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  • AERODYNAMICS
  • Animals
  • 2000-2004
  • 1970-1974  (252)
  • 1925-1929
  • 1972  (252)
Collection
Keywords
Years
  • 2000-2004
  • 1970-1974  (252)
  • 1925-1929
Year
  • 1
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    In-flight aeroacoustic environments on prospective space shuttle vehicles (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The problem of in-flight aerodynamic noise has been studied by reliable estimates of full scale surface-pressure fluctuations from scale model tests in wind tunnels. Scaling relationships have been verified, and many details of the fluctuating pressure characteristics such as spatial correlation and convection velocities are understood. The effects of the wind tunnel environmental turbulence and noise have also been investigated sufficiently so that threshold levels of usable data are known.
    Keywords: AERODYNAMICS
    Type: NASA Space Shuttle Technol. Conf.; p 71-96
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  • 2
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    Summary and future plans (1972)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: Supercritical Wing Technol.: A Report on Flight Evaluation; p 121-133
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  • 3
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    Piloting and operational aspets of the F-8 supercritical wing airplane (1972)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: Supercritical Wing Technol.: A Report on Flight Evaluation; p 97-110
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  • 4
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    Status of the F-8 supercritical wing program (1972)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: Supercritical Wing Technol.: A Report on Flight Evaluation; p 49-58
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  • 5
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    F-8 supercritical wing pressure distribution evaluation (1972)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: Supercritical Wing Technol.: A Report on Flight Evaluation; p 71-84
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  • 6
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    Buffet characteristics of the F-8 supercritical wing airplane (1972)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: Supercritical Wing Technol.: A Report on Flight Evaluation; p 85-96
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  • 7
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    The NASA supercritical airfoil and its application to swept wings (1972)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: Supercritical Wing Technol.: A Report on Flight Evaluation; p 1-12
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  • 8
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    Evolution of the F-8 supercritical wing configuration (1972)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: Supercritical Wing Technol.: A Report on Flight Evaluation; p 35-48
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  • 9
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    EBF noise tests with engine under-the-wing and over-the-wing configurations (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Noise tests of externally blown flaps with the engine under the wing and engine over the wing configurations were conducted. Flap noise data obtained on a TF-34 aircraft are discussed. Noise data obtained during a free-jet forward-speed-effect analysis are presented. Noise sources associated with upper surface flap blowing are described. Results of a small scale configuration screening study and some large scale model test data are analyzed. The noise data for the engine over wing configurations are compared with the engine under the wing configurations.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 455-473
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  • 10
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    Flap noise generation and control (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: The characteristics of aerodynamic noise generated by the interaction of an airstream with a flap surface are discussed. The location and behavior of various noise sources were investigated to determine optimal quieting techniques. A schematic diagram of the jet-flap concepts being considered for integrated-powered-lift systems for short takeoff aircraft is shown. Each of the concepts has in common high velocity turbulent air flowing over relatively rigid surfaces with resultant production of interaction noise. The nature, location, and control of noise sources which involve the interactions of air flows with airfoil surfaces are examined.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 413-426
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  • 11
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    Acoustic characteristics of large-scale STOL models at forward speed (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Wind-tunnel investigations of the acoustic characteristics of the externally blown jet flap (EBF) and augmentor wing STOL concepts are discussed. The large-scale EBF model was equipped with a triple-slotted flap blown by four JT15D turbofan engines with circular, coannular exhaust nozzles. The large-scale augmentor wing model was equipped with an unlined augmentor blown by a slot primary nozzle. The effects of airspeed and angle of attack on the acoustics of the EBF were small. Flap deflection had a greater effect on the acoustics of the augmentor wing than did airspeed. The total sound power was also significantly higher for landing indicating that turning in the augmentor generated acoustic energy. Airspeed produced a small aft shift in acoustic directivity with no significant change in the peak perceived noise levels or sound power levels. Small-scale research of the acoustics for the augmentor wing has shown that by blowing an acoustically treated augmentor with a lobed primary nozzle, the 95-PNdb noise level goal can be achieved or surpassed.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 443-454
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  • 12
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    Externally blown flap impingement noise (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Tests of the noise produced by the impingement of the jet exhaust on the wing and flap for an externally blown flap system were conducted with a CF700 turbofan engine and an F-111B wing panel. The noise produced with a daisy nozzle installed on the engine was greater than that produced by a conical nozzle at the same thrust. The presence of the wing next to the test nozzles increased the noise, as did increasing the flap deflection angle. Compared with the conical nozzle, the daisy nozzle produced slightly less noise at a flap deflection of 60 deg but produced more noise at the lower flap deflections tested. Tests showed that the single-slotted flap deflected 60 deg, produced less noise than the double-slotted flaps. Also, maintaining the maximum distance between the exit nozzle and flap system resulted in a minor reduction in noise.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 427-441
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  • 13
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    Survey of wing and flap lower-surface temperatures and pressures during full-scale ground tests of an externally blown flap system (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Full-scale ground tests of an externally blown flap system were made using the wing of an F-111B airplane and a CF700 engine. Pressure and temperature distributions were determined on the undersurface of the wing, vane, and flap for two engine exhaust nozzles (conical and daisy) at several engine power and engine/wing positions. The tests were made with no airflow over the wing. The leading-edge wing sweep angle was fixed at 26 deg, the angle of incidence between the engine and the wing was fixed at 3 deg, and the tests were conducted with the flap retracted, extended and deflected 35 deg, and extended and deflected 60 deg. The integrated local pressures on the undersurface of the flap produced loads approximately three times as great at the 60 deg flap position as at the 35 deg flap position. With both nozzle configurations, more than 90 percent of the integrated pressure loads were contained within plus or minus 20 percent of the flap span centered around the engine exhaust centerline. The maximum temperature recorded on the flaps was 218 C (424 F) for the conical nozzle and 180 C (356 F) for the daisy nozzle.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 143-156
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  • 14
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    Simulator evaluation of the flying qualities of externally blown flap and augmentor wing transport configurations (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Concurrent simulations of powered-lift STOL transport aircraft having either an externally blown flap configuration or an augmentor wing configuration were conducted. The following types of simulators of varying sophistication were used: (1) a simple fixed-base simulation with a simple visual display, (2) a more complex fixed-base simulation using a realistic transport cockpit and a high-quality visual display, and (3) a six-degree-of-freedom motion simulator that had a realistic transport cockpit and a sophisticated visual display. The unaugmented flying qualities determined from these simulations were rated as unacceptable for both the externally blown flap and augmentor wing configurations. The longitudinal, lateral-directional, and single-engine-failure characteristics were rated satisfactory with extensive augmentation, including pitch and roll command systems, flight-path (or speed) augmentation, turn coordination, and effective yaw damping. However, the flare and landing characteristics from any approach glide-path angle in excess of 4 deg were rated as unsatisfactory but acceptable.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 157-800
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  • 15
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    Aerodynamics of the upper surface blow flap (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: The results of some preliminary wind-tunnel investigations made to provide fundamental aerodynamic information on the upper surface blown jet-flap concept incorporating high-bypass-ratio turbofan engines are summarized. The results of the investigation have shown the concept to have aerodynamic performance generally similar to that of other externally blown high-lift systems. A few of the more critical problems associated with this concept have been identified and preliminary solutions to some of these problems have been found. These results have proven to be sufficiently encouraging to warrant continuation of fundamental research efforts on the concept.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center STOL Technol.; p 97-110
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  • 16
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    Advanced augmentor-wing research (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Results of research on advanced augmentors are discussed. Research concerned with performance has indicated that: (1) augmentors with lobe-type nozzles give higher thrust augmentation than those with slot-type primary nozzles, (2) the thrust of augmentor wings at forward speed is greater than that of internally blown flaps for the speed range of interest, and (3) the optimum augmentor geometry at forward speed may be different from the optimum static geometry. Analysis of augmentor-wing data has shown that the data may be correlated by accounting for the augmentation and entrainment in defining a net thrust coefficient.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 87-96
