solution of this system of equations. The analytical analysis is discussed together with a numerical analysis in the case of a wing configuration with arbitrary thickness distribution.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal; 11; May 1973
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 189
    facet.materialart.
    Unbekannt
    Model tests on unsteady rotor wake effects. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A qualitative model of unsteady asymmetric wake effects is considered, taking into account a progressing blade flapping mode in which each blade flaps in a rotating frame of reference. The rotor model used for the tests is two bladed. The experimental data are compared with an analytical flapping response. It is found that the steady wake effects are largest at zero advance ratio and low collective pitch. The effects remain significant at higher advance ratios and collective pitch settings.
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Aircraft; 10; Jan. 197
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 190
    facet.materialart.
    Unbekannt
    Wing tip vortex measurements with laser Doppler systems (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The vortex velocity field produced by a rectangular wing in a subsonic wind tunnel was measured using two laser Doppler velocimeter systems. One system made three dimensional mean velocity measurements and the other made one dimensional turbulence measurements. The systems and test procedures are described and comparisons of the measurements are made. The data defined a strong spiral motion in the vortex formation process.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-124444 , RTR-002-3
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 191
    facet.materialart.
    Unbekannt
    An experimental investigation of three oblique-wing and body combinations at Mach numbers between 0.60 and 1.40 (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: An experimental investigation was conducted in an 11- by 11-foot transonic wind tunnel to determine the aerodynamic characteristics of three oblique high aspect ratio wings in combination with a high fineness-ratio Sears-Haack body. The three wings had the same elliptical planform and base line curvature but had different airfoil sections. One wing had an airfoil section designed to have a lift coefficient of 1.0 at a Mach number of 0.7, another to have shock-free supersonic flow over the upper surface, and the other to have a lift coefficient of 1.3 at a Mach number of 0.6. Longitudinal and lateral-directional stability data were obtained at wing yaw angles of 0 deg, 45 deg, 50 deg, and 60 deg over a test Mach number range from 0.6 to 1.4 for angles of attack between minus 7 deg and 9 deg. Reynolds numbers for the study were 4 and 6 million per foot. Flow-visualization studies were made to examine the nature of the flow on the wing surfaces. Notable differences were found in the aerodynamic characteristics of the three wing-body combinations, particularly in the lateral-directional characteristics.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-X-62256
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 192
    facet.materialart.
    Unbekannt
    Two-dimensional analytical and experimental performance comparison for a compressor stator section with D-factor of 0.47 (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Analytically computed flow parameters were compared to measured values for the midspan double-circular-arc section of a stator in subsonic flow. Analytical procedures included calculations for inviscid flow, blade surface boundary layers, and loss coefficients. Comparisons were made at three incidence angles. Methods for prescribing the exit fluid angle in inviscid flow calculations were investigated. Measured loss coefficients were compared to calculated values. Two methods for predicting performance involving iterative use of ideal flow and boundary layer calculations were investigated.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TN-D-7425 , E-7280
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 193
    facet.materialart.
    Unbekannt
    Experimental investigation of a large-scale, two-dimensional, mixed-compression inlet system: Internal performance and drag at transonic conditions, free stream Mach equals 0.6 to 1.28 (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A large scale, variable-geometry inlet system with a design Mach number of 3.0 was tested at Mach numbers from 0.6 to 1.28. Variable features for off-design operation are an adjustable-height ramp system and a translating cowl. Experimental results are presented for transonic ramp and cowl positions showing the effect of throat boundary layer bleed and vortex generators on engine-face performance. Detailed pressure and force-balance data are used to evaluate transonic drag characteristics.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TN-D-7445 , A-4775
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 194
    facet.materialart.
    Unbekannt
    Research on the sonic boom problem. Part 1: Second-order solutions for the flow field around slender bodies in supersonic flow for sonic boom analysis (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A second-order theory for supersonic flow past slender bodies is presented. Through the introduction of characteristic coordinates as independent variables and the expansion procedure proposed by Lin and Oswatitsch, a uniformly valid solution is obtained for the whole flow field in the axisymmetric case and for far field in the general three-dimensional case. For distances far from the body the theory is an extension of Whitham's first-order solution and for the domain close to the body it is a modification of Van Dyke's second-order solution in the axisymmetric case. From the theory useful formulas relating flow deflections to the Whitham F-function are derived, which permits one to determine the sonic boom strength from wind tunnel measurements fairly close to the body.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-2339 , FFA-AU-621-PT-1
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 195
    facet.materialart.
