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  • Analytical Chemistry and Spectroscopy  (628)
  • Physics  (487)
  • AERODYNAMICS  (383)
  • Life and Medical Sciences  (374)
  • Engineering  (234)
  • Animals
  • INSTRUMENTATION AND PHOTOGRAPHY
  • 1975-1979  (2,325)
  • 1925-1929
  • 1977  (2,325)
Collection
Keywords
Publisher
Years
  • 1975-1979  (2,325)
  • 1925-1929
Year
  • 101
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    Improvement of maneuver aerodynamics by spanwise blowing (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Spanwise blowing was used to test a generalized wind-tunnel model to investigate component concepts in order to provide improved maneuver characteristics for advanced fighter aircraft. Primary emphasis was placed on performance, stability, and control at high angles of attack and subsonic speeds. Test data were obtained in the Langley high speed 7 by 10 foot tunnel at free stream Mach numbers up to 0.50 for a range of model angles of attack, jet momentum coefficients, and leading and trailing edge flap deflection angles. Spanwise blowing on a 44 deg swept trapezoidal wing resulted in leading edge vortex enhancement with subsequent large vortex induced lift increments and drag polar improvements at the higher angles of attack. Small deflections of a leading edge flap delayed these lift and drag benefits to higher angles of attack. In addition, blowing was more effective at higher Mach numbers. Spanwise blowing in conjunction with a deflected trailing edge flap resulted in lift and drag benefits that exceeded the summation of the effects of each high lift device acting alone. Asymmetric blowing was an effective lateral control device at the higher angles of attack.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1065 , L-11642
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  • 102
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    Flow separation detector (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An arrangement for sensing the fluid separation along a surface which employs a thermally insulating element having a continuous surface blending into and forming a part of the fluid flow surface is described. A sudden decrease in the temperature of the downstream sensor conductor and concomitant increase in the temperature of the upstream sensor conductor is an indication of the separation. When the temperatures are returned to the state achieved during normal flow, the indicator thereby indicates the normal, attached fluid flow. The conductors may be, for example, wires or thin films, and should be within the viscous sub-layer of the expected fluid flow. A single heater and several pairs of sensors and corresponding sensor conductors may be used to detect not only the fluid flow and the separation, but the direction of the fluid flow, over the fluid flow surface.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
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  • 103
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    Aerodynamic characteristics of a small-scale straight and swept-back wing with knee-blown jet flaps (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Two sting-mounted, 50.8 cm (20 in.) span, knee-blown, jet-flap models were tested in a large (2.1- by 2.5-m (7- by 10-ft) subsonic wind tunnel. A straight- and swept-wing model were tested with fixed flap deflection with various combinations of full-span leading-edge slats. The swept-wing model was also tested with wing tip extensions. Data were taken at angles-of-attack between 0 deg and 40 deg, at dynamic pressures between 143.6 N/sq m (3 lb/sq ft) and 239.4 N/sq m (5 lb/sq ft), and at Reynolds numbers (based on wing chord) ranging from 100,000 to 132,000. Jet flap momentum blowing coefficients up to 10 were used. Lift, drag, and pitching-moment coefficients, and exit flow profiles for the flap blowing are presented in graphical form without analysis.
    Keywords: AERODYNAMICS
    Type: NASA-TM-78427 , A-7161
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  • 104
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    A gas filter correlation monitor for CO, CH4, and HCl (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A fast response instrument for monitoring the atmospheric constituents CO, CH4, and HCl, using a modified nondispersive infrared technique, was designed, assembled, and tested. This gas filter correlation method uses a sample of gas to provide a selective filter for radiation absorbed in a gas mixture containing the specified gas. Depending on the spectral line broadening, temperature, and optical depth of the gas selected, exceptionally high spectral resolution may be attained. A description of the single beam rotating cell system and its specific application is presented along with the signal processing circuit. Calibrations of the instrument show that the technique can be used to measure CO, CH4, and HCl concentrations as small as 5 ppm-m. A field version was employed to measure diurnal variations of CO and CH4 and the interfering effects of other atmospheric gases were analyzed.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-TP-1113 , L-11868
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  • 105
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    Reliability analysis of forty-five strain-gage systems mounted on the first fan stage of a YF-100 engine (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The reliability of 45 state-of-the-art strain gage systems under full scale engine testing was investigated. The flame spray process was used to install 23 systems on the first fan rotor of a YF-100 engine; the others were epoxy cemented. A total of 56 percent of the systems failed in 11 hours of engine operation. Flame spray system failures were primarily due to high gage resistance, probably caused by high stress levels. Epoxy system failures were principally erosion failures, but only on the concave side of the blade. Lead-wire failures between the blade-to-disk jump and the control room could not be analyzed.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-TM-73724 , E-9274
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  • 106
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    Microbial load monitor (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Design analysis of a microbial load monitor system flight engineering model was presented. Checkout of the card taper and media pump system was fabricated as well as the final two incubating reading heads, the sample receiving and card loading device assembly, related sterility testing, and software. Progress in these areas was summarized.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-CR-151565 , MDC-E1781
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  • 107
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    Optically selective, acoustically resonant gas detecting transducer (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A gas analyzer is disclosed which responds to the resonant absorption or emission spectrum of a specific gas by producing an acoustic resonance in a chamber containing a sample of that gas, and which measures the amount of that emission or absorption by measuring the strength of that acoustic resonance, e.g., the maximum periodic pressure, velocity or density achieved. In the preferred embodiment, a light beam is modulated periodically at the acoustical resonance frequency of a closed chamber which contains an optically dense sample of the gas of interest. Periodic heating of the absorbing gas by the light beam causes a cyclic expansion, movement, and pressure within the gas. An amplitude is reached where the increased losses were the cyclic radiation energy received. A transducing system is inclined for converting the pressure variations of the resonant gas into electronic readout signals.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
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  • 108
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    Computation of transonic boattail flow with separation (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The relaxation procedure of South and Jameson for the full potential transonic flow equation was coupled to a modified Reshotko-Tucker integral boundary-layer technique with an empirical model for separated flow. The viscous and inviscid flows were solved iteratively until convergence was obtained. This iterative method was then applied to the subsonic and transonic flow over a series of axisymmetric circular-arc boattails with solid jet plume simulators. Comparisons of theoretical and experimental surface pressures and boattail drag are presented over a free-stream Mach numbers below 0.90. The qualitative variation of boattail drag with free-stream Mach number and boattail angle well into the region of transonic drag rise was correctly predicted; however, the absolute drag levels were significantly underpredicted. For separated flows, the empirical discriminating streamline model gives good results up to a free-stream Mach number of about 0.90 and allows reasonable predictions for shock-induced separation if the proper separation location and separation turning angle are known.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1070 , L-11669
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  • 109
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    Effects of roughness size on the position of boundary-layer transition and on the aerodynamic characteristics of a 55 deg. swept delta wing at supersonic speeds (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation was conducted to determine the effects of roughness size on the position of boundary layer transition and on the aerodynamic characteristics of a 55 deg swept delta wing model. Results are presented and discussed for wind tunnel tests conducted at free stream Mach numbers from 1.50 to 4.63, Reynolds numbers per meter from 3,300,000 to 1.6 x 10 to the 7th power, angles of attack from -8 to 16 deg, and roughness sizes ranging from 0.027 cm sand grit to 0.127 cm high cylinders. Comparisons were made with existing flat plate data. An approximate method was derived for predicting the drag of roughness elements used in boundary layer trips.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1027 , L-11496
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  • 110
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    Theoretical and experimental analysis of longitudinal and lateral aerodynamic characteristics of skewed wings at subsonic speeds to high angles of attack (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effects of sweep and aspect ratio on the longitudinal and lateral-directional aerodynamic characteristics of low-aspect-ratio skewed (oblique) wings having separation-induced vortex flows along leading and side edges were investigated in the Langley high-speed 7- by 10-foot tunnel at a low-subsonic Mach number. The theoretical analysis used the vortex-lattice method for estimating attached-flow aerodynamic characteristics and the leading-edge suction analogy of Polhamus for estimating separation induced vortex-flow effects. Experimental results were compared with asymmetric, separated, vortex flow theory.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-8512 , L-11230
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  • 111
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    Effects of deflected thrust on the longitudinal aerodynamic characteristics of a close-coupled wing-canard configuration (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effects of power on the longitudinal aerodynamic characteristics of a close-coupled wing-canard fighter configuration with partial-span rectangular nozzles at the trailing edge of the wing were investigated. Data were obtained on a basic wing-strake configuration for nozzle and flap deflections from 0 deg to 30 deg and for nominal thrust coefficients from 0 to 0.30. The model was tested over an angle-of-attack range from -2 deg to 40 deg at Mach numbers of 0.15 and 0.18. Results show substantial improvements in lift-curve slope, in maximum lift, and in drag-due-to-lift efficiency when the canard and strakes have been added to the basic wing-fuselage (wing-alone) configuration. Addition of power increased both lift-curve slope and maximum lift, improved longitudinal stability, and reduced drag due to lift on both the wing-canard and wing-canard-strake configurations. These beneficial effects are primarily derived from boundary-layer control due to moderate thrust coefficients which delay flow separation on the nozzle and inboard portion of the wing flaps.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1090 , L-11886
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  • 112
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    Investigation of compressible vortex flow characteristics (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The nature of intense air vortices was studied and the factors which determine the intensity and rate of decay of both single and pairs of vortices were investigated. Vortex parameters of axial pressure differential, circulation, outflow rates, separation distance and directions of rotation were varied. Unconfined vortices, generated by a single rotating cage, were intensified by an increasing axial pressure gradient. Breakdown occurred when the axial gradient became negligible. The core radius was a function of the axial gradient. Dual vortices, generated by two counterrotating cages, rotated opposite to the attached cages. With minimum spacing only one vortex was formed which rotated in a direction opposite to the attached cage. When one cage rotated at half the speed of the other cage, one vortex formed at the higher speed cage rotating in the cage direction.