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  • 17
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    Aerodynamic characteristics of a swept augmentor wing (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: A brief outline of augmentor wing research sponsored by Ames Research Center is presented and is followed by a discussion of large-scale wind-tunnel test results for a swept augmentor wing configuration. The results showed that the augmentor wing could be applied to high-speed swept wing designs with little adverse effect on either the basic performance of the augmentor or the longitudinal characteristics, including maximum lift and stall. Three lateral control devices were shown to be effective and ground effect was measured for several complete aircraft configurations.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 71-86
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  • 18
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    Aerodynamic loads measurements on externally blown flap STOL models (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Small-scale-model data have shown large static loads on the flap system behind the engines. The large-scale-model tests confirmed the magnitude of these loads and indicated that the relative loading of each flap element depends on the engine-wing-flap geometry. Flap response measurements indicated that the unsteady pressure loading excited the natural vibration modes of the flap system on this model. Since this was a boilerplate model, the only conclusion that can be drawn is that the possibility of large vibration loads must be considered for a flight-weight structure. The similarity of the unsteady pressure and flap response spectra for the wind-off and wind-on cases indicated that it may be possible to realistically test flight-weight flap structures on a static test stand rather than endure the extra costs and scheduling problems associated with large-scale wind-tunnel tests. There is a potential flap-temperature problem which if not resolved might preclude the use of materials such as aluminum and the composites in the flap structure.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 121-130
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  • 19
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    Aerodynamic and performance characteristics of externally blown flap configurations (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: The application of externally blown flaps for improving the performance of short takeoff aircraft is discussed. The characteristics of externally blown flap powered lift are examined. A method for predicting the aerodynamic performance of a particular externally blown flap configuration is presented. The following specific effects are analyzed: (1) induced aerodynamics, (2) static turning, (3) flap span and deflection, and (4) engine size and chord flap.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 43-54
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  • 20
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    Stability and control of externally blown flap configurations (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: The results of wind-tunnel investigations on the stability and control characteristics of externally blown jet-flap configurations are presented. Conventional wind-tunnel tests and free-flight model tests have shown that longitudinal trim and stability can be achieved by a properly located horizontal tail of sufficient size, and that lateral trim in the engine-out condition can be produced by combinations of differential flap, spoiler, and rudder deflection. Free-flight model tests have revealed a lightly damped Dutch roll lateral oscillation, and have shown that the oscillation can be stabilized by use of artificial damping.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 55-70
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  • 21
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    Reduction of wave drag by antisymmetric arrangement of wings and bodies. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The wave interference effects for bodies or wings in a mirror-symmetric arrangement, and in an antisymmetric arrangement are discussed. It is shown that while in the case of a mirror-symmetric arrangement large adverse interference effects can be observed, antisymmetric arrangements provide comparatively much smaller wave drags. The single continuous wing panels also adapt themselves more readily to varying angles of obliquity, and hence, to varying flight speeds. A detailed review is presented of the previous work on the aerodynamic properties and flight stability of oblique elliptic wing combinations. A possible mode of application of these combinations to transport aircraft operating at moderate supersonic speeds is suggested.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Feb. 197
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  • 22
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    Impact probe displacement in a supersonic turbulent boundary layer. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The experiment was performed on the test section sidewall in a supersonic pressure tunnel. The boundary layer at the test station was surveyed in turn by each of 8 impact probes ranging in size from about 1.3 to 48 mm. The impact pressures measured by these probes were combined with the test section static pressure to calculate Mach numbers. Probe displacement effects were evaluated in terms of these Mach number values.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Apr. 197
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  • 23
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    Effects of transverse outflow from a hypersonic separated region. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Features of hypersonic, finite-span separated flows with a turbulent boundary layer have been studied to provide a partial assessment of transverse outflow effects on separated flowfield characteristics. Results demonstrate the critical importance of transverse outflow in determining some of the characteristic features of a turbulent, separated boundary layer.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Apr. 197
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  • 24
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    Turbulent-wake calculations with an eddy-viscosity model. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: A simple eddy-viscosity model is shown to make it possible to calculate numerically the mean properties of a turbulent wake. Although the structure of the Reynolds stress terms is not resolved, the results obtained are adequate for predicting velocity profiles and displacement thicknesses.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Feb. 197
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  • 25
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    Shock-wave, turbulent boundary-layer interaction on a blunted compression surface. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The application of Rose's (1970) analytical method to the study of a shock wave interacting with a turbulent layer on a blunted compression surface is described. Only those details of the method that specifically apply to the case under consideration are discussed.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 9; Apr. 197
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  • 26
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    Measurements of skin friction on the wall of a hypersonic nozzle. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Direct skin friction measurements obtained on the wall of a Mach 19.8 nozzle are presented. These measurements of skin friction and values deduced from the profile data are compared with predictions from a finite difference theory and also with several 'flat-plate' prediction methods for skin friction.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Sept
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  • 27
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    Taylor instability in the shock layer on a Jovian atmosphere entry probe. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Investigation of the Taylor instability relative to the dynamical instability whose presence in the shock layer on a spacecraft entering the Jovian atmosphere is to be expected because of the difference in velocity across the shear layer. Presented calculations show that the Taylor instability at the interface between shock-heated freestream gas and ablation products is inconsequential in comparison to the shear layer instability.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 9; Sept
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  • 28
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    Transition in compressible free shear layers. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The transition Reynolds number for shear layers produced by interactions between weak and strong shock waves is determined on the basis of experiments performed in a 20-in. (Mach 6) and an 11-in. (Mach 6.9) hypersonic tunnel. A variable angle wedge was used to generate a planar shock wave which interacted with the bow wave of a blunt body. An average value of the transition length (defined as the length along the shear layer from the shock interaction to the point where turbulence became visible on schlieren photographs) was used to determine the transition Reynolds number.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 9; Aug. 197
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  • 29
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    Correlations of peak heating in shock interference regions at hypersonic speeds. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Correlations are given of measured pressure and heat-transfer peaks for shock/boundary-layer interactions and shear layer attachment on configurations with both two- and three-dimensional interactions. The peak values were obtained from an investigation of shock interference heating on hemispheres, a 30-deg included angle wedge, and a 2.54-cm-diam cylindrical leading-edge fin model. The investigation covers data for Mach numbers of 6 and 20 over freestream Reynolds numbers ranging from (3.3 to 25.6) million per meter, and specific heat ratios of 1.4 and 1.67.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 9; Aug. 197
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  • 30
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    The effect of angle of attack on boundary-layer transition on cones. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Boundary-layer transition on 5- and 15-deg half-angle cones was studied as a function of angle of attack (ranging from 0 to 20 deg) in a 3.5 ft hypersonic wind tunnel at a freestream Mach number of 7.4. It is shown that the influence of the angle of attack on the transition Reynolds number is a function of the meridian angle. On the windward ray of the 15-deg cone, transition Reynolds numbers show an initial slight increase and then a decrease with increasing angle of attack; leeward-ray Reynolds numbers for this cone decrease rapidly with angle of attack. Windward-ray transition Reynolds numbers increase monotonically with angle of attack on the 5-deg cone, but the effect of the angle of attack on the leeward ray is the same as for the 15-deg cone.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Aug. 197
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  • 31
