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  • AERODYNAMICS
  • 1970-1974  (257)
  • 1973  (257)
  • 1
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    Preliminary lift and drag characteristics of the F-8 supercritical wing airplane (1973)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: its Supercritical Wing Technol.: A Report on Flight Evaluation; p 59-70
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  • 2
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    Externally blown flap dynamic loads (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Some of the principal results obtained in three series of measurements of fluctuating surface pressures induced on externally blown flaps by jet impingment are presented. Large- and small-scale models and hot- and cold-flow tests are considered. The discussion sets forth scaling parameters and consistent features of the root-mean-square values and spectra of the loading. Implications of these results with regard to sonic fatigue are indicated.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 131-142
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  • 3
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    Review of drag measurements from flight tests of manned aircraft with comparisons to wind-tunnel predictions (1973)
    In:  CASI
    Details
    Publication Date: 2011-10-14
    Description: In-flight studies of the overall and local components of drag of many types of aircraft were conducted. The primary goal of these studies was to evaluate wind-tunnel and semiempirical prediction methods. Some evaluations are presented in this paper which may be summarized by the following observations: Wind-tunnel predictions of overall vehicle drag can be accurately extrapolated to flight Reynolds numbers, provided that the base drag is removed and the boattail areas on the vehicle are small. The addition of ablated roughness to lifting body configurations causes larger losses in performance and stability than would be expected from the added friction drag due to the roughness. Successful measurements of skin friction have been made in flight to Mach numbers above 4. A reliable inflatable deceleration device was demonstrated in flight which effectively stabilizes and decelerates a lifting aircraft at supersonic speeds.
    Keywords: AERODYNAMICS
    Type: AGARD Aerodyn. Drag; 12 p
    Format: text
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  • 4
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    A summary of current research in rotor unsteady aerodynamics with emphasis on work at Langley Research Center (1973)
    In:  CASI
    Details
    Publication Date: 2011-10-14
    Description: The basic unsteady aerodynamic environment of the rotary wing is summarized. Some of the observed trends in the state of the art are discussed. Some of the research needs that will require attention are reported. A review of a number of research investigations as a part of a joint NASA/Army rotorcraft project is presented. The research is directed toward achieving a better understanding of rotor unsteady airfoils. The investigations include: (1) rotor maneuver loads; (2) level flight and maneuver wake prediction; (3) tip-vortex flow; (4) blade-vortex interactions; (5) dynamic stall; (6) transient Mach number air loads; and (7) development of variable geometry rotors.
    Keywords: AERODYNAMICS
    Type: AGARD Aerodyn. of Rotary Wings; 20 p
    Format: text
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  • 5
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    Integral equation for small perturbations of irrotational flows (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: An investigation is conducted concerning the validity of analytical methods which are based on deriving an integral equation, taking into account small perturbations in the case of a nonuniform but irrotational flow. The results obtained apply to a wide Mach number range, but are restricted to small amplitude motions and to nonviscous flows. It is shown that the integral equation relating the unknown velocity potential to the known normal flow velocity can be derived from the appropriate Green's identity.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 11; Dec. 197
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  • 6
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    On the inviscid rolled-up structure of lift-generated vortices (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A simple form is presented of the relationships derived by Betz for the inviscid, fully developed structure of lift-generated vortices behind aircraft. An extension is then made to arbitrary span-load distributions by inferring guidelines for the selection of rollup centers for the vortex sheet. These techniques are easier to use and yield more realistic estimates of the rolled-up structure of vortices than the original form of Betz' theory when the span loading differs appreciably from elliptic loading.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 10; Nov. 197
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  • 7
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    Van Driest generalization applied to turbulent skin friction and velocity profiles measured on the wall of a Mach 7.4 wind tunnel (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 11; Dec. 197
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  • 8
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    Effect of anisotropic turbulence on aerodynamic noise (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A model based on Lighthill's theory for predicting aerodynamic noise from a turbulent shear flow is developed. This model is a generalization of the one developed by Ribner. It does not require that the turbulent correlations factor into space and time-dependent parts. It replaces his assumption of isotropic turbulence by the more realistic one of axisymmetric turbulence. In the course of the analysis, a hierarchy of equations is developed wherein each succeeding equation involves more assumptions than the preceding equation but requires less experimental information for its use. The implications of the model for jet noise are discussed. It is shown that for the particular turbulence data considered anisotropy causes the high-frequency self-noise to be beamed downstream.
    Keywords: AERODYNAMICS
    Type: Acoustical Society of America; vol. 54
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  • 9
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    Three-dimensional separation for interaction of shock waves with turbulent boundary layers (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: For the interaction of shock waves with turbulent boundary layers, obtained experimental three-dimensional separation results and correlations with earlier two-dimensional and three-dimensional data are presented. It is shown that separation occurs much earlier for turbulent three-dimensional than for two-dimensional flow at hypersonic speeds.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 11; Nov. 197
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  • 10
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    A graphical method for the investigation of shock interference phenomena (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 11; Nov. 197
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  • 11
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    Shooting method for solution of boundary-layer flows with massive blowing (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A modified, bidirectional shooting method is presented for solving boundary-layer equations under conditions of massive blowing. Unlike the conventional shooting method, which is unstable when the blowing rate increases, the proposed method avoids the unstable direction and is capable of solving complex boundary-layer problems involving mass and energy balance on the surface.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 11; Nov. 197
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  • 12
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    Derivation of aerodynamic kernel functions (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The method of Fourier transforms is used to determine the kernel function which relates the pressure on a lifting surface to the prescribed downwash within the framework of Dowell's (1971) shear flow model. This model is intended to improve upon the potential flow aerodynamic model by allowing for the aerodynamic boundary layer effects neglected in the potential flow model. For simplicity, incompressible, steady flow is considered. The proposed method is illustrated by deriving known results from potential flow theory.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 11; Nov. 197
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  • 13
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    Correlation of hypersonic zero-lift drag data. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A pseudo-one-dimensional model of the supersonic combustion ramjet engine cycle is revised on the basis of recent (additional) data obtained from combustor tests. The data were generated in a simple nonreacting system which produces shock structures and shock/boundary layer interactions analogous to those observed at the entrance of supersonic combustors. It is shown that the revised model provides better descriptions of the wall pressure distributions and the overall shock pressure rises for the available test data.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 10; Sept
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  • 14
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    Transonic flow about lifting configurations. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A transonic flow solution is presented for configurations with span-to-length ratios of order one. The angles of attack are sufficiently large to produce lift effects that are either dominant or comparable to the thickness effects. The analysis is performed with the aid of the method of matched asymptotic expansions. The results obtained are compared with data reported by Cheng and Hafez (1972).