    Keywords: AERODYNAMICS
    Type: NASA-CR-145261 , CRINC-FRL-260-1
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  • 113
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    Subsonic longitudinal and lateral directional static stability characteristics of a variable sweep fighter configuration employing various control surface deflections at angles of attack of 0 deg to 50 deg and large sideslip angles (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A variable sweep fighter configuration with the wing in the 22 deg sweep position having leading edge slats and trailing edge flaps on the outboard panels was tested at a Mach number of 0.15 in the Langley 7- by 10-foot high speed tunnel. The angle of attack range was 0 deg to 50 deg and the sideslip angle range was -20 deg to 20 deg. Pitch, roll, and yaw control effectiveness were studied as well as the effects of spoilers. The data are presented without analysis.
    Keywords: AERODYNAMICS
    Type: NASA-TM-74050
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  • 114
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    Computations of supersonic viscous flow over a finite-width plate (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Finite difference methods were applied to solve the parabolic Navier-Stokes equations for the flow over a finite width plate at 0 deg and 10 deg angles of attack. The methods were developed on the basis of the operator factorization concept resulting in the split of a three dimensional equation into successive two dimensional equations. Backward and centered implicit factorization schemes, were used and their results were compared. Available numerical solutions and experimental data obtained at low Reynolds number conditions were also used for comparison. The backward implicit method provides a more successful solution, which ranges from the merged layer to the strong interaction regimes. Detailed structures were revealed of the shear layer around and behind the side edge.
    Keywords: AERODYNAMICS
    Type: NASA-CR-151534 , JSC-13140 , TR-7004
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  • 115
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    Ground simulation and tunnel blockage for a swept, jet-flapped wing tested to very high lift coefficients (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Ground effects experiments and large/small tunnel interference studies were carried out on a model with a 20 inch (50.8 cm) 25 degree swept wing. The wing is slatted, has a 60 degree knee-blown flap and can be fitted with unflapped tips. A tail rake of pitch-yaw probes can be fitted to the fuselage. Certain check tests were also made with a very similar straight-wing model.
    Keywords: AERODYNAMICS
    Type: NASA-CR-152032
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  • 116
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    Low gravity phase separator (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An apparatus is described for phase separating a gas-liquid mixture as might exist in a subcritical cryogenic helium vessel for cooling a superconducting magnet at low gravity such as in planetary orbit, permitting conservation of the liquid and extended service life of the superconducting magnet.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
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  • 117
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    Photo sensor array technology development (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The development of an improved capability photo sensor array imager for use in a Viking '75 type facsimile camera is presented. This imager consists of silicon photodiodes and lead sulfide detectors to cover a spectral range from 0.4 to 2.7 microns. An optical design specifying filter configurations and convergence angles is described. Three electronics design approaches: AC-chopped light, DC-dual detector, and DC-single detector, are investigated. Experimental and calculated results are compared whenever possible using breadboard testing and tolerance analysis techniques. Results show that any design used must be forgiving of the relative instability of lead sulfide detectors. A final design using lead sulfide detectors and associated electronics is implemented by fabrication of a hybrid prototype device. Test results of this device show a good agreement with calculated values.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-CR-145269 , MCR-77-563
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  • 118
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    Supersonic aerodynamic characteristics of a Sparrow 3 type missile model with wing controls and comparison with existing tail-control results (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation was conducted on a model of a wing control version of the Sparrow III type missile to determine the static aerodynamic characteristics over an angle of attack range from 0 deg to 40 deg for Mach numbers from 1.50 to 4.60.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1078 , L-11715
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  • 119
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    Spin-tunnel investigation of the spinning characteristics of typical single-engine general aviation airplane designs. 2: Low-wing model A; tail parachute diameter and canopy distance for emergency spin recovery (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A spin tunnel study is reported on a scale model of a research airplane typical of low-wing, single-engine, light general aviation airplanes to determine the tail parachute diameter and canopy distance (riser length plus suspension-line length) required for energency spin recovery. Nine tail configurations were tested, resulting in a wide range of developed spin conditions, including steep spins and flat spins. The results indicate that the full-scale parachute diameter required for satisfactory recovery from the most critical conditions investigated is about 3.2 m and that the canopy distance, which was found to be critical for flat spins, should be between 4.6 and 6.1 m.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1076 , L-11804
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  • 120
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    An experimental and analytical investigation of proprotor whirl flutter (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of an experimental parametric investigation of whirl flutter are presented for a model consisting of a windmilling propeller-rotor, or proprotor, having blades with offset flapping hinges mounted on a rigid pylon with flexibility in pitch and yaw. The investigation was motivated by the need to establish a large data base from which to assess the predictability of whirl flutter for a proprotor since some question has been raised as to whether flutter in the forward whirl mode could be predicted with confidence. To provide the necessary data base, the parametric study included variation in the pylon pitch and yaw stiffnesses, flapping hinge offset, and blade kinematic pitch-flap coupling over a large range of advance ratios. Cases of forward whirl flutter and of backward whirl flutter are documented. Measured whirl flutter characteristics were shown to be in good agreement with predictions from two different linear stability analyses which employed simple, two dimensional, quasi-steady aerodynamics for the blade loading. On the basis of these results, it appears that proprotor whirl flutter, both forward and backward, can be predicted.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1047 , L-11656
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  • 121
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    Performance of twin two-dimensional wedge nozzles including thrust vectoring and reversing effects at speeds up to Mach 2.20 (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Transonic tunnel and supersonic pressure tunnel tests were reformed to determine the performance characteristics of twin nonaxisymmetric or two-dimensional nozzles with fixed shrouds and variable-geometry wedges. The effects of thrust vectoring, reversing, and installation of various tails were also studied. The investigation was conducted statically and at flight speeds up to a Mach number of 2.20. The total pressure ratio of the simulated jet exhaust was varied up to approximately 26 depending on Mach number. The Reynolds number per meter varied up to 13.20 x 1 million. An analytical study was made to determine the effect on calculated wave drag by varying the mathematical model used to simulate nozzle jet-exhaust plume.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-8449 , L-11277
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  • 122
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    Aerodynamic characteristics at Mach numbers from 0.33 to 1.20 of a wing-body design concept for a hypersonic research airplane (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation of the static aerodynamic characteristics of a model of one design concept for the proposed National Hypersonic Flight Research Facility was conducted in the Langley 8 foot transonic pressure tunnel. The experiment consisted of configuration buildup from the basic body by adding a wing, center vertical tail, and a three module or six module scramjet engine. The freestream test Mach numbers were 0.33, 0.80, 0.90, 0.95, 0.98, 1.10, and 1.20 at Reynolds numbers per meter ranging from 4.8 x 1 million to 10.4 x 1 million. The test angle of attack range was approximately -4 deg to 22 deg at constant angles of sideslip of 0 deg and 4 deg; the angle of sideslip ranged from about -6 deg to 6 deg at constant angles of attack of 0 deg and 17 deg. The elevons were deflected 0 deg, -10 deg, and -20 deg with rudder deflections of 0 deg and 15.6 deg.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1044 , L-11723
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  • 123
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    On the logarithmic-singularity correction in the kernel function method of subsonic lifting-surface theory (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A logarithmic-singularity correction factor is derived for use in kernel function methods associated with Multhopp's subsonic lifting-surface theory. Because of the form of the factor, a relation was formulated between the numbers of chordwise and spanwise control points needed for good accuracy. This formulation is developed and discussed. Numerical results are given to show the improvement of the computation with the new correction factor.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-8513 , L-11142
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  • 124
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    Computation of unsteady transonic flows through rotating and stationary cascades. 2: User's guide to FORTRAN program B2DATL (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Documentation for the FORTRAN program B2DATL is provided. The program input, output, and operational procedures are described; a dictionary of the principal FORTRAN variables is provided; the function of all subroutines; is outlined and flow charts of the principal subroutines and the main program are presented.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2901 , ATL-TR-205-VOL-2
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  • 125
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    Computation of unsteady transonic flows through rotating and stationary cascades. 3: Acoustic far-field analysis (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A small perturbation type analysis has been developed for the acoustic far field in an infinite duct extending upstream and downstream of an axial turbomachinery stage. The analysis is designed to interface with a numerical solution of the near field of the blade rows and, thereby, to provide the necessary closure condition to complete the statement of infinite duct boundary conditions for the subject problem. The present analysis differs from conventional inlet duct analyses in that a simple harmonic time dependence was not assumed, since a transient signal is generated by the numerical near-field solution and periodicity is attained only asymptotically. A description of the computer code developed to carry out the necessary convolutions numerically is included, as well as the results of a sample application using an impulsively initiated harmonic signal.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2902 , ATL-TR-205-VOL-3
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  • 126
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    Longitudinal aerodynamic characteristics at Mach numbers from 1.60 to 2.86 for a fixed-span missile with three wing planforms (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Effects of wing planform modifications on the longitudinal aerodynamic characteristics of a fixed span, maneuverable cruciform missile configuration were determined. A basic delta planform and two alternate trapezoidal planforms having progressively increasing tip chords were included. Data were obtained for angles of attack up to approximately -32 deg, model roll angles of 0 deg to 45 deg, and tail control deflections of 0 deg and -20 deg. The experimental drag due to lift was compared with linear values.