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    Computation of transonic flow about finite lifting wings. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The results of Murman and Krupp (1971) are used to develop a procedure for computing a transonic flow about a finite lifting wing. A small disturbance equation describing the velocity potential of three-dimensional wings is solved in the process. The procedure is applied to a wing with a symmetric biconvex airfoil section in a zero-incidence subsonic flow, to a supersonic rectangular lifting wing with a sharp leading edge and to a subcritical nonlifting rectangular wing with a blunt leading edge.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; July 197
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  • 32
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    Subsonic, transonic, and supersonic nozzle flow by the inverse technique. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The inverse technique is used to obtain a mathematically and physically consistent solution of the flowfield in a nozzle from the mass generation surface through the supersonic region. The inverse method employs an assumed centerline function which is of the Cauchy type in that the values and the derivatives of the function are known. Since the Cauchy boundary conditions can give rise to numerical instabilities, the governing gasdynamic equations for rotational steady flow were transformed into a form which puts the geometry into a rectangular shape, and which spaces the network of interior points more finely in regions of the greatest gradients of the dependent variables. For arbitrarily specified centerline data, the solution of the governing flow equations may not exist, and if it does it may not depend continuously on the data.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 9; June 197
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  • 33
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    Influence of contraction section shape and inlet flow direction on supersonic nozzle flow and performance. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Wall static pressure measurements and performance parameters are presented for axisymmetric supersonic nozzles with relatively steep convergent sections and comparatively small radius-of-curvature throats. The nozzle walls were essentially adiabatic. These results are compared with those obtained in other nozzles tested previously to appraise the influence of contraction shape on performance. Both the flow coefficient and the thrust were less than the corresponding values for one-dimensional, isentropic, plane flow for both the axial and radial inflow nozzles considered, but the specific impulse, the most important performance parameter, was found to be relatively unchanged. The thrust decrement for the axial inflow nozzles was established primarily by the shape of the contraction section, and could be estimated reasonably well from a conical sink flow consideration. The radial inflow nozzle has a potential advantage from a cooling point of view if used in a rocket engine.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 9; June 197
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  • 34
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    Cone transitional boundary-layer structure at Me = 14. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Experimental results suggest that the boundary-layer mean profiles in hypersonic flows may be highly transitional in the outer part of the boundary layer before the transition process is detected at the surface. Means of determining the initial location where the transition process begins in the outer part of the boundary layer are considered.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; May 1972
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  • 35
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    Aerodynamic properties of spherical balloon wind sensors. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A first-order theory of the fluctuating lift and drag coefficients associated with the aerodynamically induced motions of rising and falling spherical wind sensors is developed. The equations of motion of a sensor are perturbed about an equilibrium state in which the buoyancy force balances the mean vertical drag force. It is shown that, to within first order in perturbation quantities, the aerodynamic lift force is confined to the horizontal, and the fluctuating drag force associated with fluctuations in the drag coefficient acts along the vertical. The perturbation equations are transformed with Fourier-Stieltjes integrals. The resulting equations lead to relationships between the power spectra of the aerodynamically induced velocity components and the spectra of the fluctuating lift and drag coefficients.
    Keywords: AERODYNAMICS
    Type: Journal of Applied Meteorology; 11; Apr. 197
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  • 36
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    Multiple-orifice liquid injection into hypersonic air streams. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Review of oblique water and fluorocarbon injection test results obtained in experimental studies of the effects of multiple-orifice liquid injection into hypersonic air streams. The results include the finding that maximum lateral penetration from such injections increases linearly with the square root of the jet-to-freestream dynamic-pressure ratio and is proportional to an equivalent orifice diameter.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Dec. 197
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  • 37
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    Lee-side vortices on delta wings at hypersonic speeds. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: A fluid-dynamic investigation was carried out to determine the cause of intense heating observed on the lee meridian of hypersonic delta wings and also to derive means for its suppression. Several experimental techniques were combined with analysis of extensive heat-transfer measurements at a freestream Mach number of six in a range of Reynolds number to acquire a general description of the lee-flow structure. With attached leading-edge flow on the delta wings, the dominant feature is a pair of embedded vortices on the lee meridian whose interaction with the boundary-layer is responsible for the observed local heating. On the basis of flow visualization results and heat-transfer correlations, a qualitative vortex flow model is proposed which differs essentially from the conventional inboard separation vortex model.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Nov. 197
    Format: text
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  • 38
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    Simplification of the wing-body interference problem. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 9; Oct. 197
    Format: text
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  • 39
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    Oblique shock-sound interaction at a freestream Mach number of about 20 in helium. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Detailed experimental measurements of the characteristics and level of pre- and postshock disturbances obtained for typical disturbance modes and shock angles are presented to aid in the evaluation of transition studies conducted in 'noisy' hypersonic wind tunnels. The presented data suggest that the shock is probably generating total temperature fluctuations in a fashion directly related to shock strength. Since in high supersonic and hypersonic flows the total temperature fluctuations are mainly contained in velocity fluctuations, it may be concluded that the predominant disturbances generated are vorticity as long as the postshock flow is at a sufficiently high Mach number.-
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Dec. 197
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  • 40
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    Turbulent bursts and rings on a cone in helium at Me = 7.6. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Review of data obtained on turbulent burst geometry and growth characteristics for cone boundary-layer transition in a helium wind tunnel at a boundary-layer edge Mach number (Me) of 7.6. Detailed data concerning turbulent spot geometry and downstream propagation velocities were obtained using a spark schlieren system with sequential spark capability. In one particular test evidence of a symmetrical turbulent burst ring was obtained; all other bursts developed in a singular random manner. Profiles of the apparent outer edges of the bursts were obtained, and the velocities of the leading and trailing edges of the bursts relative to the local velocity were determined. The velocities of the leading and trailing edges were found to be fairly consistent for each observation, with the leading edge of the burst traveling at about local edge velocity, while the trailing edge moved supersonically relative to local speed.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Oct. 197
    Format: text
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  • 41
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    Radiative and convective heating during Venus entry. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Determination of the stagnation region heating of probes entering the Venusian atmosphere. Both convective and radiative heat-transfer rates are predicted, and account is taken of the important effects of radiative transport in the vehicle shock layer. A nongray radiative transport model is utilized which parallels a four-band treatment previously developed for air (Page et al., 1969), but includes two additional bands to account for the important CO(4+) molecular band system. Some comparisons are made between results for Venus entry and results for earth entry obtained using a viscous earth entry program.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Oct. 197
    Format: text
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  • 42
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    Calculation of metric coefficients for streamline coordinates. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: A procedure is given for deriving the equations describing the surface streamline metric in a general form and in a form suitable for incorporation into computer codes to calculate an inviscid flow about three-dimensional bodies. Sample results are included to show the application of the metric in conjunction with an axisymmetric analog to predict heat transfer to a typical space shuttle orbiter.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Nov. 197
    Format: text
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  • 43
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    Secondary jet interaction with emphasis on outflow and jet location. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Data were obtained concerning a model which utilized a two-dimensional sonic jet. It was found that outflow and jet location significantly influence the magnitude and behavior of the secondary jet interaction forces. Continued refinements in jet interaction analyses which do not account for outflow are of limited usefulness in the design of control systems for supersonic and hypersonic vehicles. The jet total back pressure ratio increases with either jet pressure ratio or freestream Mach number.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 9; Nov. 197
    Format: text
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  • 44
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    B-70 Aircraft Study (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This volume contains cost, schedule, and technical information on the following B-70 aircraft subsystems: air induction system, flight control, personnel accommodation and escape, alighting and arresting, mission and traffic control, flight indication, test instrumentation, and installation, checkout, and pre-flight.