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 11; May 1973
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  • 15
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    High Reynolds number experimental data for forebody axial force. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Brief review of the operational principle and capability of the high-Reynolds-number wind tunnel developed over the last few years. Its test medium is stored in a Ludwieg tube and held there by means of a diaphragm. When the diaphragm is broken, a rearward-facing centered rarefaction fan propagates upstream through the test section and nozzle into the supply tube, and the useful run time is bounded by the reflected rarefaction wave and the starting shock wave caused by choking at the nozzle. The operating problems center around the ability of model and sting support systems to withstand the loads and to meet the instrumentation requirements. Evaluation tests have shown that satisfactory force and moment measurements can be obtained in this facility.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 11; Mar. 197
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  • 16
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    Reference temperature method for predicting turbulent compressible skin-friction coefficient. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 11; Feb. 197
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  • 17
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    Performance characteristics of a model VTOL lift fan in crossflow. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: This paper presents a summary of principal results obtained from crossflow tests of a model 15-in.-diam lift fan installed in a wing in the NASA Lewis Research Center, 9 by 15 ft V/STOL Propulsion Wind Tunnel. Tests were run with and without exit louvers over a range of tunnel air speeds, fan speeds, and wing angle of attack. Fan thrust in crossflow was influenced by two principal factors: the effects of inflow distortion on blade-row performance, and changes in fan stage operating point brought about by changes in back pressure ratio. In this particular fan, flow separation on the inlet bellmouth did not appear to be a serious problem for crossflow operation.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 10; Mar. 197
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  • 18
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    Remarks on vortex-lattice methods. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Results are presented of some numerical experiments on simple planar configurations. The experiments serve to establish more precisely some ground rules for optimum lattice arrangements. In particular, the location of both the horseshoe vortex elements and the control points at which the surface boundary conditions are to be satisfied is uniquely determined. Questions of lattice arrangement are discussed together with numerical results and problems of control point location.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 10; May 1973
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  • 19
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    Corner pressures and fillet shock locations for symmetrical corners by an approximate method. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Description of an approximate method for predicting the pressure in the immediate corner region and the shock structure on stream-aligned, sharp-leading-edge, symmetrical corner configurations. The method is basically the two-shock method developed by Charwat and Redekopp (1966), with the additional assumption that the corner fillet shock can be located from the calculated pressure in the corner. Corner pressures are correlated over a wide range of Mach numbers in air and helium for different corner wedge angles. The shock structure calculated by this method is compared with supersonic and hypersonic data.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 10; Jan. 197
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  • 20
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    Conformal mapping for potential flow about airfoils with attached flap. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The conformal mapping sequence presented transforms the potential flow about a circle into that about an airfoil with an attached flap or spoiler. It is found that adequate versatility of the flap shape for a given airfoil can usually be obtained with the indicated functions, although other transformations would expand the variety of possible flap shapes.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 10; Jan. 197
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  • 21
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    Experimental studies of turbulent aircraft wake (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Review of wind tunnel test data obtained for tip vortex studies on a square-tipped rectangular wing. The results include wing surface pressure distributions, three-dimensional velocity components in the wake, and principal vortex characteristics such as peak tangential velocity and core size distributions. The wind tunnel measurements are compared with flight test data. These comparisons show that the magnitudes of circumferential velocities, normalized by flight speed and lift coefficient, as well as the vortex core radius, normalized by wing span, are in close agreement. The data obtained make possible the calculation of turbulence stress distributions and the formulation of models for the prediction of downstream flow fields.
    Keywords: AERODYNAMICS
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  • 22
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    Approximation for maximum centerline heating on lifting entry vehicles. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A centerline heating approximation is proposed in which only three basic equations need be solved. The heat rates correlate well with those obtained by more complex procedures. The approximation is readily adaptable to existing trajectory optimization programs to provide realistic surface temperature constraint capability with little increase in computer storage capacity and computer time. It is based on an analysis of heat-rate data computed for altitudes from 36,000 to 122,000 m, velocities from 600 to 7900 m/sec, and angles of attack from 0 to 60 degrees.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 10; Sept
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  • 23
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    Advanced supersonic inlet technology. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Recently, relatively new analytical procedures have been successfully used to design bleed systems for mixed-compression inlets designed to operate efficiently up to Mach number 2.65. The procedures used constitute a major advance in inlet technology by offering a promising approach to attain high internal and external performance for mixed-compression inlets that operate over a large supersonic Mach number range. Unfortunately, there is a lack of data describing bleed hole performance characteristics to verify these procedures at high Mach numbers. This paper briefly discusses the analytical procedures for designing advanced inlet systems and suggests facility modifications wherein the procedures can be verified on large-scale inlet models up to approximately Mach number 4.5.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 10; May 1973
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  • 24
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    Estimation of aerodynamics for slender bodies alone and with lifting surfaces at alpha's from 0 deg to 90 deg. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Expressions are derived, according to a method developed by the author (1972), for bodies in which the cross-sectional shape (but not necessarily the area) is constant along the longitudinal axis. For the more general case of a body alone or with lifting surfaces where the cross-sectional shape varies along the length, a similar procedure is suggested. The specific case for an elliptic cone with a triangular wing is considered, and formulas for winged elliptic cross sections are developed. For the limited test conditions shown, the agreement between computed and experimental results is very good.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 11; Mar. 197
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  • 25
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    Silica RSI entry simulation tests (1973)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: Simulated reentry heating of the all-silica surface insulation material under a variety of conditions including arc jet and radiant lamp facilities for up to 100 simulated flight cycles has demonstrated consistent thermal performance capability. Consistent predictability along with demonstrated coating integrity and dimensional stability to 1645 K validates the earlier selection of the all-silica material for the RSI application.
    Keywords: AERODYNAMICS
    Type: NASA. Ames Res. Center Symp. on Reusable Surface Insulation for Space Shuttle, Vol. 2; p 623-666
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  • 26
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    Entry environmental simulation testing of REI-Mullite TPS (1973)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: Glassy fibrous mullite coatings exhibit noncatalytic surface characteristics which limit surface temperature rise under certain convective heat flux conditions. Thermal conductivity design curves provide good agreement with test results. The inclusion of shine-in effects results in improved accuracy of transient temperature gradient predictions for the materials.
    Keywords: AERODYNAMICS
    Type: NASA. Ames Res. Center Symp. on Reusable Surface Insulation for Space Shuttle, Vol. 2; p 485-524
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  • 27
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    Aerodynamic simulation tests of RSI panels (1973)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The technique of mixing argon with air was used to simulate the temperature-time trajectory experienced by space shuttle vehicle insulation panels. Gap heating appears to be highly dependent upon gap design, it is relatively low for interlocking and tapered panel designs and significantly higher for a wider, unfilled gap design. The heating rate appears to be significantly higher at the windward facing edges of flush tiles and is aggravated at forward facing steps. This heating, however, is highly dependent on step heights relative to some characteristic thickness of the boundary layer.