    Keywords: AERODYNAMICS
    Type: NASA-TM-74088 , L-11916
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  • 127
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    Supersonic longitudinal aerodynamic characteristics of two space shuttle orbiter configurations (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was conducted to determine the supersonic longitudinal aerodynamic characteristics of 0.015 scale models of the Rockwell International 089B and 139B space shuttle orbiter configurations and the 139B orbiter with a modifier forebody. The models each had a 45 deg swept delta wing that was blended into the body with an 81 deg swept fillet to form a double delta planform. The vertical tail had a split rudder deflected 27.5 deg on each side to form a speed brake. Tests were conducted at Mach numbers of 2.5, 3.9, and 4.6 at a Reynolds number, based on the body length of the 089B model, of 4,150,000. Angles of attack varied from -4 deg to 44 deg at 0 deg sideslip.
    Keywords: AERODYNAMICS
    Type: NASA-TM-74074 , L-11787
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  • 128
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    Viscous effects in aircraft trailing vortices (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The mechanism of merging of like-signed aircraft vortices leading to a rapid redistribution of trailed vorticity in a wake through both convective and turbulent processes was investigated. Research was done experimentally in a small wind tunnel and analytically through the use of a code which computes turbulent transport using a second-order closure turbulent model. Computations are reported which demonstrate the merging phenomenon, and comparisons are made with experimental results. The usefulness of point vortex computations in predicting merging was explored. Limited computations showed that jet exhaust does not appreciably alter the merging phenomenon. The effect of ambient atmospheric turbulence on the aging of an aircraft wake was investigated at a constant turbulent dissipation rate. It was shown that under stable atmospheric conditions, when atmospheric macroscales are less than or equal to the vortex spacing, misleading results may be obtained.
    Keywords: AERODYNAMICS
    Type: NASA, Washington Wake Vortex Minimization; p 61-128
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  • 129
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    Supersonic separated turbulent boundary - layer over a wavy wall (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A prediction method is developed for calculating distributions of surface heating rates, pressure and skin friction over a wavy wall in a two-dimensional supersonic flow. Of particular interest is the flow of thick turbulent boundary layers. The surface geometry and the flow conditions considered are such that there exists a strong interaction between the viscous and inviscid flow. First, using the interacting turbulent boundary layer equations, the problem is formulated in physical coordinates and then a reformulation of the governing equations in terms of Levy-Lees variables is given. Next, a numerical scheme for solving interacting boundary layer equations is adapted. A number of modifications which led to the improvement of the numerical algorithm are discussed. Finally, results are presented for flow over a train of up to six waves at various flow conditions.
    Keywords: AERODYNAMICS
    Type: NASA-CR-155329 , AFL-77-11-36
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    A technique for simulating turbulence for aerospace vehicle flight simulation studies (1977)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: An atmospheric turbulence model which accommodates variability of turbulence properties along an aerospace vehicle trajectory was developed. The technique involves the use of Dryden spectral forms in which the defining parameters are the standard deviations (sigma) and integral scales (L) of turbulence. These spectra are expressed as nondimensional functions of the nondimensional frequency Omega = omega L/V where omega is dimensional radian frequency and V is the true air speed of the aerospace vehicle. The nondimensional spectra are factored by standard techniques to obtain nondimensional linear recursive filters in the time domain whereby band-limited white-like noise can be operated upon to obtain nondimensional longitudinal, lateral, and vertical turbulence velocities, as functions of nondimensional time, tV/L, where t is time. Application of the technique to the simulation of the space shuttle orbiter entry flight phase is discussed.
    Keywords: AERODYNAMICS
    Type: NASA-TM-78141
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  • 131
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    A user's guide for V174, a program using a finite difference method to analyze transonic flow over oscillating wings (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The design and usage of a pilot program using a finite difference method for calculating the pressure distributions over harmonically oscillating wings in transonic flow are discussed. The procedure used is based on separating the velocity potential into steady and unsteady parts and linearizing the resulting unsteady differential equation for small disturbances. The steady velocity potential which must be obtained from some other program, is required for input. The unsteady differential equation is linear, complex in form with spatially varying coefficients. Because sinusoidal motion is assumed, time is not a variable. The numerical solution is obtained through a finite difference formulation and a line relaxation solution method.
    Keywords: AERODYNAMICS
    Type: NASA-CR-145214
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  • 132
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    Static aerodynamic characteristics of a 0.035-scale model of a modified NKC-135 airplane at a Mach number of 0.28 (1977)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: A 0.035-scale model fo a modified NKC-135 airplane was tested in 12-foot pressure wind tunnel to determine the effects on the static aerodynamic characteristics of modifications to the basic aircraft. Modifications investigated included: nose, lower fuselage, and upper fuselage radomes; wing pylons and pods; overwing probe; and air conditioning inlets. The investigation was performed at a Mach number of 0.28 over a Reynolds number range from 6.6 to 26.2 million per meter. Angles of attack and sideslip varied from -8 deg to 20 deg and from -18 deg to 8 deg, respectively, for various combinations of flap, aileron, and rudder deflections. A limited analysis of the test results indicates that the addition of the radomes reduces lateral-directional stability and control effectiveness of the basic aircraft.
    Keywords: AERODYNAMICS
    Type: NASA-TM-73250 , A-7068
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  • 133
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    Effect of coolant flow ejection on aerodynamic performance of low-aspect-ratio vanes. 2: Performance with coolant flow ejection at temperature ratios up to 2 (1977)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: The aerodynamic performance of a 0.5 aspect ratio turbine vane configuration with coolant flow ejection was experimentally determined in a full annular cascade. The vanes were tested at a nominal mean section ideal critical velocity ratio of 0.890 over a range of primary to coolant total temperature ratio from 1.0 to 2.08 and a range of coolant to primary total pressure ratio from 1.0 to 1.4 which corresponded to coolant flows from 3.0 to 10.7 percent of the primary flow. The variations in primary and thermodynamic efficiency and exit flow conditions with circumferential and radial position were obtained.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1057 , E-9213
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  • 134
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    Experimental performance of a 13.65-centimeter-tip-diameter tandem-bladed sweptback centrifugal compressor designed for a pressure ratio of 6 (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A 13.65 cm tip diameter backswept centrifugal impeller having a tandem inducer and a design mass flow rate of 0.907 kg/sec was experimentally investigated to establish stage and impeller characteristics. Tests were conducted with both a cascade diffuser and a vaneless diffuser. A pressure ratio of 5.9 was obtained near surge for the smallest clearance tested. Flow range at design speed was 6.3 percent for the smallest clearance test. Impeller exit to shroud axial clearance at design speed was varied to determine the effect on stage and impeller performance.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1091
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  • 135
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    Wind tunnel investigation of rotor lift and propulsive force at high speed. Test data appendix (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N78-10020.