    Keywords: AERODYNAMICS
    Type: NASA-CR-115705 , SD-72-SH-0003-VOL-4 , NAS 1.26:115705 , JSC-CN-29834
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  • 45
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    B-70 Aircraft Study (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Volume 2 of the final report on the B-70 aircraft study is presented here. The B-70 Program, at the onset, was a full weapon system capable of sustained Mach 3 flight for the major portion of its design missions. The weapon system was to enter the SAC inventory as an RS-70 with the first intercontinental resonnaissance/bomber wing scheduled to go operational in July, 1964. After several redirections, a two XB-70 air vehicle program emerged with its prime objective being to demonstrate the technical feasibility of sustained Mach 3 flight. This section describes the original Weapon System 110A concepts, the evolution of the RS-70 design, and the XB-70 air vehicles which demonstrated the design, fabrication, and technical feasibility of long range Mach 3 flights at high altitude. The data presented shows that a very large step forward in the state-of-the-art of manned aircraft design was achieved during the B-70 development program and that advances were made and incorporated in every area, including design, materials application, and manufacturing techniques.
    Keywords: AERODYNAMICS
    Type: NASA-CR-115703 , SD-72-SH-0003-VOL-2 , NAS 1.26:115703 , JSC-CN-29832
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  • 46
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    B-70 Aircraft Study (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This Phase 2 final report for the B-70 aircraft study contains the data location matrix, which provides a summary of the major cost, schedule, and technical items provided in the report; work breakdown structure; cost definitions; and B-70 program level summary data. The Phase 2 objective was to provide the B-70 aircraft data in accordance with the approved study plan. Several minor modifications to the original plan have been made as the result of the Phase 2 effort.
    Keywords: AERODYNAMICS
    Type: NASA-CR-115702 , SD-72-SH-0003-VOL-1 , NAS 1.26:115702 , JSC-CN-29818
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  • 47
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    Wind-tunnel investigation at Mach numbers from 0.25 to 1.01 of a transport configuration designed to cruise at near-sonic speeds (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The results of the investigation showed that the configuration exhibits a sufficiently high drag divergence Mach number to cruise at near sonic speeds. The configuration is longitudinally stable through the cruise Mach number and lift coefficient range, but at higher lift coefficients displays pitchup and becomes unstable. The configuration was directionally stable at all test conditions and laterally stable in the angle of attack range required for cruise.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2622 , L-8226
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  • 48
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    Static aerodynamic characteristics of a model with a 17 percent thick supercritical wing (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The statis stability and control characteristics and air loads on the wing and aileron of a 0.09 scale model of an airplane with a 17 percent thick supercritical wing were investigated. The longitudinal aerodynamic characteristics were determined over a lift coefficient range sufficiently high to induce buffet onset at Mach numbers from 0.30 to 0.80. In addition, the lateral aerodynamic characteristics were determined as a function of sideslip angle and angle of attack at selected Mach numbers.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2551 , L-8081 , NAS 1.15:X-2551
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  • 49
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    Analysis and testing of stability augmentation systems (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Testing and evaluation of stability augmentation systems for aircraft flight control were conducted. The flutter suppression system analysis of a scale supersonic transport wing model is described. Mechanization of the flutter suppression system is reported. The ride control synthesis for the B-52 aeroelastic model is discussed. Model analyses were conducted using equations of motion generated from generalized mass and stiffness data.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132349 , D3-8884
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  • 50
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    Effects of increased leading-edge thickness on performance of a transonic rotor blade (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A single-stage transonic compressor was tested with two rotor blade leading-edge configurations to investigate the effect of increased leading-edge thickness on the performance of a transonic blade row. The original rotor blade configuration was modified by cutting back the leading edge sufficiently to double the blade leading-edge thickness and thus the blade gap blockage in the tip region. At design speed this modification resulted in a decrease in rotor overall peak efficiency of four points. The major portion of this decrement in rotor overall peak efficienty was attributed to the flow conditions in the outer 30 percent of the blade span. At 70 and 90 percent of design speed, the modification had very little effect on rotor overall performance.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7489 , E-7076
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  • 51
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    Multiple element airfoils optimized for maximum lift coefficient. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Optimum airfoils in the sense of maximum lift coefficient are obtained for incompressible fluid flow at large Reynolds number. The maximum lift coefficient is achieved by requiring that the turbulent skin friction be zero in the pressure rise region on the airfoil upper surface. Under this constraint, the pressure distribution is optimized. The optimum pressure distribution is a function of Reynolds number and the trailing edge velocity. Geometries of those airfoils which will generate these optimum pressure distributions are obtained using a direct-iterative method which is developed in this study. This method can be used to design airfoils consisting of any number of elements. Numerical examples of one- and two-element airfoils are given. The maximum lift coefficients obtained range from 2 to 2.5.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Dec. 197
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  • 52
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    Experimental aerodynamic characteristics of 120 deg included-angle cone with attached and separated 20 deg included-angle cone at Mach numbers of 2.36 and 2.70 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation has been conducted in a unitary plan wind tunnel to determine the aerodynamic characteristics of two different size blunt 120 deg-included-angle cones behind a 20 deg-included-angle cone. Forces and moments were measured at Mach numbers of 2.36 and 2.70, longitudinal separation distances from 0 to 3.5 body diameters, lateral (side) distances from 0 to 0.50 body diameter, angles of attack of the 120 deg-included-angle cone from 0.5 deg to 22 deg, angles of attack of the 20 deg-included-angle cone from 0 deg to 180 deg, and a Reynolds number of one million per foot. Large variations in pitching-moment, normal-force, and axial-force coefficients were noted for both Mach numbers and all longitudinal distances for the 120 deg cones in the wake of a 20 deg cone.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2603 , L-8424
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  • 53
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    A theory of supercritical wing sections, with computer programs and examples. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Mathematical methods for the design of supercritical wings, which depend on the numerical solution of the partial differential equations of two-dimensional gas dynamics, are developed. The main contribution is a computer program for the design of shockless transonic airfoils using the hodograph transformation and analytic continuation into the complex domain. The mathematical theory is described, and a manual for users of the programs is provided. Numerical examples are given and computational results are discussed, and the computer programs themselves are listed. The analysis routine can be used to ascertain whether the profiles behave well at off-design conditions, or to smooth coordinates and obtain a desirable shape more quickly when perfectly shockless flow is not essential.
    Keywords: AERODYNAMICS
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  • 54
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    Application of the leading edge suction analogy to prediction of longitudinal load distribution and pitching moments for sharp edged delta wings (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The leading-edge-suction analogy of Polhamus has been used to develop the longitudinal load distribution of the vortex lift for delta wings. This distribution is shown to be similar in shape to that of the potential-flow longitudinal loading for delta wings having aspect ratios of 2 or less. The totals of the two theoretical distributions for delta wings with an aspect ratio near 1 are in good agreement with the experimentally determined loadings over the angle-of-attack range from 0 to 30 deg. The corresponding predicted pitching moments show slightly more stability than those measured, because of loss of lift near the wing tips.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6994 , L-8224
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  • 55
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    An invariant second-order closure model of the compressible turbulent boundary layer on a flat plate (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The development of an invariant model designed expressly for the computation of shear flows is discussed. The model for incompressible layers seeks a second-order closure of the equations for the mean and fluctuating fields. The development of a method for computing the behavior of shear layers in compressible forces is described. The complexity of the analysis is restrained by limiting the consideration to a flat plate boundary layer where the mean pressure can be taken to be constant.