    Keywords: AERODYNAMICS
    Type: Symp. on Reusable Surface Insulation for Space Shuttle, Vol. 2; p 371-423
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  • 28
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    Feasibility study of an Integrated Program for Aerospace vehicle Design (IPAD) Volume 7: IPAD benefits and impact (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The potential benefits, impact and spinoff of IPAD technology are described. The benefits are projected from a flowtime and labor cost analysis of the design process and a study of the flowtime and labor cost savings being experienced with existing integrated systems. Benefits in terms of designer productivity, company effectiveness, and IPAD as a national resource are developed. A description is given of the potential impact of information handling as an IPAD technology, upon task and organization structure and people who use IPAD. Spinoff of IPAD technology to nonaerospace industries is discussed. The results of a personal survey made of aerospace, nonaerospace, government and university sources are given.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132397 , D6-60181-7
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  • 29
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    Feasibility study of an Integrated Program for Aerospace vehicle Design (IPAD). Volume 6: IPAD system development and operation (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: The strategy of the IPAD implementation plan presented, proposes a three phase development of the IPAD system and technical modules, and the transfer of this capability from the development environment to the aerospace vehicle design environment. The system and technical module capabilities for each phase of development are described. The system and technical module programming languages are recommended as well as the initial host computer system hardware and operating system. The cost of developing the IPAD technology is estimated. A schedule displaying the flowtime required for each development task is given. A PERT chart gives the developmental relationships of each of the tasks and an estimate of the operational cost of the IPAD system is offered.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132396 , D6-60181-6
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  • 30
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    Feasibility study of an Integrated Program for Aerospace vehicle Design (IPAD). Volume 5: Catalog of IPAD technical program elements (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: The catalog is presented of technical program elements which are required to support the design activities for a subsonic and supersonic commercial transport. Information for each element consists of usage and storage information, ownership, status and an abstract describing the purpose of the element.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132395 , D6-60181-5
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  • 31
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    Feasibility study of an Integrated Program for Aerospace vehicle Design (IPAD). Volume 4: IPAD system design (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: The computing system design of IPAD is described and the requirements which form the basis for the system design are discussed. The system is presented in terms of a functional design description and technical design specifications. The functional design specifications give the detailed description of the system design using top-down structured programming methodology. Human behavioral characteristics, which specify the system design at the user interface, security considerations, and standards for system design, implementation, and maintenance are also part of the technical design specifications. Detailed specifications of the two most common computing system types in use by the major aerospace companies which could support the IPAD system design are presented. The report of a study to investigate migration of IPAD software between the two candidate 3rd generation host computing systems and from these systems to a 4th generation system is included.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132394 , D6-60181-4
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  • 32
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    Feasibility study of an Integrated Program for Aerospace vehicle Design (IPAD). Volume 3: Support of the design process (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: The user requirements for computer support of the IPAD design process are identified. The user-system interface, language, equipment, and computational requirements are considered.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132393 , D6-60181-3
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  • 33
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    Feasibility study of an Integrated Program for Aerospace vehicle Design (IPAD). Volume 2: The design process (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: The extent to which IPAD is to support the design process is identified. Case studies of representative aerospace products were developed as models to characterize the design process and to provide design requirements for the IPAD computing system.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132392 , D6-60181-2
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  • 34
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    Feasibility study of an Integrated Program for Aerospace vehicle Design (IPAD). Volume 1B: Concise review (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: Reports on the design process, support of the design process, IPAD System design catalog of IPAD technical program elements, IPAD System development and operation, and IPAD benefits and impact are concisely reviewed. The approach used to define the design is described. Major activities performed during the product development cycle are identified. The computer system requirements necessary to support the design process are given as computational requirements of the host system, technical program elements and system features. The IPAD computer system design is presented as concepts, a functional description and an organizational diagram of its major components. The cost and schedules and a three phase plan for IPAD implementation are presented. The benefits and impact of IPAD technology are discussed.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132391 , D6-60181-1B
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  • 35
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    Feasibility study of an Integrated Program for Aerospace vehicle Design (IPAD). Volume 1A: Summary (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: IPAD was defined as a total system oriented to the product design process. This total system was designed to recognize the product design process, individuals and their design process tasks, and the computer-based IPAD System to aid product design. Principal elements of the IPAD System include the host computer and its interactive system software, new executive and data management software, and an open-ended IPAD library of technical programs to match the intended product design process. The basic goal of the IPAD total system is to increase the productivity of the product design organization. Increases in individual productivity were feasible through automation and computer support of routine information handling. Such proven automation can directly decrease cost and flowtime in the product design process.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132390 , D6-60181-1A
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  • 36
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    Feasibility study of an Integrated Program for Aerospace-vehicle Design (IPAD) system. Volume 6: Implementation schedule, development costs, operational costs, benefit assessment, impact on company organization, spin-off assessment, phase 1, tasks 3 to 8 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A baseline implementation plan, including alternative implementation approaches for critical software elements and variants to the plan, was developed. The basic philosophy was aimed at: (1) a progressive release of capability for three major computing systems, (2) an end product that was a working tool, (3) giving participation to industry, government agencies, and universities, and (4) emphasizing the development of critical elements of the IPAD framework software. The results of these tasks indicate an IPAD first release capability 45 months after go-ahead, a five year total implementation schedule, and a total developmental cost of 2027 man-months and 1074 computer hours. Several areas of operational cost increases were identified mainly due to the impact of additional equipment needed and additional computer overhead. The benefits of an IPAD system were related mainly to potential savings in engineering man-hours, reduction of design-cycle calendar time, and indirect upgrading of product quality and performance.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132406
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    Feasibility study of an Integrated Program for Aerospace-vehicle Design (IPAD) system. Volume 5: Design of the IPAD system. Part 2: System design. Part 3: General purpose utilities, phase 1, task 2 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Viable designs are presented of various elements of the IPAD framework software, data base management system, and required new languages in relation to the capabilities of operating systems software. A thorough evaluation was made of the basic systems functions to be provide by each software element, its requirements defined in the conceptual design, the operating systems features affecting its design, and the engineering/design functions which it was intended to enhance.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132405
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  • 38
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    Feasibility study of an Integrated Program for Aerospace-vehicle Design (IPAD) system. Volume 4: Design of the IPAD system. Part 1: IPAD system design requirements, phase 1, task 2 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: System requirements, software elements, and hardware equipment required for an IPAD system are defined. An IPAD conceptual design was evolved, a potential user survey was conducted, and work loads for various types of interactive terminals were projected. Various features of major host computing systems were compared, and target systems were selected in order to identify the various elements of software required.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132404
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  • 39
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    Feasibility study of an Integrated Program for Aerospace-vehicle Design (IPAD) system. Volume 3: Engineering creative/evaluation processes, phase 1, task 2 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A series of functional flow charts are considered that were developed to properly identify and record the degree of participation of the disciplines considered in this feasibility study and the type of data required in the design process.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132403
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  • 40
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    Feasibility study of an Integrated Program for Aerospace-vehicle Design (IPAD) system. Volume 2: Characterization of the IPAD system, phase 1, task 1 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The aircraft design process is discussed along with the degree of participation of the various engineering disciplines considered in this feasibility study.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132402
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  • 41
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    Feasibility study of an Integrated Program for Aerospace-vehicle Design (IPAD) system. Volume 1: Summary (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An overview is provided of the Ipad System, including its goals and objectives, organization, capabilities and future usefulness. The systems implementation is also presented with operational cost summaries.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132401
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  • 42
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    Plotting program for aerodynamic lifting surface theory (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A description of and users manual for a USA FORTRAN IV computer program which plots the planform and control points of a wing are presented. The program also plots some of the configuration data such as the aspect ratio. The planform data is stored on a disc file which is created by a geometry program. This program, the geometry program, and several other programs are used together in the analysis of lifting, thin wings in steady, subsonic flow according to a kernel function lifting surface theory.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-62321
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  • 43