    Unbekannt
    Experimental investigation of boundary layers in an axisymmetric, Mach 2.5, mixed-compression inlet (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: An experimental investigation has been made of the boundary layer flow in a supersonic axisymmetric inlet. The inlet was designed for Mach 2.5 and had a 60 percent internal supersonic area contraction. Porous bleed regions were incorporated into both the cowl and centerbody for boundary-layer control. Five bleed configurations were studied; these included bleed regions upstream of, across, and downstream of the experimentally determined shock-impingement points. The tests were conducted at tunnel unit Reynolds numbers of 8.2 million and 2.7 million per meter. Static-pressure measurements were made along the internal inlet surfaces. In addition to locating the position of the shocks, these measurements also showed local regions of expansion resulting from the suction bleed. Boundary-layer profiles were measured with translating pitot pressure probes located on both sides of the shock-impingement points on the cowl and centerbody. These measurements showed that the boundary-layer profiles were distorted in the vicinity of the terminal shock.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-X-2902 , E-7380
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 196
    facet.materialart.
    Unbekannt
    A Study of Trailing Edge Blowing as a Means of Reducing Noise Generated by the Interaction of Flow with a Surface (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A system for reducing the noise generated when a jet impinges against a flap is described. The eddies formed by the alternate zones of positive and negative pressure on the flap surface are identified as the sound source. In the proposed concept, a stream of low velocity secondary air is ejected from a slot near the trailing edge of the flap as a buffer between the flap and the primary air jet to reduce the intensity of the fluctuating surface pressure field near the flap edge and thus reduce the intensity of the aerodynamic noise.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-132270 , BBN-2593
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 197
    facet.materialart.
    Unbekannt
    Pressure recovery performance of conical diffusers at high subsonic Mach numbers (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The pressure recovery performance of conical diffusers has been measured for a wide range of geometries and inlet flow conditions. The approximate level and location (in terms of diffuser geometry of optimum performance were determined. Throat Mach numbers from low subsonic (m sub t equals 0.2) through choking (m sub t equals 1.0) were investigated in combination with throat blockage from 0.03 to 0.12. For fixed Mach number, performance was measured over a fourfold range of inlet Reynolds number. Maps of pressure recovery are presented as a function of diffuser geometry for fixed sets of inlet conditions. The influence of inlet blockage, throat Mach number, and inlet Reynolds number is discussed.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-2299 , TN-165
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 198
    facet.materialart.
    Unbekannt
    Finite element analysis and computer graphics visualization of flow around pitching and plunging airfoils (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A general computational method for analyzing unsteady flow around pitching and plunging airfoils was developed. The finite element method was applied in developing an efficient numerical procedure for the solution of equations describing the flow around airfoils. The numerical results were employed in conjunction with computer graphics techniques to produce visualization of the flow. The investigation involved mathematical model studies of flow in two phases: (1) analysis of a potential flow formulation and (2) analysis of an incompressible, unsteady, viscous flow from Navier-Stokes equations.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-2249
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 199
    facet.materialart.
    Unbekannt
    Subsonic aerodynamic characteristics of a space shuttle orbiter (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A space shuttle orbiter has been studied in a low turbulence pressure tunnel at a Mach number of 0.25 and Reynolds numbers from 4.17 x 1 million to 29. 17 x 1 million, based model length. The angle of attack range was about -4 to 24 deg at angles of sideslip of 0 and 5 deg. Static longitudinal and lateral directional aerodynamic characteristics were obtained for elevon deflections from 0 to -20 deg. The model was longitudinally stable at all test conditions; however, depending on Reynolds number and eleven deflection angle, the model was directionally unstable for angles of attack between 9 and 17 deg. The model had a maximum trimmed lift drag ratio of about 6.25 which occured at an angle of attack of about 9 deg with an elevon deflection of -10 deg.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-X-2786 , L-8765
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 200
    facet.materialart.
    Unbekannt
    Local flow measurements at the inlet spike tip of a Mach 3 supersonic cruise airplane (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The flow field at the left inlet spike tip of a YF-12A airplane was examined using at 26 deg included angle conical flow sensor to obtain measurements at free-stream Mach numbers from 1.6 to 3.0. Local flow angularity, Mach number, impact pressure, and mass flow were determined and compared with free-stream values. Local flow changes occurred at the same time as free-stream changes. The local flow usually approached the spike centerline from the upper outboard side because of spike cant and toe-in. Free-stream Mach number influenced the local flow angularity; as Mach number increased above 2.2, local angle of attack increased and local sideslip angle decreased. Local Mach number was generally 3 percent less than free-stream Mach number. Impact-pressure ratio and mass flow ratio increased as free-stream Mach number increased above 2.2, indicating a beneficial forebody compression effect. No degradation of the spike tip instrumentation was observed after more than 40 flights in the high-speed thermal environment encountered by the airplane. The sensor is rugged, simple, and sensitive to small flow changes. It can provide accurate imputs necessary to control an inlet.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TN-D-6987 , H-722
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
Schließen ⊗
Diese Webseite nutzt Cookies und das Analyse-Tool Matomo. Weitere Informationen finden Sie hier...