    Keywords: AERODYNAMICS
    Type: NASA-CR-145217-APP-2 , D210-11135-2
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  • 136
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    Splined version of FLEXSTAB: A critical analysis of alternate schemes (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Recommendations are made for improved aerodynamic models and numerical schemes to be considered for inclusion into the FLEXSTAB computer program system. These recommendations are based on a critical analysis of numerical technology.
    Keywords: AERODYNAMICS
    Type: NASA-CR-152030
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  • 137
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    An Exploratory Investigation of the Effects of a Thin Plastic Film Cover on the Profile Drag of an Aircraft Wing Panel (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Exploratory wind tunnel tests were conducted on a large chord aircraft wing panel to evaluate the potential for drag reduction resulting from the application of a thin plastic film cover. The tests were conducted at a Mach number of 0.15 over a Reynolds number range from about 7 x 10 to the 6th power to 63 x 10 to the 6th power.
    Keywords: AERODYNAMICS
    Type: NASA-TM-74073
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  • 138
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    Unsteady aerodynamic modeling and active aeroelastic control (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Unsteady aerodynamic modeling techniques are developed and applied to the study of active control of elastic vehicles. The problem of active control of a supercritical flutter mode poses a definite design goal stability, and is treated in detail. The transfer functions relating the arbitrary airfoil motions to the airloads are derived from the Laplace transforms of the linearized airload expressions for incompressible two dimensional flow. The transfer function relating the motions to the circulatory part of these loads is recognized as the Theodorsen function extended to complex values of reduced frequency, and is termed the generalized Theodorsen function. Inversion of the Laplace transforms yields exact transient airloads and airfoil motions. Exact root loci of aeroelastic modes are calculated, providing quantitative information regarding subcritical and supercritical flutter conditions.
    Keywords: AERODYNAMICS
    Type: NASA-CR-148019 , SUDAAR-504
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  • 139
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    Visible optical isolator using ZnSe (1977)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: A compact Faraday effect optical isolator was constructed for visible wavelengths and tested at 5145 A. The nonreciprocal element of the isolator was polycrystalline zinc selenide placed in the magnetic field of a permanent magnet. For 5145 A the isolator had a 2.06-dB insertion loss and a 25.5-dB isolation. Indices of refraction and Verdet constants were measured for zinc selenide in the wavelength region from 4700 to 6300 A.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 16; June 197
    Format: text
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  • 140
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    Self-scanned anode array with a microchannel plate electron multiplier - The SSANACON (1977)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: A photoelectron counting detector utilizing a 128-element linear self-scanned anode array to collect the output of a dual microchannel plate electron multiplier is described. The operation of the detector, its spatial resolution and detection efficiency, and radiation behavior are discussed. The low-noise detector was developed for the Mariner Jupiter/Saturn mission UV spectrometer, and offers a large dynamic range and count rate of 0.003 per anode-sec. It can measure simultaneously two spatially separated signals differing by more than six orders of magnitude in count rate.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 16; June 197
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  • 141
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    Identification of state variables and dynamic inflow from rotor model dynamic tests (1977)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The paper describes methods for extracting unknown state variables and parameters from dynamic rotor model tests given transient cyclic pitch stirring inputs, blade root flap-bending measurements, and the form of the dynamic rotor equations, including a rotor dynamic inflow description, when none of the physical parameters are known. A simplified version of the maximum likelihood method seems best suited for this purpose. The measurement equation error covariance matrix is assumed constant during each iteration, but updated for the subsequent iteration. A detailed analysis of the suitability of the derived techniques for studying various rotor dynamic inflow effects is provided.
    Keywords: AERODYNAMICS
    Type: American Helicopter Society; vol. 22
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  • 142
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    A numerical study of the unsteady leading edge separation bubble on an oscillating airfoil (1977)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: A preliminary study of the unsteady viscous flow in the region of an airfoil leading edge was performed, in which the interaction between the viscous and inviscid flow fields is neglected. The solution method uses the finite difference form of the governing equations throughout the separated flow field and incorporates a transition model based on the integral turbulence kinetic energy equation. The validity of the numerical procedure is verified by making comparisons with analytical solutions to several test problems, including unsteady flow over a plate oscillating in its own plane. The method was then applied to the problem of unsteady viscous flow over a NACA 0012 airfoil oscillating sinusoidally in pitch. The flow field characteristics were in qualitative agreement with experimental results. The bubble moved forward on the airfoil and decreased in size as incidence was increased. Viscous flow in the leading edge region was found to be quasi-steady, while bubble height varied inversely with Reynolds number.
    Keywords: AERODYNAMICS
    Type: Computer Methods in Applied Mechanics and Engineering; 11; Apr. 197
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  • 143
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    Effect of Winglets on a First-Generation Jet Transport Wing. 2: Pressure and Spanwise Load Distributions for a Semispan Model at High Subsonic Speeds (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Pressure and spanwise load distributions on a first-generation jet transport semispan model at high subsonic speeds are presented for the basic wing and for configurations with an upper winglet only, upper and lower winglets, and a simple wing-tip extension. Selected data are discussed to show the general trends and effects of the various configurations.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-8474 , L-11026
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  • 144
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    Interferometer mirror tilt correcting system (1977)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: An interferometer is described, having several means for automatically adjusting the angular tilt of a reflecting surface in one of two paths to maintain the exit beams from the two paths parallel to each other. Three detectors at the output of the interferometer were disposed on mutually perpendicular axes which define a plane normal to the nominal exit beam axis. One detector at the origin of the axes was used as a reference for separate phase difference comparison with the outputs of the other two detectors on the X and Y axes to develop servo error signals.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
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    Cameras for semiconductor process control (1977)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: The application of X-ray topography to semiconductor process control is described, considering the novel features of the high speed camera and the difficulties associated with this technique. The most significant results on the effects of material defects on device performance are presented, including results obtained using wafers processed entirely within this institute. Defects were identified using the X-ray camera and correlations made with probe data. Also included are temperature dependent effects of material defects. Recent applications and improvements of X-ray topographs of silicon-on-sapphire and gallium arsenide are presented with a description of a real time TV system prototype and of the most recent vacuum chuck design. Discussion is included of our promotion of the use of the camera by various semiconductor manufacturers.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-CR-150459
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  • 146
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    Gas compression apparatus (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Apparatus for transferring gas from a first container to a second container of higher pressure was devised. A free-piston compressor having a driving piston and cylinder, and a smaller diameter driven piston and cylinder, comprise the apparatus. A rod member connecting the driving and driven pistons functions for mutual reciprocation in the respective cylinders. A conduit may be provided for supplying gas to the driven cylinder from the first container. Also provided is apparatus for introducing gas to the driving piston, to compress gas by the driven piston for transfer to the second higher pressure container. The system is useful in transferring spacecraft cabin oxygen into higher pressure containers for use in extravehicular activities.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
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  • 147
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    VLBI clock synchronization (1977)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The potential accuracy of VLBI (very long baseline interferometry) for clock epoch and rate comparisons was demonstrated by results from long- and short-baseline experiments. It was found that atomic clocks at widely separated sites (several thousand kilometers apart) can be synchronized to within several nanoseconds from a few minutes of VLBI observations and to within one nanosecond from several hours of observations.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: IEEE; vol. 65
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  • 148
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    Demand-type gas supply system for rocket borne thin-window proportional counters (1977)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: A simple closed loop control system has been developed to maintain the gas pressure in thin-window proportional counters during rocket flights. This system permits convenient external control of detector pressure and system flushing rate. The control system is activated at launch with the sealing of a reference volume at the existing system pressure. Inflight control to plus or minus 2 torr at a working pressure of 760 torr has been achieved on six rocket flights.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Review of Scientific Instruments; 48; Nov. 197
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  • 149
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    Limitations of the narrow-angle convergent pair (1977)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Spatial triangulations and topographies of the Martian surface derived from Viking Orbiter pictures depend on the use of symmetric narrow-angle convergent pairs. The overlap in each pair is close to 100 percent and the ground principal points virtually coincide. The analysis of this paper reveals a high degree of indeterminacy in such pairs and at least in part explains the rather disappointing precision of the associated spatial triangulations.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Photogrammetric Engineering and Remote Sensing; 43; Dec. 197