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    Analysis of stall flutter of a helicopter radar blade (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A study of rotor blade aeroelastic stability was carried out, using an analytic model of a two-dimensional airfoil undergoing dynamic stall and an elastomechanical representation including flapping, flapwise bending and torsional degrees of freedom. Results for a hovering rotor demonstrated that the models used are capable of reproducing both classical and stall flutter. The minimum rotor speed for the occurrence of stall flutter in hover, was found to be determined from coupling between torsion and flapping. Instabilities analogous to both classical and stall flutter were found to occur in forward flight. However, the large stall-related torsional oscillations which commonly limit aircraft forward speed appear to be the response to rapid changes in aerodynamic moment which accompany stall and unstall, rather than the result of an aeroelastic instability. The severity of stall-related instabilities and response was found to depend to some extent on linear stability. Increasing linear stability lessens the susceptibility to stall flutter and reduced the magnitude of the torsional response to stall and unstall.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2322
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  • 44
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    Hypersonic aerodynamic characteristics of a family of power-law, wing body configurations (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The configurations analyzed are half-axisymmetric, power-law bodies surmounted by thin, flat wings. The wing planform matches the body shock-wave shape. Analytic solutions of the hypersonic small disturbance equations form a basis for calculating the longitudinal aerodynamic characteristics. Boundary-layer displacement effects on the body and the wing upper surface are approximated. Skin friction is estimated by using compressible, laminar boundary-layer solutions. Good agreement was obtained with available experimental data for which the basic theoretical assumptions were satisfied. The method is used to estimate the effects of power-law, fineness ratio, and Mach number variations at full-scale conditions. The computer program is included.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7427 , L-7176
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  • 45
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    Theoretical and experimental investigation of the performance of a fan-in-wing VTOL configuration (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The incompressible-flow momentum theory is extended to the case of lifting fans. The resulting theory includes many of the known experimentally determined characteristics of fan-in-wing aircraft. These characteristics include the negligible effect of forward speed on fan thrust, the large momentum drag, and the generally inefficient performance throughout the transition speed range. Although mutual interference between the fans and the wing was totally neglected, the theory is confirmed by experimental results for the configuration tested. Examination of the results of an investigation of wall interference leads to the conclusion that the large fan-induced lift reported in many earlier investigations was largely the result of neglecting wall interference in the reduction of wind-tunnel data.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7498 , L-9219
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  • 46
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    Effect of sweep angle on the pressure distributions and effectiveness of the ogee tip in diffusing a line vortex (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Low-speed wind tunnel tests were conducted to study the influence of sweep angle on the pressure distributions of an ogee-tip configuration with relation to the effectiveness of the ogee tip in diffusing a line vortex. In addition to the pressure data, performance and flow-visualization data were obtained in the wind tunnel tests to evaluate the application of the ogee tip to aircraft configurations. The effect of sweep angle on the performance characteristics of a conventional-tip model, having equivalent planform area, was also investigated for comparison with the ogee-tip configuration. Results of the investigation generally indicate that sweep angle has little effect on the characteristics of the ogee in diffusing a line vortex.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132355 , RASA-73-07
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  • 47
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    Low speed aerodynamic characteristics of a 17 percent thick airfoil section designed for general aviation applications (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Wind-tunnel tests have been conducted to determine the low-speed two-dimensional aerodynamic characteristics of a 17-percent-thick airfoil designed for general aviation applications (GA(W)-1). The results were compared with predictions based on a theoretical method for calculating the viscous flow about the airfoil. The tests were conducted over a Mach number range from 0.10 to 0.28. Reynolds numbers based on airfoil chord varied from 2.0 million to 20.0 million. Maximum section lift coefficients greater than 2.0 were obtained and section lift-drag ratio at a lift coefficient of 1.0 (climb condition) varied from about 65 to 85 as the Reynolds number increased from about 2.0 million to 6.0 million.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7428 , L-9132
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  • 48
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    Approximations in the minimum time-to-climb problem (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The minimum time-to-climb problem is formulated as a third order system and three approximate solutions based on reduced order systems are presented. The first of these is the often used energy state, the second is the less frequently used two state and the third is a slightly altered form of the second, herein called the modified two state. These three approximations are discussed and compared both qualitatively and, by using a numerical example, quantitatively. The numerical example is also solved by the steepest descent method to provide a basis for comparison. It is concluded that the modified two state approximation is significantly better than the other two. This approximation is used to assess the sensitivity of climb performance to various vehicle parameters and it is found that, as expected, thrust and weight influence the time-to-climb most strongly.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-62292
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  • 49
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    Streamline curvature design procedure for subsonic and transonic ducts (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A procedure for designing ducts for subsonic and transonic speeds is described. Examples discussed are a wind-tunnel contraction cone, a supersonic nozzle, and a diffuser. A listing of the computer program is included. The streamline curvature equations represent a form of the exact, compressible, inviscid flow equations. The method is applicable from low subsonic to supersonic speeds.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7368 , L-8963
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  • 50
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    Canard-wing lift interference related to maneuvering aircraft at subsonic speeds (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was conducted at Mach numbers of 0.7 and 0.9 to determine the lift interference effect of canard location on wing planforms typical of maneuvering fighter configurations. The canard had an exposed area of 16.0 percent of the wing reference area and was located in the plane of the wing or in a position 18.5 percent of the wing mean geometric chord above the wing plane. In addition, the canard could be located at two longitudinal stations. Two different wing planforms were tested: one with a leading-edge sweep angle of 60 deg and the other with a leading-edge sweep angle of 44 deg. The results indicated that although downwash from the canard reduced the wing lift at angles of attack up to approximately 16 deg, the total lift was substantially greater with the canard on than with the canard off. At angles of attack above 16 deg, the canard delayed the wing stall. Changing canard deflection had essentially no effect on the total lift, since the additional lift generated by the canard deflection was lost on the wing due to an increased downwash at the wing from the canard.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2897 , L-9096
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  • 51
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    Wind-tunnel roll-damping measurements of a winged space shuttle configuration in launch attitude (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Ground-wind load studies were conducted on three model configurations to assess the importance of aeroelastic instabilities of erected space shuttle vehicles. Roll damping was measured on a fuselage-alone model, which had a D cross section, and a fuselage and tail surfaces in combination with either a clipped-delta wing or a low-sweep tapered wing as the primary lifting surface. The largest negative roll-damping coefficients were measured with the fuselage-alone configuration and were a function of wind azimuth. At the wind azimuths at which the wing-fuselage configuration was unstable, the negative roll-damping coefficients were a function of reduced frequency.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7394 , L-8991
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  • 52
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    An experimental investigation of a highly underexpanded sonic jet ejecting from a flat plate into a subsonic crossflow (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The induced static pressures due to a highly underexpanded sonic jet ejecting normally from a flat plate into a subsonic crosswind have been investigated. These pressure data have been recorded on the flat plate for a range of nominal jet-to-free-stream dynamic-pressure ratios from 0 to 1000 at free-stream Mach numbers of 0.1, 0.2, 0.4, and 0.6. The static pressure data measured on the flat plate are presented and correlated based upon the Riemann shock geometry in the jet plume. This data correlation improves with increasing free-stream Mach number.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7314 , L-8863
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  • 53
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    Noise tests on an externally blown flap with the engine in front of the wing (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Noise tests were conducted with a nozzle exhausting over a small scale model of an externally blown flap (EBF) lift-augmentation system, with exhaust impingement on the wing leading edge. Two series of tests were conducted: with wing leading edge inside the nozzle; and with leading edge set back from the nozzle exit plane 1 diameter on the jet axis. The results indicated no significant differences in spectral shape, level, or directivity pattern. Static lift and thrust tests were conducted on the same model indicated considerable flow attachment on both configurations, with slightly greater attachment and turning for the wing outside the nozzle. Finally, a comparison with engine-above- and engine-below-the-wing EBF's tested by previous investigators shows the acoustic performance of the configurations tested for this report to lie between the other two.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2942 , E-7564
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  • 54
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    Results of a feasibility study using the Newton-Raphson digital computer program to identify lifting body derivatives from flight data (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A brief study was made to assess the applicability of the Newton-Raphson digital computer program as a routine technique for extracting aerodynamic derivatives from flight tests of lifting body types of vehicles. Lateral-direction flight data from flight tests of the HL-10 lifting body reserch vehicle were utilized. The results in general, show the computer program to be a reliable and expedient means for extracting derivatives for this class of vehicles as a standard procedure. This result was true even when stability augmentation was used. As a result of the study, a credible set of HL-10 lateral-directional derivatives was obtained from flight data. These derivatives are compared with results from wind-tunnel tests.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-56017
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  • 55
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    An experimental program using a 9.7 deg half-angle cone model at free stream Mach number equals 4.88 and alpha prime S of 10 deg and 29.5 deg (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The flow field of a blunted cone model at supersonic speeds is described. The data consist of surface pressure measurements, surface oil flow photographs, and schlieren photographs. The tests were conducted in a two-dimensional, blow down type wind tunnel, using air as a test gas. A mercury filled manometer board was used to measure model surface pressure data.