    Keywords: AERODYNAMICS
    Type: NASA-CR-128172
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  • 56
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    Supersonic aerodynamic characteristics of a lifting-body orbiter model with a blunted delta planform at Mach 2.30 to 4.60 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation has been made in the Langley Unitary Plan wind tunnel to determine the aerodynamic characteristics of a lifting-body orbiter model with a blunted delta planform. The model was tested at Mach numbers from 2.30 to 4.60, at nominal angles of attack from -4 deg to 60 deg and angles of sideslip from -4 deg to 10 deg, and at a Reynolds number of 2.5 million per foot.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2581 , L-8366
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  • 57
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    Aerodynamic effects of leading-edge serrations on a two-dimensional airfoil (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was conducted to determine the flow field and aerodynamic effects of leading-edge serrations on a two-dimensional airfoil at a Mach number of 0.13. The model was a NACA 66-012 airfoil section with a 0.76 m (30 in.) chord, 1.02 m (40 in.) span, and floor and end plates. It was mounted in the Ames 7- by 10-Foot Wind Tunnel. Serrated brass strips of various sizes and shapes were attached to the model in the region of the leading edge. Force and moment data, and photographs of tuft patterns and of oil flow patterns are presented. Results indicated that the smaller serrations, when properly placed on the airfoil, created vortices that increased maximum lift and angle of attack for maximum lift. The drag of the airfoil was not increased by these serrations at airfoil angles of attack near zero and was decreased at large angles of attack. Important parameters were serration size, position on the airfoil, and spacing between serrations.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2643 , A-3706
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  • 58
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    Supersonic aerodynamic characteristics of a two-staged space-shuttle model having a delta-wing orbiter mated atop a winged booster (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation has been conducted in the Langley Unitary Plan wind tunnel to determine the static aerodynamic characteristics of a two-staged space-shuttle system consisting of a delta-wing orbiter mated atop a winged booster. The tests were performed at Mach numbers from 2.30 to 4.60 at a Reynolds number of one million per foot.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2569 , L-8300
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  • 59
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    Effect of configuration modification on the hypersonic aerodynamic characteristics of a blended delta wing-body entry vehicle (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The longitudinal, lateral, and directional aerodynamic characteristics of a delta-wing configuration were obtained experimentally at Mach 20 in helium with Reynolds numbers, based on model length, of 1.5 million and 2.9 million and at a Mach number of 6 in air with a Reynolds number, based on model length, of 4.8 million. The angles of attack varied from 0 deg to 55 deg for two sideslip angles. The effects of the addition of dorsal fins, the removal of wing tip fins, an increase in elevon span, and changes in elevon hinge-line sweep angle are discussed. The unmodified vehicle had a maximum lift-drag ratio of 2.1 at Mach 19 and of 2.4 at Mach 6 with about the same lateral and directional stability level at both Mach numbers. As the Mach number increased from 6 to 20, the longitudinal center of pressure moved forward and more positive elevon deflection was therefore required to maintain a given trim angle. The removal of wing tip fins increased the maximum lift-drag ratio and had a negligible effect on longitudinal stability, but caused directional instability that was not corrected by the dorsal fins examined. The shape of the wing and elevon hinge-line sweep had a large influence on the induced yawing moment due to roll control.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2611 , L-8419
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  • 60
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    Analytical study of effect of casing treatment on performance of a multistage compressor (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The simulation was based on individual stage pressure and efficiency maps. These maps were modified to account for casing treatment effects on the individual stage characteristics. The individual stage maps effects on overall compressor performance were observed. The results show that to improve the performance of the compressor in its normal operating range, casing treatment of the rear stages is required.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6917 , E-6920
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  • 61
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    Calculative techniques for transonic flows about certain classes of wing body combinations (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Procedures based on the method of local linearization and transonic equivalence rule were developed for predicting properties of transonic flows about certain classes of wing-body combinations. The procedures are applicable to transonic flows with free stream Mach number in the ranges near one, below the lower critical and above the upper critical. Theoretical results are presented for surface and flow field pressure distributions for both lifting and nonlifting situations.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2103
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  • 62
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    Experimental damping-in-pitch of two slender cones at Mach 2 and incidences up to 30 deg (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Oscillatory experiments were performed on two slender cones at Mach 2 and incidences up to 30 deg, using three different experimental arrangements. The damping-in-pitch was found to remain constant at incidences of up to a value approximately corresponding to the cone semi-angle, after which an almost linear increase with incidence was noted. The results obtained with the different techniques were in very good agreement up to an incidence of 15 deg and in some cases up to 25 deg.
    Keywords: AERODYNAMICS
    Type: NASA-CR-114483 , LTR-UA-19
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  • 63
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    Numerical calculation of boundary-induced interference in slotted or perforated wind tunnels including viscous effects in slots (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A numerical method is presented for calculating the incompressible boundary-induced interference in wind tunnels of rectangular cross section with slotted or perforated walls. The method includes a wall representation which is capable of satisfying a generalized homogeneous boundary condition including the effects of viscosity within the slots. The effects of viscosity in the slots are found to be very significant. The method allows for a variation in the boundary conditions along the tunnel walls. The model can be any configuration and can be located anywhere in the test section. The interference can be computed at any point in the test section.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6871 , L-8349
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  • 64
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    Low speed aerodynamic characteristics of a large scale model with a thin, highly swept, 2.67 aspect ratio wing having a cranked leading edge (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The low speed aerodynamic characteristics of a large-scale model intended to represent advanced fixed-wing fighters have been investigated in the Ames 40 by 80 foot wind tunnel. The model possessed positive static longitudinal stability to nearly 28 deg angle of attack, the maximum tested, both with and without leading-edge flaps deflected. Lateral control with differentially deflected ailerons and a right wing spoiler simultaneously deployed as combined controls was only slightly greater than that with the differentially deflected ailerons deployed as a separate control without the spoiler. Measured lift and drag were in close agreement with that predicted by theory to about 14 deg angle of attack, including the prediction of lift due to 30 deg of trailing edge flap deflection. Estimated takeoff performance of an aircraft 4/3 the scale of the test model showed takeoff distances of less than 2000 ft.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6919 , A-3893
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  • 65
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    Wind tunnel investigation of aerodynamic characteristics of scale models of three rectangular shaped cargo containers (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Wind tunnel tests were conducted on scale models of three rectangular shaped cargo containers to determine the aerodynamic characteristics of these typical externally-suspended helicopter cargo configurations. Tests were made over a large range of pitch and yaw attitudes at a nominal Reynolds number per unit length of 1.8 x one million. The aerodynamic data obtained from the tests are presented.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-62169
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  • 66
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    Analysis and testing of high entrainment single nozzle jet pumps with variable mixing tubes (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analytical model was developed to predict the performance characteristics of axisymmetric single-nozzle jet pumps with variable area mixing tubes. The primary flow may be subsonic or supersonic. The computer program uses integral techniques to calculate the velocity profiles and the wall static pressures that result from the mixing of the supersonic primary jet and the subsonic secondary flow. An experimental program was conducted to measure mixing tube wall static pressure variations, velocity profiles, and temperature profiles in a variable area mixing tube with a supersonic primary jet. Static pressure variations were measured at four different secondary flow rates. These test results were used to evaluate the analytical model. The analytical results compared well to the experimental data. Therefore, the analysis is believed to be ready for use to relate jet pump performance characteristics to mixing tube design.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2067
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  • 67
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    FORTRAN program for calculating total efficiency - specific speed characteristics of centrifugal compressors (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program for predicting design point specific speed - efficiency characteristics of centrifugal compressors is presented with instructions for its use. The method permits rapid selection of compressor geometry that yields maximum total efficiency for a particular application. A numerical example is included to demonstrate the selection procedure.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2594 , E-6884
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  • 68
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    Experimental investigation of stability and stall flutter of a free-floating wing V/STOL model (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation was made of the static and dynamic stability characteristics of a one-fourth scale model of a tilt-propeller free-wing V/STOL aircraft. The effects of wing pivot location, wing chord, trailing-edge angle, propeller tilt angle, and thrust were studied, and a limited evaluation was made of high-lift devices. A dynamically similar wing was used to measure frequency and damping ratio from transient response data in the linear aerodynamic regime and the results were compared to quasi-steady and unsteady aerodynamic theory. It was found that at high trim angles of attack, in the nonlinear aerodynamic regime, stall flutter oscillations occurred with typical amplitudes ranging from 15 to 20 deg. Wing control tab deflection was effective in initiating and terminating stall flutter but variations in configuration or operating conditions did not greatly influence the occurrence of characteristics of the oscillations.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6831 , A-4088
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  • 69
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    A review of sphere drag coefficients applicable to atmospheric density sensing (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A comprehensive search has been performed on the drag coefficient of spheres in the Reynolds number range from 50 to 50,000 and for Mach numbers up to 5. This Reynolds-Mach number range corresponds to the range of interest in the falling sphere technique of atmospheric sensing. In this technique, the knowledge of the sphere's trajectory and its aerodynamic characteristics are utilized to obtain the density of the atmosphere. Presently available data have been collected and analyzed as to their validity and applicability to atmospheric density measurements. A new drag table is recommended for use in these measurements.