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    Viking 1975 Mars lander interactive computerized video stereophotogrammetry (1977)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: A novel computerized interactive video stereophotogrammetry system has been developed for analysis of Viking 1975 lander imaging data. Prompt, accurate, and versatile performance is achieved. Earth-returned digital imagery data are driven from a computer to a pair of video monitors. Powerful computer support enables a photogrammetrist, stereoscopically viewing the video displays, to create diverse topographic products. Profiles, representing the intersection of any definable surface with the Martian relief, are readily generated. Vertical profiles and elevation contour maps, including stereo versions, are produced. Computer overlays of map products on stereo images aid map interpretation and permit independent quality evaluation. Slaved monitors enable parallel viewing. Maps span from the immediate foreground to the remote limits of ranging capability. Surface sampler arm specific vertical profiles enable direct reading of arm commands required for sample acquisition, rock rolling, and trenching. The ranging accuracy of plus or minus 2 cm throughout the sample area degrades to plus or minus 20 m at 100-m range.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Journal of Geophysical Research; 82; Sept. 30
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  • 151
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    Charge-flow structures as polymeric early-warning fire alarm devices (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The charge-flow transistor (CFT) and its applications for fire detection and gas sensing were investigated. The utility of various thin film polymers as possible sensing materials was determined. One polymer, PAPA, showed promise as a relative humidity sensor; two others, PFI and PSB, were found to be particularly suitable for fire detection. The behavior of the charge-flow capacitor, which is basically a parallel-plate capacitor with a polymer-filled gap in the metallic tip electrode, was successfully modeled as an RC transmission line. Prototype charge-flow transistors were fabricated and tested. The effective threshold voltage of this metal oxide semiconductor was found to be dependent on whether surface or bulk conduction in the thin film was dominant. Fire tests with a PFI-coated CFT indicate good sensitivity to smouldering fires.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-CR-157215 , TR-1
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  • 152
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    Viking lander camera radiometry calibration report, volume 2 (1977)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: The requirements the performance validation, and interfaces for the RADCAM program, to convert Viking lander camera image data to radiometric units were established. A proposed algorithm is described, and an appendix summarizing the planned reduction of camera test data was included.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: JPL-PUB-77-62-VOL-2
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    Calculation of evapotranspiration using color-infrared photography (1977)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: Data from 38 color-infrared photographic missions flown during a five year period over the Gila River Phreatophyte Project in southeastern Arizona were analyzed to determine the possibility of identifying and measuring vegetative parameters and their associated hydrologic variables by spectral analysis of the photographs. The derived spectra equations are discussed, and a table of 24 statistical parameters describing the spectral and hydrologic variables is included.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-CR-156157 , GSPP-655-0
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    Scientist/AMPS equipment interface study (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The principal objective was to determine for each experiment how the operating procedures and modes of equipment onboard shuttle can be managed in real-time or near-real-time to enhance the quality of results. As part of this determination the data and display devices that a man will need for real-time management are defined. The secondary objectives, as listed in the RFQ and technical proposal, were to: (1) determine what quantities are to be measured (2) determine permissible background levels (3) decide in what portions of space measurements are to be made (4) estimate bit rates (5) establish time-lines for operating the experiments on a mission or set of missions and (6) determine the minimum set of hardware needed for real-time display. Experiment descriptions and requirements were written. The requirements of the various experiments are combined and a minimal set of joint requirements are defined.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-CR-156699
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  • 155
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    Over-under double-pass interferometer (1977)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: An over-under double pass interferometer in which the beamsplitter area and thickness can be reduced to conform only with optical flatness considerations was achieved by offsetting the optical center line of one cat's-eye retroreflector relative to the optical center line of the other in order that one split beam be folded into a plane distinct from the other folded split beam. The beamsplitter is made transparent in one area for a first folded beam to be passed to a mirror for doubling back and is made totally reflective in another area for the second folded beam to be reflected to a mirror for doubling back. The two beams thus doubled back are combined in the central, beamsplitting area of the beamsplitting and passed to a detector. This makes the beamsplitter insensitive to minimum thickness requirements and selection of material.
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  • 156
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    Return Beam Vidicon (RBV) panchromatic two-camera subsystem for LANDSAT-C (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A two-inch Return Beam Vidicon (RBV) panchromatic two camera Subsystem, together with spare components was designed and fabricated for the LANDSAT-C Satellite; the basis for the design was the Landsat 1&2 RBV Camera System. The purpose of the RBV Subsystem is to acquire high resolution pictures of the Earth for a mapping application. Where possible, residual LANDSAT 1 and 2 equipment was utilized.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-CR-156639 , AE-R-4231
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    Preliminary study of the use of the STAR-100 computer for transonic flow calculations (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An explicit method for solving the transonic small-disturbance potential equation is presented. This algorithm, which is suitable for the new vector-processor computers such as the CDC STAR-100, is compared to successive line over-relaxation (SLOR) on a simple test problem. The convergence rate of the explicit scheme is slower than that of SLOR, however, the efficiency of the explicit scheme on the STAR-100 computer is sufficient to overcome the slower convergence rate and allow an overall speedup compared to SLOR on the CYBER 175 computer.
    Keywords: AERODYNAMICS
    Type: NASA-TM-74086
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    A procedure for accurate calibration of the orientation of the three sensors in a vector magnetometer (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Procedures are described for the calibration of a vector magnetometer of high absolute accuracy. It is assumed that the calibration will be performed in the magnetic test facility of Goddard Space Flight Center (GSFC). The first main section of the report describes the test equipment and facility calibrations required. The second presents procedures for calibrating individual sensors. The third discusses the calibration of the sensor assembly. In a final section recommendations are made to GSFC for modification of the test facility required to carry out the calibration procedures.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-CR-156638
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  • 159
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    Effect of a simulated engine jet blowing above an arrow wing at Mach 2.0 (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effects of a gas jet simulating a turbojet engine exhaust blowing above a cambered and twisted arrow wing were investigated. Tests were conducted in the Langley 4-foot supersonic pressure tunnel at a Mach number of 2.0. Nozzle pressure ratios from 1 to 64 were tested with both helium and air used as jet gases. The tests were conducted at angles of attack from -2 deg to 8 deg at a Reynolds number of 9,840,000 per meter. Only the forces and moments on the wing were measured. Results of the investigation indicated that the jet blowing over the wing caused reductions in maximum lift-drag ratio of about 4 percent for helium and 6 percent for air at their respective design nozzle pressure ratios, relative to jet-off data. Moderate changes in the longitudinal, vertical, or angular positions of the jet relative to the wing had little effect on the wing aerodynamic characteristics.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1050 , L-11751
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  • 160
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    Finite element analysis of low speed viscous and inviscid aerodynamic flows (1977)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: A weak interaction solution algorithm was established for aerodynamic flow about an isolated airfoil. Finite element numerical methodology was applied to solution of each of differential equations governing potential flow, and viscous and turbulent boundary layer and wake flow downstream of the sharp trailing edge. The algorithm accounts for computed viscous displacement effects on the potential flow. Closure for turbulence was accomplished using both first and second order models. The COMOC finite element fluid mechanics computer program was modified to solve the identified equation systems for two dimensional flows. A numerical program was completed to determine factors affecting solution accuracy, convergence and stability for the combined potential, boundary layer, and parabolic Navier-Stokes equation systems. Good accuracy and convergence are demonstrated. Each solution is obtained within the identical finite element framework of COMOC.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2908 , COMOC-77TR-2
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    Effects of canard location on the aerodynamic characteristics of a sharp-nosed missile at Mach numbers of 1.5 and 2.0 (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A sharp-nosed missile model with nose-mounted canards and cruciform tail surfaces was tested in the Ames 6- by 6-foot wind tunnel to determine the contributions of the component aerodynamic surfaces on the static aerodynamic characteristics at Mach numbers of 1.5 and 2.0 and a Reynolds number of 1,000,000 based on body diameter. Effect of canard location (at three different axial positions) was investigaed. Data were obtained at angles of attack ranging from 3 deg to 12 deg, roll angles of 0 deg and 45 deg, and canard-deflection angles from 3 deg to 15 deg for various stages of model build-up (i.e., with and without canard and/or tail surfaces). The canard in the most aft position was least effective in trimming the model. With movement of the canard to the most forward position, the model was trimmable at angles of attack up to about 5 deg or 6 deg with panel deflections of 9 deg.