    Keywords: AERODYNAMICS
    Type: NASA-CR-134132 , REPT-73004
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  • 56
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    Effect of Subsonic Inlet Lip Geometry on Predicted Surface and Flow Mach Number Distributions (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effect of subsonic inlet lip geometry on predicted surface and flow Mach number distributions is illustrated. The theoretical results were obtained from incompressible potential flow calculations corrected for compressibility. The major emphasis of this investigation is on the low-speed (takeoff and landing) operating conditions. The low-speed results were obtained for a range of three geometric variables of interest: contraction ratio, defined as the ratio of highlight area to throat area; internal lip major - to minor-axis ratio; and internal lip shape. The low-speed results were obtained at both static conditions and a free-stream velocity of 42.6m/sec, with incidence angles ranging from 0 deg to 50 deg. The results indicate that of the three geometric variables considered, contraction ratio had the largest effect on the surface Mach number distributions. The effects of inlet diameter ratio and blunting of the external forebody on maximum external surface Mach numbers are illustrated at a cruise Mach number of 0.8.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7446 , E-7522
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  • 57
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    Geometry program for aerodynamic lifting surface theory (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program that provides the geometry and boundary conditions appropriate for an analysis of a lifting, thin wing with control surfaces in linearized, subsonic, steady flow is presented. The kernel function method lifting surface theory is applied. The data which is generated by the program is stored on disk files or tapes for later use by programs which calculate an influence matrix, plot the wing planform, and evaluate the loads on the wing. In addition to processing data for subsequent use in a lifting surface analysis, the program is useful for computing area and mean geometric chords of the wing and control surfaces.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-62309
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  • 58
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    Analysis and testing of aeroelastic model stability augmentation systems (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Testing and evaluation of a stability augmentation system for aircraft flight control were performed. The flutter suppression system and synthesis conducted on a scale model of a supersonic wing for a transport aircraft are discussed. Mechanization and testing of the leading and trailing edge surface actuation systems are described. The ride control system analyses for a 375,000 pound gross weight B-52E aircraft are presented. Analyses of the B-52E aircraft maneuver load control system are included.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132345 , D3-9245
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  • 59
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    The results of low-speed wind tunnel tests to investigate the effects of the NASA refan JT8D engine nacelles on the stability and control characteristics of the Boeing 727-200 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results from two low-speed wind tunnel tests of the Boeing 727-200 airplane as configured with the NASA refan JT8D-109 turbofan engines are presented. The objective of these tests was to determine the effects of the refan installation on the low-speed stability and control characteristics of the 727 airplane. Four side nacelle locations were tested to insure that aerodynamic interactions of the nacelles and empennage would be optimized. The optimum location was judged to be the same as that of the production JT8D-9 engines; the current production engine mounts can be used for this location. Some small changes in the basic airplane characteristics are attributable to the refan nacelles. The flaps up longitudinal and lateral-directional stability are both slightly increased for low angles of attack and sideslip respectively. The longitudinal stability at stall is improved for both the flaps up and landing flap configurations. The high attitude characteristics of the basic airplane are not significantly altered by the refan nacelle installation. Directional control capability is not affected by the refan nacelles.
    Keywords: AERODYNAMICS
    Type: NASA-CR-134503 , BCAC-D6-41312
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  • 60
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    Large amplitude flutter of a low aspect ratio panel at low supersonic speeds comparison of theory and experiment (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Flutter boundaries, as well as flutter limit cycle amplitudes, frequencies and stresses were computed for a panel of length-width ratio 4.48 exposed to applied in-plane and transverse loads. The Mach number range was 1.1 to 1.4. The method used involved direct numerical integration of modal equations of motion derived from the nonlinear plate equations of von Karman, coupled with linearized potential flow aerodynamic theory. The flutter boundaries agreed reasonably well with experiment, except when the in-plane loading approached the buckling load. Structural damping had to be introduced, to produce frequencies comparable to the experimental values. Attempts to compute panel deflections or stress at a given point met with limited success. There is some evidence, however, that deflection and stress maxima can be estimated with somewhat greater accuracy.
    Keywords: AERODYNAMICS
    Type: NASA-CR-120105 , AMS-1116
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  • 61
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    Transonic aerodynamic characteristics associated with variations in the geometry of the forward portion of irregular planform wings (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The experimental aerodynamic characteristics of three basic wing planforms on a conceptual orbiter fuselage (designated the LO-100) have been obtained in the 8-Foot Transonic Pressure Tunnel. The study included variations in the forward portion (fillet) of each basic wing. Fillet sweeps to 78 deg were investigated while holding the spanwise intersection of the fillet and wing constant. The data were obtained at Mach numbers of 0.35 to 1.2 and at Reynolds number (depending on Mach number) of 1.9 million to 2.11 million per foot. The angle of attack was varied from about minus 2 deg to 22 deg at 0 deg of sideslip.
    Keywords: AERODYNAMICS
    Type: NASA-CR-128781 , DMS-DR-2041
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  • 62
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    Research on the sonic boom problem. Part 2: Flow field measurement in wind tunnel and calculation of second order F-function (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation has been carried out in a wind tunnel to test some of the results of Landahl's second order theory. The slender models consisted of a parabolic spindle, tested at M = 3, and a wing body configuration, suggested by Ferri, and tested at M = 2.7. The theory indicates that shock position and strength at an arbitrary distance can be calculated by means of near field measurements. The results show that this method is an appropriate one for simple bodies and for bodies with complicated geometries as well.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2340 , FFA-AU-621-PT-2
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  • 63
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    Noise and wake structure measurements in a subsonic tip speed fan (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of an experimental program are reported which show the effect of blade angle, tip speed, fan pressure ratio, and thrust on noise of a model fan of 0.457m (18 inches) diameter operating at subsonic tip speeds at pressure ratios between 1.06 and 1.15. The fan used in this study had 12 blades, 7 stator vanes, and a spacing between the rotor and stator of 1.85 blade chords. This fan was originally designed for aerodynamic testing and was considered a good performer. It was used in the noise test program as it incorporated features found to reduce noise in an earlier analytical parametric study. For a given pressure ratio the fan was shown to exhibit minimum noise at the blade angle and tip speed near that of maximum aerodynamic efficiency. Also, the noise level and spectrum character of this fan showed excellent correlation with scaled data of a similar larger diameter fan. Results of the program confirm the trends shown in the earlier analytical parametric study which showed that fan noise could be reduced for a given thrust and pressure ratio by increasing fan solidity, improving fan aerodynamic design, and operating the fan at an optimum subsonic tip speed. In addition to noise, the blade wake characteristics at the leading edge of the stator were measured in this program. At root and tip sections some difference between predicted and measured wakes was found. However comparisons between predicted and measured wakes at mid span locations was found to be good.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2323
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  • 64
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    Effect of blockage ratio on drag and pressure distributions for bodies of revolution at transonic speeds (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental data were obtained in two wind tunnels for 13 models over a Mach number range from 0.70 to 1.02. Effects of increasing test-section blockage ratio in the transonic region near a Mach number of 1.0 included change in the shape of the drag curves, premature drag creep, delayed drag divergence, and a positive increment of pressures on the model afterbodies. Effects of wall interference were apparent in the data even for a change in blockage ratio from a very low 0.000343 to an even lower 0.000170. Therefore, models having values of blockage ratio of 0.0003 - an order of magnitude below the previously considered safe value of 0.0050 - had significant errors in the drag-coefficient values obtained at speeds near a Mach number of 1.0. Furthermore, the flow relief afforded by slots or perforations in test-section walls - designed according to previously accepted criteria for interference-free subsonic flow - does not appear to be sufficient to avoid significant interference of the walls with the model flow field for Mach numbers very close to 1.0.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7331 , L-8449
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  • 65
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    Performance of transonic fan stage with weight flow per unit annulus area of 178 kilograms per second per square meter (6.5(lb/sec)/(sq ft)) (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The overall and blade-element performances are presented over the stable flow operating range from 50 to 100 percent of design speed. Stage peak efficiency of 0.834 was obtained at a weight flow of 26.4 kg/sec (58.3 lb/sec) and a pressure ratio of 1.581. The stall margin for the stage was 7.5 percent based on weight flow and pressure ratio at stall and peak efficiency conditions. The rotor minimum losses were approximately equal to design except in the blade vibration damper region. Stator minimum losses were less than design except in the tip and damper regions.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2904 , E-7081