    Keywords: AERODYNAMICS
    Type: NASA-CR-126742 , NOLTR-72-34
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  • 70
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    Prediction of unsteady aerodynamic loadings caused by trailing edge control surface motions in subsonic compressible flow: Analysis and results (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A theoretical analysis and a computer program have been developed for the prediction of unsteady lifting surface loadings caused by motions of trailing edge control surfaces having sealed gaps. The final form of the downwash integral equation has been formulated by isolating the singularities from the non-singular terms and establishing a preferred solution process to remove and evaluate the downwash discontinuities in a systematic manner. Comparisons of theoretical and experimental pressure data are made for several control surface configurations. The comparisons indicate that reasonably accurate theoretical pressure distributions and generalized forces may be obtained for a wide variety of control surface configurations. Spanwise symmetry or antisymmetry of motion, and up to four control surfaces on each half span can be accommodated.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2003
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  • 71
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    Safe atmosphere entry of an isotope heat source with a single stable trim attitude at hypersonic speeds (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A theoretical investigation has been made to design an isotope heat source capable of satisfying the conflicting thermal requirements of steady-state operation and atmosphere entry. The isotope heat source must transfer heat efficiently to a heat exchange during normal operation with a power system in space, and in the event of a mission abort, it must survive the thermal environment of atmosphere entry and ground impact without releasing radioactive material. A successful design requires a compatible integration of the internal components of the heat source with the external aerodynamic shape. To this end, configurational, aerodynamic, motion, and thermal analyses were coupled and iterated during atmosphere entries at suborbital through superorbital velocities at very shallow and very steep entry angles. Results indicate that both thermal requirements can be satisfied by a heat source which has a single stable aerodynamic orientation at hypersonic speeds. For such a design, the insulation material required to adequately protect the isotope fuel from entry heating need extend only half way around the fuel capsule on the aerodynamically stable (wind-ward) side of the heat source. Thus, a low-thermal-resistance, conducting heat path is provided on the opposite side of the heat source through which heat can be transferred to an adjacent heat exchanger during normal operation without exceeding specified temperature limits.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6833 , A-4342
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  • 72
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    Flight testing techniques for the evaluation of light aircraft stability derivatives: A review and analysis (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Techniques quoted in the literature for the extraction of stability derivative information from flight test records are reviewed. A recent technique developed at NASA's Langley Research Center was regarded as the most productive yet developed. Results of tests of the sensitivity of this procedure to various types of data noise and to the accuracy of the estimated values of the derivatives are reported. Computer programs for providing these initial estimates are given. The literature review also includes a discussion of flight test measuring techniques, instrumentation, and piloting techniques.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2016
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  • 73
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    Boundary layer stability on a yawed spinning body of revolution and its effect on the magnus force and moment (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The parameters are established which are important to the stability of a boundary layer flow over a yawed spinning cylinder in a uniform stream. It is shown that transition occurs asymmetrically in general and this asymmetry can be important for the prediction of aerodynamic forces and moments (e.g., the Magnus effect). Instability of the steady-state boundary layer flow is determined using small disturbance theory. Although the approach is strictly valid only for the calculation of the conditions for stability in the small, experimental data indicate that in many problems, it provides a good estimate for the transition to turbulence.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2060 , AEEP-4089-101-71U
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  • 74
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    Normal impingement loads due to small air jets issuing from a base plate and reflecting off a platform for various jet Mach numbers, separation distances, and ambient pressures (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was conducted in a 12.5-meter-diameter vacuum sphere to determine the impingement loads due to air jets issuing from and perpendicular to a circular base and reflecting off a square platform, that is, a simulation of rendezvous maneuvering, docking, launch, impact dampers etc. The nozzles had exit Mach numbers of 1, 3, 5, and 7. The ambient pressures were 0.0006, 5, 225, and 760 torr. Under near-field separation distances and at 0.0006 torr, reflections were significant; and ratios of the impingement force to thrust on both plates in the biplane arrangement varied from about 750 for exit Mach number 1 to 120 for exit Mach number 7. The far-field force ratios were near unity for the platform and zero for the base and indicated few, if any, reflections. Some reversals and rapid changes in loads were obtained at transition distances between the near and far fields. In general, increasing the exit Mach number or ambient pressure reduced the impingement loads.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6817 , L-8356
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  • 75
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    Calculation of laminar heat transfer to the windward surfaces of straight wing shuttle vehicles at high angle of attack and with yaw (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Calculations of laminar heat transfer to windward wing and body surfaces of a straight wing MSC orbiter have been made at high angles of attack and with yaw. The predictions of heat transfer made by swept cylinder theory generally agree with measurements in areas free of external flow interference. An optimum elliptic cross section was then determined using swept cylinder theory for an aerodynamically heated windward body surface in radiation equilibrium.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6614 , A-4196
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  • 76
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    Effects of body shape on the aerodynamic characteristics of an all-body hypersonic aircraft configuration at Mach numbers from 0.65 to 10.6 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation was conducted to determine the effects of several variations in body shape on the aerodynamic characteristics of an all-body hypersonic aircraft configuration. The basic configuration had a delta planform with an elliptic cone forebody and an afterbody of elliptic cross section terminating in a straight-line trailing edge. Variations in body shape included the ratio of maximum cross-sectional to body planform area, body leading-edge sweep, and forebody length ratio. In addition, the effects of a thin wing mounted on one of the bodies was investigated, and the aerodynamic characteristics of just the forebodies of two of the configurations were determined. The models had no stabilizing surfaces or propulsion system packages. Ranges of angle of attack (-4 deg to +15 deg) and angle of sideslip (-4 deg to +8 deg) were investigated. Of the four complete bodies, the configuration with the lowest ratio of cross-sectional to body planform area had the highest maximum lift-drag ratio and the greatest level of longitudinal stability at most Mach numbers. All the configurations had positive longitudinal stability near maximum lift-drag ratio at most Mach numbers. With exception of the lowest subsonic Mach numbers, changes in body sweep angle and in forebody length ratio had only minor effects on maximum lift-drag ratio.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6821 , A-4297
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  • 77
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    Wind tunnel test data for wing trailing vortex flow survey (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Data are presented on velocity measurements made with hot wire anemometers in the wake of a model of the CV-990 aircraft and a rectangular wing in the NASA-Ames 2.14x3.05 meter (7- by 10-foot) wind tunnels. Variables included angle of attack, tunnel speed and axial distance up to 12 chord lengths downstream from the wing trailing edge. Effects of deflecting trailing edge flaps and small spoiler panels are shown.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-62148
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  • 78
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    Experimental investigation of hypersonic buzz on a high cross-range shuttle configuration (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A wind tunnel investigation has been conducted to determine the nature of an unsteady hypersonic flow phenomenon, often referred to as hypersonic buzz, on a 1:100 scale model representative of a high cross-range shuttle configuration. The tests, conducted in helium at a nominal Mach number of 17.5, were specifically directed at obtaining a better understanding of the character of the hypersonic flow field in the vicinity of a deflected control surface. Power spectral densities and root mean squared values of surface pressure fluctuations are presented along with observations made from high speed motion pictures, schlieren and oil flow photographs. Flap deflections of 0, 20, 30, 35, 40 and 60 deg were tested at various angles of attack from 0 deg to 37 deg. It is quite clear from these tests that, under certain conditions, extremely unstable hypersonic flow patterns are formed.