    Keywords: AERODYNAMICS
    Type: NASA-TM-73221 , A-6959
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  • 162
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    Wind tunnel investigation of rotor lift and propulsive force at high speed: Test data appendix (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N78-10020.
    Keywords: AERODYNAMICS
    Type: NASA-CR-145217-APP-3 , D210-11135-3-APP
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  • 163
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    Tetroon evaluation program (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The actual volume of a constant volume superpressured tetrahedron shaped balloon changes as the amount of superpressure is changed. The experimental methods used to measure these changes in volume are described and results are presented. The basic equations used to determine the amount of inflation gas required for a tetroon to float at a predetermined flight level are presented and inflation techniques discussed.
    Keywords: AERODYNAMICS
    Type: NASA-CR-150437
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  • 164
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    Effects of lengthwise lift distribution on sonic boom of SST configurations (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Sonic Boom signatures produced by possible SST configurations during cruise were investigated. It is shown that optimization based on a far field analysis is not necessarily the optimum for these conditions. For an airplane length of 300 ft, near-field effects can be obtained when sufficient lift is generated near the nose of the airplane. Because of the near-field effects, sonic booms with maximum overpressures of the order of 1 lb/square foot can be obtained with possible airplane configurations having the same flight conditions at cruise.
    Keywords: AERODYNAMICS
    Type: Selected Papers on Advanced Design of Air Vehicles; p 51-54
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  • 165
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    General purpose computer program for interacting supersonic configurations. User's manual (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The input data required to execute the computer program ISCON are described. The program generates a numerical procedure for the determination of unsteady aerodynamic forces on arbitrarily interacting wings and tails in supersonic flow. A velocity potential gradient method is used. Constant Mach number is assumed throughout the flow field. Lifting surfaces are represented by trapezoidal elements which can be generated automatically by the program. The wake field is represented by rectangular strip elements. The formulation is reviewed as well as input overview and input format. Instruction on how to use ISCON, a sample problem, and the restart feature are discussed. Program size limitations, computer program flow, and error messages are also included along with a description of the SS31 program used to compute the coefficients of surface spline.
    Keywords: AERODYNAMICS
    Type: NASA-CR-145128
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  • 166
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    Digital processing of the Mariner 10 images of Venus and Mercury (1977)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: An extensive effort was devoted to the digital processing of the Mariner 10 images of Venus and Mercury at the Image Processing Laboratory of the Jet Propulsion Laboratory. This effort was designed to optimize the display of the considerable quantity of information contained in the images. Several image restoration, enhancement, and transformation procedures were applied; examples of these techniques are included. A particular task was the construction of large mosaics which characterize the surface of Mercury and the atmospheric structure of Venus.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Journal of Applied Photographic Engineering; 3; Spring 1
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  • 167
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    Application of track detectors to the measurement of sputtering yields (1977)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Nuclear Instruments and Methods; 144; 1977
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  • 168
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    DKDP /potassium dideuterium phosphate/ light valves (1977)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The use of potassium dideuterium phosphate (DKDP) light valves for optical data processing is discussed. The operating principles and structure of optically and electron beam addressed DKDPs are compared, and specifications for both devices given. Optically addressed DKDPs are capable of higher resolution and contrast, but both systems represent viable real time spatial light modulators adaptable to optical processing. Examples of real time data processing performed by the DKDPs include: image addition and subtraction; reduction of noise introduced by scattered light in recording media; reconstruction of computer generated and acoustic holograms; reconstruction of synthetic aperture radar data; retrieval of three-dimensional information in X-ray diagnoses; radar signal processing and display; and optical pattern recognition and correlation of images, which has applications for missile guidance systems.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Optical Engineering; 16; May-June
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  • 169
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    Geometry and properties of the plasma in a quadrupole ion pump (1977)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The diameter of the plasma in a quadrupole ionization gauge and quadrupole ion pump has been measured as a function of pressure. The radio-frequency quadrupole systems are tuned in such a way that electrons remain on stable trajectories in the center of the tube. Being emitted at one end, the electrons encounter an inverted field at the other end so that they travel on spiral paths back and forth until they collide with the rest gas molecules, producing ions which are collected as an ion current at a cylinder surrounding the four hyperbolically shaped quadrupole electrodes.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Journal of Vacuum Science and Technology; 14; Mar
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  • 170
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    Numerical solutions for viscous and potential flow about arbitrary two-dimensional bodies using body-fitted coordinate systems (1977)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: A procedure for numerical solution of the time-dependent, incompressible Navier-Stokes equations for the flow about arbitrarily shaped two-dimensional bodies is given. This solution is based on a technique of automatic numerical generation of a curvilinear coordinate system having a coordinate line coincident with the body contour regardless of its shape. The implicit solution utilizes the vorticity-stream function formulation with a false-position iterative adjustment of the surface vorticity in satisfaction of the no-slip boundary condition. Excellent agreement with the Blasius boundary layer solution is obtained for a semi-infinite flat plate. Results are presented for Reynolds numbers up to 2000 for several airfoils and a cambered rock.
    Keywords: AERODYNAMICS
    Type: Journal of Computational Physics; 24; July 197
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  • 171
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    Absolute radiometric measurements of the emission from a BRV source at 34 nm (1977)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The paper reports measurements of the time integrated spectral intensity near 34 nm of a BRV (Balloffet-Romand-Vodar) source of emission continuum. The transmittance profile of the combined filters is presented and the percent efficiency (electrons per photon) of the calibration system is given as a function of wavelength. It is noted that the BRV source provides an excellent emission continuum for XUV spectroscopy.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 16; July 197
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  • 172
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    Variable threshold zonal filtering (1977)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Variable threshold zonal filtering is an active nonlinear image enhancement technique designed to avoid ringing artifacts which filtering can introduce near sharp brightness transitions in the original scene. The filtering procedure can be implemented in the Fourier domain or by subtractive box filtering. It is shown, in reference to a Landsat scene of Iceland, that while conventional box filtering produces severe ringing, zonal filtering results in a more uniform display of local detail.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 16; July 197
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  • 173
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    A practical method for holographic interference fringe assessment (1977)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: A theory concerning the problem of fringe interpretation reported by Hecht et al. (1973) is extended and a simpler semiquantitative method for the assessment of the fringes is developed. According to the new method, the fringe contrast between any two points on an object, is determined on the basis of the difference of the path-length changes at each point. The theoretical development of the method is discussed and a description of experimental results is given.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Optical Engineering; 16; Mar
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  • 174
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    Compressible laminar boundary layers with suction on swept and tapered wings (1977)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: In this paper we present a numerical method for solving the compressible laminar boundary-layer equations with suction on swept and tapered wings. The method employs an efficient two-point finite-difference method to solve the governing equations, and a very convenient similarity transformation which removes the wall normal velocity as a boundary condition and places it into the governing equations as a parameter. In this way the awkward nonlinear boundary condition which couples all the variables is avoided. To test and demonstrate the method, we present a sample calculation for a typical laminar-flow-control (LFC) wing.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 14; July 197
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  • 175
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    Load distributions on slender delta wings having vortex flow (1977)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Results obtained through application of potential-flow theory based on a suction flow analogy for incompressible flow are compared to attached-flow theory and to experimental data acquired for sharp-edged delta wings. The error incurred in predicting structural loads on the basis of attached-flow theory is investigated. Force and moment coefficients and load distributions are used in the comparisons. The root bending moment can be estimated by assuming vortex lift concentrated at the wing leading edge. While this may entail some error at large angles of attack (owing to inboard movement of the center of vortex lift), it may furnish an upper bound in evaluating results based on other theories.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 14; July 197
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  • 176
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    Gray-level transformations for interactive image enhancement (1977)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: A gray-level transformation method suitable for interactive image enhancement is presented. It is shown that the well-known histogram equalization technique is a special case of this method. Experimental results which illustrate the enhancement capabilities of the procedure are also described.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
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  • 177