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    Exploratory investigation at Mach numbers from 0.40 to 0.95 of the effects of jets blown over a wing (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An exploratory investigation has been made at Mach numbers from 0.40 to 0.95 to determine the effects on lift, drag, and pitching moment of blowing a jet exhaust over the upper surface of a 50 deg swept leading-edge wing. Also investigated were the effects of varying the longitudinal and vertical location of the nozzle exit on the induced effects of jet blowing.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7367 , L-9067
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  • 67
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    Performance comparison of a lobed-daisy mixer nozzle with a convergent nozzle at subsonic speeds (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation to determine the performance, in terms of thrust minus nozzle axial force, of a lobed-daisy mixer nozzle has been conducted in a 16-foot transonic tunnel at static conditions and at Mach numbers from 0.40 to 0.90 at angles of attack from 4 minus to 8. Jet-total-pressure ratio was varied from about 1.2 to 2.0. The performance of a reference convergent nozzle with a similar nozzle throat area and length was used as a base line to evaluate the performance of the lobed-daisy mixer nozzle. The results of this investigation indicate that with no external airflow (Mach number M of 0), and at values of jet-total-pressure ratio between 1.2 and 2.0, the static thrust exerted by the lobed-daisy mixer nozzle is less than that of the convergent nozzle by about 10 percent of ideal gross thrust. About 3.4 percent of the thrust loss was attributed to an unintentional internal area expansion in the fan passage.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2806 , L-8939
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  • 68
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    Supersonic aerodynamic characteristics of the North American Rockwell ATP shuttle orbiter (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A wind tunnel study to determine the supersonic aerodynamic characteristics of a 0.01925-scale model of the space shuttle orbiter configuration is reported. The model consisted of a low-finess-ratio body with a blended 50 swept delta wing forming an ogee planform and a center-line-mounted vertical tail. Tests were made at Mach numbers from 1.90 to 4.63, at angles of attack from -6 to 30, at angles of sideslip of 0 and 3, and at a Reynolds number, based on body length, of 5.3x 1 million.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2804 , L-8840
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  • 69
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    On the numerical simulation of three-dimensional transonic flow with application to the C-141 wing (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results computed by a finite-difference, relaxation algorithm are presented for the supercritical flow (M = 0.825) about the C-141 airplane wing, which has sweep, taper, and twist. Comparisons with both wind-tunnel and flight data indicate that computed solutions of the classical transonic small disturbance equation can accurately simulate high Reynolds number flows when the shock sweep angle is small. It is also shown that this equation poorly approximates the complete potential equation when embedded shock waves are swept at angles greater than about 15 deg. Hence, a more consistent small disturbance equation is derived for use in more general cases.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6933 , A-4583
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  • 70
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    Analytical method for predicting the pressure distribution about a nacelle at transonic speeds (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The formulation and development of a computer analysis for the calculation of streamlines and pressure distributions around two-dimensional (planar and axisymmetric) isolated nacelles at transonic speeds are described. The computerized flow field analysis is designed to predict the transonic flow around long and short high-bypass-ratio fan duct nacelles with inlet flows and with exhaust flows having appropriate aerothermodynamic properties. The flow field boundaries are located as far upstream and downstream as necessary to obtain minimum disturbances at the boundary. The far-field lateral flow field boundary is analytically defined to exactly represent free-flight conditions or solid wind tunnel wall effects. The inviscid solution technique is based on a Streamtube Curvature Analysis. The computer program utilizes an automatic grid refinement procedure and solves the flow field equations with a matrix relaxation technique. The boundary layer displacement effects and the onset of turbulent separation are included, based on the compressible turbulent boundary layer solution method of Stratford and Beavers and on the turbulent separation prediction method of Stratford.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2217
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  • 71
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    Effect of nose shape and tail length on supersonic stability characteristics of a projectile (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effect of nose shape and tail length on the static stability of a fin-stabilized projectile has been investigated in the Langley Unitary Plan with tunnel at angles of attack to about 12 deg for a Mach number range from 1.5 to 2.5. The tests were made at a constant Reynolds number of 6.56 x 1,000,000 per meter. The results of the investigation showed that nose shape had no effect on the static stability. Increasing the tail length resulted in a progressively stabilizing tendency. However, only the 1.5-caliber-tail-length configuration was stable over the test angle-of-attack range at Mach number 1.5. This configuration was marginally stable or unstable at the higher Mach numbers, and the shorter configurations were unstable at all Mach numbers for either part of or the entire test angle-of-attack range.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2831 , L-8995
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  • 72
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    Full-scale experiments with an ejector to reduce jet engine exhaust noise (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experiments with a modified J65 turbojet engine and ejector resulted in noise power reductions as large as 13 decibels in the low-frequency range. High-frequency noise power, which appeared to originate mainly from the mixing processes within the ejector, increased. Peak velocities at the ejector exit were reduced by one-half to two-thirds, although survey rakes showed that mixing was not complete. Acoustical lining inside the ejector would reduce the perceived noise level (in PNdB) by removing much of the high-frequency noise.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2841 , E-7445
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  • 73
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    Aerodynamic and flow-visualization studies of two delta-wing entry vehicles at a Mach number of 20.3 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The longitudinal, lateral, and directional aerodynamic characteristics of two space shuttle concepts have been obtained in helium for operational flight Reynolds numbers at angles of attack from minus 10 to 55 deg. Included are elevon control deflections, roll control due to ailerons, and the effects of a nose modification. Selected results were compared with those derived from tangent-cone and Newtonian theories. Also included are results of a flow-visualization study consisting of electron-beam-illuminated flow and surface oil-flow patterns.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7282 , L-8892
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  • 74
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    FORTRAN program for calculating velocities and streamlines on the hub-shroud mid-channel flow surface of an axial- or mixed-flow turbomachine. 1: User's manual (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A FORTRAN 4 computer program has been developed that obtains a subsonic or shock-free transonic flow solution on the hub-shroud mid-channel flow surface of a turbomachine. The blade row may be fixed or rotating, and may be twisted and leaned. Flow may be axial or mixed, up to 45 deg from axial. Upstream and downstream flow variables may vary from hub to shroud, and provision is made to correct for loss of stagnation pressure. The results include velocities, streamlines, and flow angles on the flow surface; and approximate blade surface velocities. Subsonic solutions are obtained by a finite-difference stream-function solution. Transonic solutions are obtained by a velocity-gradient method, using information from a finite-difference stream-function solution at a reduced mass flow.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7343 , E-7154
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  • 75
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    Effect of fin planform on the aerodynamic characteristics of a wingless missile with AFT cruciform controls at Mach 1.60, 2.36, and 2.86 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was made in the Langley Unitary Plan wind tunnel to determine the effects of fin planform on the static longitudinal aerodynamic characteristics of a wingless maneuvering missile configuration having cruciform, all-movable, aft control surfaces. The tests were made at Mach numbers of 1.60, 2.36, and 2.86 through an angle of attack range from about -4 to 22 deg, at an angle of sideslip of 0 deg, and at a Reynolds number of 8.2 million based on model length. The pitch-control data were obtained at model roll angles of 0 and 45 deg. Control-surface forces and moments were also measured. Four alternate fin planforms were investigated.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2774 , L-8783
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  • 76
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    Aeronautical Engineering: A special bibiliography, supplement 30, April 1973 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This special bibliography lists 423 reports, articles, and other documents introduced into the NASA scientific and technical information system in March 1973.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(30)
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  • 77
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    Supersonic aerodynamic characteristics of hypersonic low-wave-drag elliptical body-tail combinations as affected by changes in stabilizer configuration (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation has been made at Mach numbers from 1.50 to 4.63 to determine systematically the effects of the addition and position of outboard stabilizers and vertical- and vee-tail configurations on the performance and stability characteristics of a low-wave-drag elliptical body. The basic body shape was a zero-lift hypersonic minimum-wave-drag body as determined for the geometric constraints of length and volume. The elliptical cross section had an axis ratio of 2 (major axis horizontal) and an equivalent fineness ratio of 6.14. Base-mounted outboard stabilizers were at various dihedral angles from 90 deg to minus 90 deg with and without a single center-line vertical tail or a vee-tail. The angle of attack was varied from about minus 6 to 27 deg at sideslip angles of 0 and 5 deg and a constant Reynolds number of 4.58 x one million (based on body length).