    Keywords: AERODYNAMICS
    Type: NASA-CR-112053 , RIAS-TR-72-05C
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  • 79
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    The role of fluctuating forces in the generation of compressor noise (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of a theoretical and experimental study on the role of aerodynamically-induced fluctuating forces in the sound generation by axial-flow compressors are presented. Analytical models for the generation and radiation of sound by rotor/stator combinations were developed. For the experimental substantiation of the analytical results, the technology was developed to measure fluctuating forces directly on rotating airfoils using miniature differential-pressure sensors and FM telemetry. Under the assumption of full coherence of the force field on the blade, radiated sound power was predicted from the force measurements on blades and compared with measured sound power. Both broadband radiation from a single rotating airfoil and discrete frequency radiation due to interaction of multi-bladed stator/rotor configurations were investigated. The results indicate the necessity to obtain information on the details of the force field for accurate prediction of the radiated sound spectrum.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2012 , REPT-2160
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  • 80
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    Effects of casing boundary-layer removal on noise of a turbofan rotor (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effect of casing boundary-layer removal on noise produced by a turbofan rotor was measured. The outlet guide vanes were removed for these tests. A comparison was made between the noise measurements when the boundary layer was bled off and under zero bleed conditions. When the boundary layer was removed, overall sound pressure level was reduced 2 dB with moderate blade loading and 3 dB with heavier blade loading. An analysis of the changes in the spectral density with bleed is presented.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6763 , E-6727
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  • 81
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    Effect of transient winds on the flow quality of an open-circuit wind-tunnel model (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effect of a transient wind on the test-section flow quality of an open-circuit wind tunnel was investigated experimentally. The investigation was restricted to transient wind effects associated with the inlet. A small open-circuit wind tunnel was placed outside in the real wind environment. Test-section speed and angularity as well as wind speed and direction was measured by high-response instrumentation. The inlet configuration was varied with a set of screens, a removable honeycomb, and a removable inlet lip. Acceptable flow was obtained at all wind angles and for wind- to test-section-velocity ratios up to 0.4 with an inlet configuration having five screens, a honeycomb, and a lip. With inlet configurations sensitive to winds, a transient wind parallel to the tunnel axis produced local fluctuations in test-section speed and angularity; however, oscillation of the average test-section speed was not evident. The effect of wind direction was negligible up to wind angles of 45 deg relative to the tunnel axis. At larger wind angles, flow distortions occurred primarily on the windward side of the test section.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2538 , E-6773
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  • 82
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    A study analysis of cable-body systems totally immersed in a fluid stream (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A general stability analysis of a cable-body system immersed in a fluid stream is presented. The analytical portion of this analysis treats the system as being essentially a cable problem, with the body dynamics giving the end conditions. The mathematical form of the analysis consists of partial differential wave equations, with the end and auxiliary conditions being determined from the body equations of motion. The equations uncouple to give a lateral problem and a longitudinal problem as in first order airplane dynamics. A series of tests on a tethered wind tunnel model provide a comparison of the theory with experiment.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2021 , SUDAAR-411
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  • 83
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    Subsonic pressure distributions around a solid model of an inflatable decelerator attached to the base of an ogive-cylinder (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A wind-tunnel investigation was conducted at free-stream Mach numbers from 0.20 to 1.00 and corresponding Reynolds numbers, based on maximum afterbody diameter, from 2.25 x one million to 6.90 x one million on a solid model of an attached inflatable decelerator (AID) connected to the base of an ogive-cylinder. Tests were conducted to obtain ram-air and surface pressure distributions about the AID. AID shapes derived for subsonic deployment are dependent on the pressure distributions used in their derivation, and the different shapes obtained are dependent on the Mach number for which the design is made. The resulting pressure distributions were used in a design program to obtain new shapes which were compared with the original pressure-distribution shape.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2535 , L-8188
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  • 84
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    Effect of wing design on the longitudinal aerodynamic characteristics of a wing-body model at subsonic speeds (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation has been conducted to determine the effects of wing camber and twist on the longitudinal aerodynamic characteristics of a wingbody configuration. Three wings were used each having the same planform (aspect ratio of 2.5 and leading-edge sweep angle of 44 deg.) but differing in amounts of camber and twist (wing design lift coefficient). The wing design lift coefficients were 0, 0.35, and 0.70. The investigation was conducted over a Mach number range from 0.20 to 0.70 at angles of attack up to about 22 deg. The effect of wing strakes on the aerodynamic characteristics of the cambered wings was also studied. A comparison of the experimentally determined aerodynamic characteristics with theoretical estimates is also included.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7099 , L-8562
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  • 85
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    Gas crossflow effects on airflow through a wire-form transpiration cooling material (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental analysis was conducted to determine the effects of gas stream flow parallel to the discharging surface on the flow characteristics of a wire-form porous material. Flow data were obtained over a range of transpiration airflow rates from 0.129 to 0.695/grams per second-centimeter squared and external gas stream Mach numbers from 0 to 0.46. The conclusion was drawn that the flow characteristics of the wire cloth were not significantly affected by the external gas flows.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2687 , E-7147
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  • 86
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    Effects of wing-pivot location and forewing configuration on the low-speed aerodynamic characteristics of a variable-sweep airplane model (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation has been made to determine the effects of the location of the wing pivot and geometry of the forewing on the static longitudinal aerodynamic characteristics at subsonic speeds of a model representing a variable-sweep supersonic fighter airplane. Results indicate that as the wing-pivot location moves aft and outboard, the change in static margin due to wing sweep is reduced. Increasing the forewing area resulted in a forward shift of the aerodynamic center as well as a slight reduction in the aerodynamic-center variation due to wing sweep.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2674 , L-8026
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  • 87
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    Effect of nozzle lateral spacing on afterbody drag and performance of twin-jet afterbody models with convergent-divergent nozzles at Mach numbers up to 2.2 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Twin-jet afterbody models were investigated by using two balances to measure the thrust-minus-total drag and the afterbody drag, separately, at static conditions and at Mach numbers up to 2.2 for an angle of attack of 0 deg. Hinged-flap convergent-divergent nozzles were tested at subsonic-cruise- and maximum-afterburning-power settings with a high-pressure air system used to provide jet-total-pressure ratios up to 20. Two nozzle lateral spacings were studied, using afterbodies with similar interfairing shapes but with different longitudinal cross-sectional area distributions. Alternate, blunter, interfairings with different shapes for the two spacings, which produced afterbodies having identical cross-sectional area progressions corresponding to an axisymmetric minimum wave-drag configuration, were also tested. The results indicate that the wide-spaced configurations improved the flow field around the nozzles, thereby reducing drag on the cruise nozzles; however, the increased surface and projected cross-sectional areas caused an increase in afterbody drag. Except for a slight advantage with cruise nozzles at subsonic speeds, the wide-spaced configurations had the higher total drag at all other test conditions.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2601 , L-8338
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  • 88