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    Effect of turbulence on line-reversal temperature measurements (1977)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The effect of turbulent temperature fluctuations on line-reversal temperature measurements is examined in the thin gas, small fluctuation limit. It is shown that in this limit the fluctuations have no effect on the time average results. Only in case of a spacially uniform temperature can the fluctuating component of the temperature be directly measured. For the case of a spacially uniform mean temperature, a spacial average of the fluctuating component can be measured. For the completely nonuniform case, only a complex spacial average of the fluctuating and mean temperatures can be measured.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Journal of Quantitative Spectroscopy and Radiative Transfer; 17; Mar. 197
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  • 178
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    Laser anemometer signals - Visibility characteristics and application to particle sizing (1977)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Investigations have been conducted concerning the characteristics of the visibility function as determined by the parameters of the laser anemometer system and the electromagnetic scattering properties of the particles. Experiments have been performed to evaluate the backscatter visibility of signals from a symmetric, s polarization laser anemometer as a function of the particle diameter and a parameter ratio. The results have been compared with the predictions of an analysis based on Mie's scattering theory. The analysis has also been used to evaluate the effects of the collecting aperture's size and location.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 16; Mar. 197
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  • 179
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    A photon-counting multichannel spectrometer (1977)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: A multichannel detector system is described in which the positions of individual photon events in a high-gain image intensifier are decoded in the output of a video detector. The high-gain intensifier consists of a pair of three-stage electrostatic image-tube assemblies each containing three fiber-optically-coupled tubes potted in a rugged package with an internal high-voltage supply. Operation of the electrooptical system is discussed along with the pulse-detection process and the operation of the spectrograph in which the image-tube assembly is mounted. It is noted that the spectrometer detects 1.0 count/sec per A for an object of magnitude 13.0 at the peak of its response in the visual band when no light is lost on the slit, that a 10% coincidence correction is reached at an overall count rate of 860 per sec, and that the response follows an exponential law up to count rates of about 4000 per sec. The measured spectrum of the Seyfert galaxy NGC 5548 is provided as an example of the raw data produced by the instrument on a 1.5 meter telescope.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Astronomical Society of the Pacific; vol. 88
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  • 180
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    Cold air performance of a 12.766-centimeter-tip-diameter axial-flow cooled turbine. 2: Effect of air ejection on turbine performance (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An air cooled version of a single-stage, axial-flow turbine was investigated to determine aerodynamic performance with and without air ejection from the stator and rotor blades surfaces to simulate the effect of cooling air discharge. Air ejection rate was varied from 0 to 10 percent of turbine mass flow for both the stator and the rotor. A primary-to-air ejection temperature ratio of about 1 was maintained.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1018
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  • 181
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    Study of design and analysis methods for transonic flow (1977)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: An airfoil design program and a boundary layer analysis were developed. Boundary conditions were derived for ventilated transonic wind tunnels and performing transonic windtunnel wall calculations. A computational procedure for rotational transonic flow in engine inlet throats was formulated. Results and conclusions are summarized.
    Keywords: AERODYNAMICS
    Type: NASA-CR-152041 , NOTE-118
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  • 182
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    Effects of canard location on the aerodynamic characteristics of a blunt-nosed missile at Mach numbers of 1.5 and 2.0 (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A blunt-nosed missile model with nose-mounted canards and cruciform tail surfaces was tested in the Ames 6 by 6-Foot Wind Tunnel to determine the contributions of the component aerodynamic surfaces to the static aerodynamic characteristics at Mach numbers of 1.5 and 2.0 and Reynolds number of 1 million based on body diameter. Data were obtained at angles of attack ranging from -3 deg to 12 deg and canard-deflection angles from -3 deg to 15 deg for various stages of model build-up (i.e., with and without canard and/or tail surfaces). Results were obtained with the canards at two different nose locations. For the canard and tail arrangements investigated, the model was trimmable at angles of attack up to about 4 deg or 5 deg with canard deflections of 9 deg. For this blunt-nosed model, there was little effect of canard location on trim angle of attack. The tail arrangements studied provided ample pitch stability.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-73220 , A-6958
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  • 183
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    Rolling moments in a trailing vortex flow field (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Pressure distributions are presented which were measured on a wing in close proximity to a tip vortex of known structure generated by a larger, upstream semispan wing. Overall loads calculated by integration of these pressures are checked by independent measurements made with an identical model mounted on a force balance. Several conventional methods of wing analysis are used to predict the loads on the following wing. Strip theory is shown to give uniformly poor results for loading distribution, although predictions of overall lift and rolling moment are sometimes acceptable. Good results are obtained for overall coefficients and loading distribution by using linearized pressures in vortex-lattice theory in conjunction with a rectilinear vortex. The equivalent relation from reverse-flow theory that can be used to give economic predictions for overall loads is presented.
    Keywords: AERODYNAMICS
    Type: NASA-CR-151961 , NEAR-TR-129
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  • 184
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    Two-dimensional aerodynamic characteristics of several rotorcraft airfoils at Mach numbers from 0.35 to 0.90 (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was conducted in the Langley 6- by 28-inch transonic tunnel and the 6- by 19-inch transonic tunnel to determine the two-dimensional aerodynamic characteristics of several rotorcraft airfoils at Mach numbers from 0.35 to 0.90. The airfoils differed in thickness, thickness distribution, and camber. The FX69-H-098, the BHC-540, and the NACA 0012 airfoils were investigated in the 6- by 28-inch tunnel at Reynolds numbers (based on chord) from about 4.7 to 9.3 million at the lowest and highest test Mach numbers respectively. The FX69-H-098, the NLR-1, the BHC-540, and the NACA 23012 airfoils were investigated in the 6- by 19-inch tunnel at Reynolds numbers from about 0.9 to 2.2 million at the lowest and highest test Mach numbers respectively.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-73990
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  • 185
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    Variable thickness shear layer aerodynamics revisited (1977)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The constant boundary-layer thickness (BLT) figuring in the Ventres (1975) Kernel function can be replaced by a slowly varying BLT, in the case of shear layers of slowly varying thickness. A simplification of the extension by Chi (1976) of Ventres' solution is put forward. The Kernel function in this instance relates pressure on the lifting surface to downwash over the surface. The results should also apply, formally, to three-dimensional compressible unsteady flows, but the accuracy in assuming slowly varying shear BLT remains to be determined. All variants of the shear layer model fail when the shear layer thickness varies rapidly.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 15; May 1977
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  • 186
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    Optical zero-differential pressure switch and its evaluation in a multiple pressure measuring system (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The design of a clamped-diaphragm pressure switch is described in which diaphragm motion is detected by a simple fiber-optic displacement sensor. The switch was evaluated in a pressure measurement system where it detected the zero crossing of the differential pressure between a static test pressure and a tank pressure that was periodically ramped from near zero to fullscale gage pressure. With a ramping frequency of 1 hertz and a full-scale tank pressure of 69 N/sq cm gage (100 psig), the switch delay was as long as 2 milliseconds. Pressure measurement accuracies were 0.25 to 0.75 percent of full scale. Factors affecting switch performance are also discussed.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-TM-X-3571 , E-9139
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  • 187
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    Low speed aerodynamic characteristics of a vectored thrust V/STOL transport with two lift/cruise fans (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A wind tunnel test was conducted to obtain power on low speed characteristics of a twin fan vectored thrust V/STOL transport aircraft. Longitudinal, as well as some lateral directional data, were analyzed. Hover, STOL, and conventional flight modes were investigated. Determination of STOL characteristics, hover characteristics, roll control effectiveness and aircraft attitude were evaluated. The study also included various means to improve the lifting capability of the aircraft such as by application of fuselage strakes, exhaust vanes capable of shifting the thrust vector aft, and external flap blowing for STOL performance.
    Keywords: AERODYNAMICS
    Type: NASA-CR-152029
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  • 188
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    Load distribution on a closed-coupled wing canard at transonic speeds (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A wind tunnel test where load distributions were obtained at transonic speeds on both the canard and wing surfaces of a closely coupled wing canard configuration is reported. Detailed component and configuration arrangement studies to provide insight into the various aerodynamic interference effects for the leading edge vortex flow conditions encountered are included. Data indicate that increasing the Mach number from 0.70 to 0.95 caused the wing leading edge vortex to burst over the wing when the wing was in the presence of the high canard.
    Keywords: AERODYNAMICS
    Type: NASA-TM-74053
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  • 189
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    Low-speed wind tunnel investigation of an advanced supersonic cruise arrow-wing configuration (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A preliminary assessment of possible means for improving the low speed aerodynamic characteristics of advanced supersonic cruise arrow wing configurations and to extend the existing data base of such configurations has been made. Principle configuration variables included wing-leading and trailing-edge flap deflection, fuselage nose strakes, and engine exhaust nozzle deflection. Results showed that deflecting the wing leading edge apex flaps downward provided improved longitudinal stability but resulted in reduced directional stability. The model exhibited relatively low values of directional stability over the operational angle of attack range and experienced large asymmetric yawing moments at high angles of attack. The use of nose strakes was found to be effective in increasing the directional stability and eliminating the asymmetric yawing moment.