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2747 , L-8640
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  • 78
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    Geometric factors affecting noise suppresion and thrust loss of divergent-lobe supersonic jet noise suppressor (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: The thrust loss and noise suppression of a divergent-lobe supersonic jet noise suppressor were experimentally determined over a range of nozzle pressure ratios of 1.5 to 4.0. These small-scale cold flow tests were made to determine the effect on thrust and noise of: suppressor length, rearward facing step height, suppressor divergence angle, and ejector shroud length and location. Noise suppression was achieved at nozzle pressure ratios of 2.5 and greater. Maximum lobe jet noise attenuation of 15 db with thrust loss differences of 1.5 percent compared to the convergent nozzle were obtained at a nozzle pressure ratio of 3.5 with an ejector shroud two nozzle diameters long. Without the ejector the attenuation was 13 db with thrust loss differences of 11 percent. Short suppressors approximately one primary nozzle throat diameter long performed as well as longer suppressors. Rearward facing step height had a significant effect on noise suppression. Ejector shrouds two nozzle diameters in length are feasible.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2820 , E-7393
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  • 79
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    Maneuver and buffet characteristics of fighter aircraft (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Recent research efforts in the improvement of the maneuverability of fighter aircraft in the high-subsonic and transonic speed range are reviewed with emphasis on the factors affecting aerodynamic boundaries, such as maximum obtainable lift, buffet onset, pitchup, wing rock, and nose slice. The investigations were made using a general research configuration which encompassed a systematic matrix of wing-design parameters. These results illustrated the sensitivity of section and planform geometry to a selected design point. The incorporation of variable-geometry wing devices in the form of flaps or leading-edge slats was shown to provide controlled flow over a wide range of flight conditions and substantial improvements in maneuver capabilities. Additional studies indicated that the blending of a highly swept maneuver strake with an efficient, moderately swept wing offers a promising approach for improving maneuver characteristics at high angles of attack without excessive penalties in structural weight.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7131 , L-8554
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  • 80
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    An investigation of a two-dimensional propulsive lifting system (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: Several aspects of the nonhomogeneous flow associated with a system combining lifting and propulsive requirements of an aircraft are considered by analytical and experimental methods. The basic geometry of the problem is that of two lifting surfaces with an actuator disk located between them. The principles governing flow with energy addition are examined. Basic equations and boundary conditions are developed for the complete inviscid and incompressible analysis for the two-dimensional case. The corresponding flow singularities are discussed and the integral equations which completely specify the system are derived. The two special cases of small and large energy addition are considered in detail including solutions. A numerical procedure is developed to solve the full problem including allowance for the wake deflection. Appropriate vorticity forms are used to represent the entire system. An iterative scheme is presented which rapidly converges to a solution for the magnitude and location of the system vorticity distributions. Forces and moments are evaluated on the propulsive lift system.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2250
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  • 81
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    Development of a nonlinear unsteady transonic flow theory (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: A nonlinear, unsteady, small-disturbance theory capable of predicting inviscid transonic flows about aerodynamic configurations undergoing both rigid body and elastic oscillations was developed. The theory is based on the concept of dividing the flow into steady and unsteady components and then solving, by method of local linearization, the coupled differential equation for unsteady surface pressure distribution. The equations, valid at all frequencies, were derived for two-dimensional flows, numerical results, were obtained for two classses of airfoils and two types of oscillatory motions.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2258 , NEAR-TR-46
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  • 82
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    An improved method for the aerodynamic analysis of wing-body-tail configurations in subsonic and supersonic flow. Part 1: Theory and application (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A new method has been developed for calculating the pressure distribution and aerodynamic characteristics of wing-body-tail combinations in subsonic and supersonic potential flow. A computer program has been developed to perform the numerical calculations. The configuration surface is subdivided into a large number of panels, each of which contains an aerodynamic singularity distribution. A constant source distribution is used on the body panels, and a vortex distribution having a linear variation in the streamwise direction is used on the wing and tail panels. The normal components of velocity induced at specified control points by each singularity distribution are calculated and make up the coefficients of a system of linear equations relating the strengths of the singularities to the magnitude of the normal velocities. The singularity strengths which satisfy the boundary condition of tangential flow at the control points for a given Mach number and angle of attack are determined by solving this system of equations using an interactive procedure. Once the singularity strengths are known, the pressure coefficients are calculated, and the forces and moments acting on the configuration determined by numerical integration.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2228-PT-1
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  • 83
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    An improved method for the aerodynamic analysis of wing-body-tail configurations in subsonic and supersonic flow. Part 2: Computer program description (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see
    Keywords: AERODYNAMICS
    Type: NASA-CR-2228-PT-2
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  • 84
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    A new technique for calculating reentry base heating (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The laminar base flow field of a two-dimensional reentry body has been studied by Telenin's method. The flow domain was divided into strips along the x-axis, and the flow variations were represented by Lagrange interpolation polynomials in the transformed vertical coordinate. The complete Navier-Stokes equations were used in the near wake region, and the boundary layer equations were applied elsewhere. The boundary conditions consisted of the flat plate thermal boundary layer in the forebody region and the near wake profile in the downstream region. The resulting two-point boundary value problem of 33 ordinary differential equations was then solved by the multiple shooting method. The detailed flow field and thermal environment in the base region are presented in the form of temperature contours, Mach number contours, velocity vectors, pressure distributions, and heat transfer coefficients on the base surface. The maximum heating rate was found on the centerline, and the two-dimensional stagnation point flow solution was adquate to estimate the maximum heating rate so long as the local Reynolds number could be obtained.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7508 , M-116
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  • 85
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    Experimental study on optimization parameters of a supersonic jet ejector thrust augmentor. (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The experimental data were aimed at obtaining the effect of jet mixing, the effective length/diameter of the ejector tube, the entrance length shape factor, the shape loading, and the optimum primary jet location. The total augmented thrust is proportional to the diameter of the ejector. The data show that for a practical design the entrance lip shape and the stream lines around the lip are also important in order to optimize the percentage augmentation.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 10; Sept
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  • 86
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    Aerodynamic noise emission from turbulent shear layers. (1973)
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    Publication Date: 2019-06-27
    Description: The Phillips (1960) convected wave equation is employed in this paper to study aerodynamic noise emission processes in subsonic and supersonic shear layers. The wave equation in three spatial dimensions is first reduced to an ordinary differential equation by Fourier transformation and then solved via the WKBJ method. Three typical solutions are required for discussions in this paper. The current results are different from the classical conclusions. The effects of refraction, convection, Mach-number dependence and temperature dependence of turbulent noise emission are analyzed in the light of solutions to the Phillips equation.
    Keywords: AERODYNAMICS
    Type: Journal of Fluid Mechanics; 59; July 17
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  • 87
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    High-speed leading edge problem. (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The sharp leading edge problem has been studied for both monatomic and diatomic gases using the Boltzmann equation with the Bhatnagar-Gross-Krook type models as the governing equation and the discrete ordinate method with a closed-boundary value approach as a tool. Plate length relative to the freestream mean free path is taken to be 52. The gas-surface interaction law is assumed to be diffuse reflection. The local distribution functions of molecular velocities and internal energies (for the diatomic gas) for the entire flowfield have been calculated for a freestream Mach number of 6.1. Comparisons are made between the calculated results and experimental data.