    Keywords: AERODYNAMICS
    Type: NASA-TM-74043
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  • 190
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    Holographic flow visualization at the Langley CF4 tunnel (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A holographic flow visualization system was used to obtain shadowgraph, schlieren, and interferograms of the flow field at Langley's hypersonic (Mach 6) CF4 tunnel. The dual hologram technique which was used makes it possible to vary focusing, knife-edge position, and the orientation and spacing of the interference fringes after a tunnel run. The experimental arrangement necessary to produce high quality interferograms is discussed. Typical shadowgraphs, schlieren pictures, and interferograms are presented.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-TM-74051
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  • 191
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    Altimeter error sources at the 10-cm performance level (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Error sources affecting the calibration and operational use of a 10 cm altimeter are examined to determine the magnitudes of current errors and the investigations necessary to reduce them to acceptable bounds. Errors considered include those affecting operational data pre-processing, and those affecting altitude bias determination, with error budgets developed for both. The most significant error sources affecting pre-processing are bias calibration, propagation corrections for the ionosphere, and measurement noise. No ionospheric models are currently validated at the required 10-25% accuracy level. The optimum smoothing to reduce the effects of measurement noise is investigated and found to be on the order of one second, based on the TASC model of geoid undulations. The 10 cm calibrations are found to be feasible only through the use of altimeter passes that are very high elevation for a tracking station which tracks very close to the time of altimeter track, such as a high elevation pass across the island of Bermuda. By far the largest error source, based on the current state-of-the-art, is the location of the island tracking station relative to mean sea level in the surrounding ocean areas.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-CR-141420
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  • 192
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    Opto-mechanical subsystem with temperature compensation through isothemal design (1977)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: An opto-mechanical subsystem for supporting a laser structure which minimizes changes in the alignment of the laser optics in response to temperature variations is described. Both optical and mechanical structural components of the system are formed of the same material, preferably beryllium, which is selected for high mechanical strength and good thermal conducting qualities. All mechanical and optical components are mounted and assembled to provide thorough thermal coupling throughout the subsystem to prevent the development of temperature gradients.
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  • 193
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    Tail contribution to the directional aerodynamic characteristics of a 1/6-scale model of the rotor systems research aircraft with a tail rotor (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results are presented of a wind tunnel investigation to determine the tail contribution to the directional aerodynamic characteristics of a 1/6-scale model of the rotor systems research aircraft (RSRA) with a tail rotor. No main rotor was used during the investigation. Data were obtained with and without the tail rotor over a range of sideslip angle and over a range of rotor collective pitch angle. The model with the tail rotor was tested at several advance ratios with and without thrust from the auxiliary thrust engines on the RSRA fuselage. Increasing the space between the tail-rotor hub and the vertical tail reduced the tail-rotor torque required at moderate to high rotor thrust. Increasing the exit dynamic pressure of the auxiliary thrust engines decreases the tail contribution to the static directional stability. The tail-rotor thrust and its interference provide a positive increment to the static directional stability. The tail contribution increases with forward speed. The adverse yawing moment of the airframe would strongly affect the thrust required of the tail rotor when the helicopter is hovering in a crosswind.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3501 , L-11271
    Format: application/pdf
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  • 194
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    Boundary layer separation on isolated boattail nozzles (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The phenomenon of separated flow on a series of circular-arc afterbodies was investigated using the Langley 16-foot transonic tunnel at free-stream Mach numbers from 0.40 to 0.95 at 0 deg angle of attack. Both high-pressure air and solid circular cylinders with a diameter equal to the nozzle exit diameter were used to simulate jet exhausts. A detailed data base of boundary layer separation locations was obtained using oil-flow techniques. The results indicate that boundary layer separation is most extensive on steep boattails at high Mach numbers.
    Keywords: AERODYNAMICS
    Type: NASA-CR-152703
    Format: application/pdf
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  • 195
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    Wind-tunnel results of the aerodynamic characteristics of a 1/8-scale model of a twin engine short-haul transport (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A wind tunnel test was conducted in the Langley V/STOL tunnel to define the aerodynamic characteristics of a 1/8-scale twin-engine short haul transport. The model was tested in both the cruise and approach configurations with various control surfaces deflected. Data were obtained out of ground effect for the cruise configuration and both in and out of ground effect for the approach configuration. These data are intended to be a reference point to begin the analysis of the flight characteristics of the NASA terminal configured vehicle (TCV) and are presented without analysis.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-74011
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  • 196
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    Acoustic and aerodynamic performance of a 1.5-pressure-ratio, 1.83-meter (6 ft) diameter fan stage for turbofan engines (QF-2) (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The fan was externally driven by an electric motor. Design features for low-noise generation included the elimination of inlet guide vanes, long axial spacing between the rotor and stator blade rows, and the selection of blade-vane numbers to achieve duct-mode cutoff. The fan QF-2 results were compared with those of another full-scale fan having essentially identical aerodynamic design except for nozzle geometry and the direction of rotation. The fan QF-2 aerodynamic results were also compared with those obtained from a 50.8 cm rotor-tip-diameter model of the reverse rotation fan QF-2 design. Differences in nozzle geometry other than exit area significantly affected the comparison of the results of the full-scale fans.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3521 , E-8968
    Format: application/pdf
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  • 197
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    Analysis of internal flow of J85-13 multistage compressor (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Interstage data recorded on a J85-13 engine were used to analyze the internal flow of the compressor. Measured pressures and temperatures were used as input to a streamline analysis program to calculate the velocity diagrams at the inlet and outlet of each blade row. From the velocity diagrams and blade geometry, selected blade-element performance parameters were calculated. From the detailed analysis it is concluded that the compressor is probably hub critical (stall initiates at the hub) in the latter stages for the design speed conditions. As a result, the casing treatment over the blade tips has little or no effect on stall margin at design speed. Radial inlet distortion did not appear to change the flow in the stages that control stall because of the rapid attenuation of the distortion within the compressor.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3513 , E-8493
    Format: application/pdf
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  • 198
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    Analysis of the development of dynamic stall based on oscillating airfoil experiments (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effects of dynamic stall on airfoils oscillating in pitch were investigated by experimentally determining the viscous and inviscid characteristics of the airflow on the NACA 0012 airfoil and on several leading-edge modifications. The test parameters included a wide range of frequencies, Reynolds numbers, and amplitudes-of-oscillation. Three distinct types of separation development were observed within the boundary layer, each leading to classical dynamic stall. The NACA 0012 airfoil is shown to stall by the mechanism of abrupt turbulent leading-edge separation. A detailed step-by-step analysis of the events leading to dynamic stall, and of the results of the stall process, is presented for each of these three types of stall. Techniques for flow analysis in the dynamic stall environment are discussed. A method is presented that reduces most of the oscillating airfoil normal force and pitching-moment data to a single curve, independent of frequency or Reynolds number.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-8382 , A-6674
    Format: application/pdf
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  • 199
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    Theoretical Parametric Study of the Relative Advantages of Winglets and Wing-Tip Extensions (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For identical increases in bending moment, a winglet provides a greater gain in induced efficiency than tip extension. Winglet toe angle allows design trades between efficiency and root moment. A winglet shows the greatest benefit when the wing loads are heavy near the tip. Washout diminishes the benefit of either tip modification, and the gain in induced efficiency becomes a function of lift coefficient; thus, heavy wing loadings obtain the greatest benefit from a winglet, and low-speed performance is enhanced even more than cruise performance. Both induced efficiency and bending moment increase with winglet length and outward cant. The benefit of a winglet relative to a tip extension is greatest for a nearly vertical winglet. Root bending moment is proportional to the minimum weight of bending material required in the wing; thus, it is a valid index of the impact of tip modifications on a new wing design.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-74003
    Format: application/pdf
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  • 200
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    Lecture notes in economics and mathematical system. Volume 150: Supercritical wing sections 3 (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Application of computational fluid dynamics to the design and analysis of supercritical wing sections is discussed. Computer programs used to study the flight of modern aircraft at high subsonic speeds are listed and described. The cascades of shockless transonic airfoils that are expected to increase the efficiency of compressors and turbines are included.
    Keywords: AERODYNAMICS
    Type: NASA-CR-155581
    Format: application/pdf
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