    Keywords: AERODYNAMICS
    Type: Physics of Fluids; 16; June 197
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  • 88
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    Ablation and radiation coupled viscous hypersonic shock layers. (1973)
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    Publication Date: 2019-06-27
    Description: Coupled ablator shock layer solutions for the stagnation point are presented for typical hyperbolic entry atmospheric flight conditions. These solutions were obtained by numerically solving the stagnation line shock layer equations and quasi-steady ablator equations. These equations included ablation and radiation coupling within the viscous shock layer, line and continuum radiation for both air and phenolic-nylon ablation species and local thermodynamic equilibrium throughout. The results presented provide a sound basis for understanding many of the processes characteristic of hypersonic shock layer heating.-
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 11; Aug. 197
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  • 89
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    Pressure distribution and velocity profiles in supersonic laminar wakes. (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The method of integral relations is applied to calculate the characteristics of laminar wakes in supersonic flow past a wedge with a flat base. An earlier analysis of the flow in the critical recompression region is extended so that the flow near the base can be determined. Results are worked out for flow past a wedge of 10-deg semiangle at Mach number 6 and two values of Reynolds number. The pressure distribution along the axis is calculated, together with velocity profiles at various stations and streamline patterns in the recirculation region. Good agreement with experiment is found.
    Keywords: AERODYNAMICS
    Type: AD-776840 , AFOSR-74-0384TR
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  • 90
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    Downwash-velocity potential method for oscillating surfaces. (1973)
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    Publication Date: 2019-06-27
    Description: The application of the downwash-velocity potential method to the case of oscillating surfaces is developed, and calculated forces are given on rectangular airfoils of aspect ratio two rotating about midchord in subsonic flows. These are compared with other results published in the literature for reduced frequencies up to nine-tenths, and for Mach numbers up to nine-tenths. The concept of 'aerodynamic elements' is presented, the computed results representing three possible types of rectangular element.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 11; May 1973
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  • 91
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    Secondary flows - Theory, experiment, and application in turbomachinery aerodynamics. (1973)
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    Publication Date: 2019-06-27
    Keywords: AERODYNAMICS
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  • 92
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    Laminar boundary layer on a cone near a plane of symmetry. (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The three-dimensional laminar boundary layer near the planes of symmetry of a cone with either outflow or inflow is studied in supersonic and hypersonic flow. Solutions are presented for a variety of values of three parameters, namely those of cross flow, external Mach number, and wall enthalpy ratio. Also asymptotic solutions for ranges of pertinent similarity variables are developed and used in numerical analyses so as to assure exponential behavior as the similarity variables approach infinity. Of special interest in the results is the existence for outflow, i.e., for the windward plane of symmetry, of a new solution branch and for inflow of four solution branches. The physical significance of the new solutions is discussed.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 11; Mar. 197
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  • 93
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    Penetration of retrorocket exhausts into subsonic counterflows. (1973)
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    Publication Date: 2019-06-27
    Description: Simulation experiments were performed in the NASA Langley Full Scale Tunnel to investigate the retroplume heating rates encountered by a lander vehicle during a terminal descent to a planetary surface. A 10% scale model of the Viking Lander with freestream velocity conditions from 37 to 75 ft/sec was used for simulation. The simulation test data were close to the theoretical predictions of Hill et al. (1971).
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 10; Jan. 197
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  • 94
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    Hypersonic flows in large-scale inlet models. (1973)
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    Publication Date: 2019-06-27
    Description: Analytical and experimental investigations were conducted to determine the characteristics of the internal flows in model passages representative of inlets for a typical Mach 12 hypersonic cruise vehicle and also sufficiently large for reliable data to be obtained. Three large-scale inlet models, each having a different internal compression ratio, were designed to provide maximum performance at the throat stations. Tests were conducted in the Mach 7.4 nozzle of the NASA Ames 3.5-foot hypersonic wind tunnel at a nominal test Reynolds number of 2,700,000 per ft. The experimental results revealed that a high level of total pressure recovery, approximately 0.85 (relative to the inlet-entrance conditions) for the core flow of the internal passage, was achieved for each inlet design.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 10; Jan. 197
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  • 95
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    An experimental investigation of vortex stability, tip shapes, compressibility, and noise for hovering model rotors (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Schlieren methods of flow visualization and hot-wire anemometry for velocity measurements were used to investigate the wakes generated by hovering model propellers and rotors. The research program was directed toward investigating (1) the stability of the tip vortex, (2) the effects produced by various tip shapes on performance and tip vortex characteristics, and (3) the shock formation and noise characteristics associated with various tip shapes. A free-wake analysis was also conducted for comparison with the vortex stability experimental results. Schlieren photographs showing wake asymmetry, interaction, and instability are presented along with a discussion of the effects produced by the number of blades, collective pitch, and tip speed. Two hot-wire anemometer techniques, used to measure the maximum circumferential velocity in the tip vortex, are discussed.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2305 , BELL-299-099-641
    Format: application/pdf
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  • 96
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    Effect of nozzle lateral spacing, engine interfairing shape, and angle of attack on the performance of a twin-jet afterbody model with cone plug nozzles (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Twin-jet afterbody models were investigated by using two balances to measure separately the thrust minus total axial force and the afterbody drag at Mach numbers from 0 to 1.3. Angle of attack was varied from minus 2 deg to 8.5 deg. Translating shroud cone plug nozzles were tested at dry-power and maximum-afterburning-power settings with a high-pressure air system used to provide jet total-pressure ratios up to 9.0. Two nozzle lateral spacings were studied by using afterbodies with several interfairing shapes. The close- and wide-spaced afterbodies had identical cross-sectional area distributions when similar interfairings were installed on each. The results show that the highest overall performance was obtained with the close-spaced afterbody and basic interfairings. Increasing angle of attack decreased performance for all configurations and conditions investigated.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2724 , L-8690
    Format: application/pdf
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  • 97
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    Studies in tilt rotor VTOL aircraft aeroelasticity, volume 2 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Two methods for natural mode vibration analysis are discussed. The first consists of a direct approach based on a finite element representation of the complete structure as an entity. The mass and stiffness matrices for the complete structure are assembled by properly combining the mass and stiffness matrices of the individual elements into which the structure has been divided. The second approach is that of component mode synthesis. This method is based on the concept of synthesizing the natural modes of the complete structure from modes of conveniently difined substructures, or components, into which the structure has been partitioned. In this way the expedient of reducing the system degrees of freedom, and thus the size of the eigenvalue problem, can be introduced by partial modal synthesis.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-69496
    Format: application/pdf
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  • 98
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    Flight-measured X-24A lifting body control surface hinge moments and correlation with wind tunnel predictions (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Control-surface hinge-moment measurements obtained in the X-24A lifting body flight-test program are compared with results from wind-tunnel tests. The effects of variations in angle of attack, angle of sideslip, rudder bias, rudder deflection, upper-flap deflection, lower-flap deflection, Mach number, and rocket-engine operation on the control-surface hinge moments are presented. In-flight motion pictures of tufts attached to the inboard side of the right fin and the rudder and upper-flap surfaces are discussed.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2816 , H-748
    Format: application/pdf
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  • 99
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    Aerodynamic characteristics of a vectored-thrust V/STOL fighter in the transition speed range (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A wind-tunnel investigation was conducted with a vectored-thrust V/STOL fighter configuration. The model was equipped with two nacelle-mounted vectored-thrust jet simulators and one lift-jet simulator. The vectored-thrust jet could be tested at two alternate longitudinal positions and three nozzle deflection angles. The vectored-thrust configuration with the rear nozzles showed an increase in lift and a decrease in pitching moment when compared with the forward nozzles. The rear nozzles also improve stall characteristics.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7191 , L-8457
    Format: application/pdf
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  • 100
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    Influence matrix program for aerodynamic lifting surface theory (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A users manual is described for a USA FORTRAN 4 computer program which computes an aerodynamic influence matrix and is one of several computer programs used to analyze lifting, thin wings in steady, subsonic flow according to a kernel function method lifting surface theory. The most significant features of the program are that it can treat unsymmetrical wings, control points can be placed on the leading and/or trailing edges, and a stable, efficient algorithm is used to compute the influence matrix.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-62324
    Format: application/pdf
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