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    Asymmetric lateral-directional characteristics of pointed bodies of revolution at high angles of attack (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A low-speed wind-tunnel investigation was conducted in order to determine the cause of asymmetric yawing moments produced by long pointed fuselage nose shapes at high angles of attack. Force tests were conducted with a cone, tangent-ogive model, and a paraboloid of revolution over a range of Reynolds numbers from 0.15 million to 0.35 million for an angle-of-attack range from 0 deg to 75 deg and an angle-of-sideslip range of plus or minus 30 deg. Tuft and smoke flow-visualization tests were also conducted to aid in the analysis. Large asymmetric yawing moments were obtained for the cone and tangent-ogive body at high angles of attack (of the order of 40 to 60 deg). These large moments were caused by asymmetric shedding of vortex sheets off the long pointed nose. The asymmetric moments could be eliminated by use of symmetrically arranged strikes on the nose. The paraboloid of revolution did not produce a strong asymmetric flow field at high angles of attack and did not exhibit asymmetric moments.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7095 , L-8582
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  • 89
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    Aerodynamic characteristic of a swept-wing cruise missile at Mach numbers from 0.50 to 2.86 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation has been made in the Mach number range from 0.50 to 2.86 to determine the longitudinal and lateral aerodynamic characteristics of a cruise missile having a 58 deg swept wing and conventional aft tails. Such a vehicle might be applicable to missions such as surface- or air-launched tactical or strategic missiles, unmanned reconnaissance, or countermeasure decoys.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7069 , L-8508
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  • 90
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    Mach reflection from overexpanded nozzle flows. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Investigation of the Mach reflection associated with a steady two-dimensional overexpanded nozzle flow. The conditions of occurrence of triple point shock configuration are described, and Mach reflection configurations for two values of the incident shock are presented, along with the Mach stem height variation for different Mach numbers under conditions of different pressure ratios.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Sept
    Format: text
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  • 91
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    Analysis and testing of compressible flow ejectors with variable area mixing tubes. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: An analytical model has been developed to predict the flow behavior within axisymmetric single-nozzle ejectors employing variable-area mixing tubes. The primary flow may be supersonic or subsonic and may have a different stagnation temperature from the subsonic secondary flow. Tests were performed on an ejector with an 800 F supersonic (M = 2.72) primary jet to evaluate the analytical model. Measured velocity profiles, temperature profiles, and wall static pressure distributions are presented and compared to the analytical predictions. Agreement is generally good.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 72-FE-14
    Format: text
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  • 92
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    Noise field of a supersonic Mach 1.5 cold model jet. (1972)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Systematic surveys of both the near and far noise fields were made for a supersonic (nozzle design Mach number 1.5) cold model jet. The purpose of this investigation was to extend the existing understanding of the noise field of a supersonic shock-free jet at a moderate exit Mach number and the variations in its acoustic behavior when the nozzle was operated at its underexpanded mode, where strong shock waves were present. It was found that the broad-band pressure spectra of apparent sources in each of the individual characteristic flow regions were grossly similar. The strongest source for the shock-free jet was located in the region between the laminar core tip and the supersonic core tip, whereas for the underexpanded jet the strongest source was found near the middle of the flow region containing repetitive shock waves. It is shown that the significant increase in the noise output at the underexpanded mode of operation was primarily due to high-frequency components.
    Keywords: AERODYNAMICS
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  • 93
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    Method of characteristics for supersonic flow of a guiding centre plasma. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A study of the compressive magneto-acousic waves in a guiding centre plasma shows that the wavefront that emerges point disturbance after a finite time is a simple oblate spheroid with the axis of revolution parallel to the field lines. Thus, in a steady three-dimensional supersonic flow of guiding centre plasma a simple analytic exprencan be obtained to represent the characteristic surfaces. From a proper linear combination of the governing macroscopic equations, the characteristic equation is obtained. It represents the propagation of disturbances on the characteristic surface. The characteristic theory can be used to study the interaction of the solar wind with the moon and possibly with other planetary bodies.
    Keywords: AERODYNAMICS
    Type: Journal of Plasma Physics; 7; Feb. 197
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  • 94
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    Nonlinear actuator disk theory. (1972)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Results obtained from a recent investigation of the flowfield induced by a heavily loaded actuator disk. First, the governing nonlinear integral equations are formulated from two different points of view, and the iterative solution is briefly outlined. Calculated flow patterns are presented for representative advance ratios and blade circulation distributions. For the static condition, the experimentally observed lingering of the tip vortices in the propeller plane, and the insensitivity of the streamline pattern to thrust coefficient are both accounted for, and a 'dividing streamline' - apparently not previously discussed in the literature, is predicted for the nonstatic case. Finally, the relationship between the actuator disk flow and the zero harmonic of the flowfield induced by a finite-bladed propeller is considered.
    Keywords: AERODYNAMICS
    Type: Zeitschrift fuer Flugwissenschaften; 20; Mar. 197
    Format: text
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  • 95
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    Effects of leading-edge camber on low-speed characteristics of slender delta wings (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Wind-tunnel studies have been conducted to determine the effects of leading-edge camber on the low-speed aerodynamic characteristics of a thin, sharp-edge 74 deg delta wing. The results include force and moment measurements, pressure distributions, and flow visualization patterns determined from oil flow, tuft and water vapor observations. The study indicated that leading-edge camber near the apex is effective in controlling the pitch-up tendency of slender delta wings.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2002
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  • 96
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    Spherical balloon response to three-dimensional time-dependent flows (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The concept of the Lagrangian displacement of a balloon is introduced. It is shown that the general balloon response problem is extremely complicated because the wind-forcing functions in the balloon equations of motion are functions of the wind velocity vector and its Eulerian first derivatives evaluated at the location of the balloon. The linear perturbation equations for a spherical balloon are derived by perturbing the components of velocity of the balloon about a terminal velocity state which is in equilibrium with a space-time invariant mean horizontal flow. The atmospheric flow is also perturbed such that the resulting equations can be used to analyze the responses of spherical balloons to three-dimensional time-dependent flows. The wind field is represented in terms of a four-fold Fourier integral that involves three orthogonal wave numbers and a frequency, while the balloon components of velocity are represented as Fourier integrals involving a frequency which, in turn, is a function of the wind field wave numbers and frequency and the unperturbed flow components of velocity.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6829 , M-188
    Format: application/pdf
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  • 97
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    Hypersonic and transonic buzz measurements on the lower pitch flap of the M2-F2 lifting entry configuration (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Free-oscillation damping measurements at hypersonic and transonic Mach numbers are presented for the lower pitch flap of the M2-F2 reentry vehicle. For the flow and model conditions tested, the damping measurements indicate the absence of hypersonic buzz instability for flap rotation frequencies of 47.3 Hz, 153 Hz, and 360 Hz, the presence of transonic buzz for 47.3 Hz flap, and the absence of transonic buzz for a 115 Hz flap. There are not enough flap damping data for an error estimate based on repeatability, but a partial damping calibration is presented in which an analog computer simulation of random flap response for a known flap damping is fed into the autocorrelation computer and filter combination used for most of the damping measurements.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6799 , A-3790
    Format: application/pdf
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  • 98
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    Performance of a 1380-foot-per-second-tip-speed axial-flow compressor rotor with a blade tip solidity of 1.3 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Aerodynamic design parameters are presented along the overall and blade element performance, of an axial flow compressor rotor designed to study the effects of blade solidity on efficiency and stall margin. At design speed the peak efficiency was 0.844 and occurred at an equivalent weight flow of 63.5 lb/sec with a total pressure ratio of 1.801. Design efficiency, pressure ratio, and weight flow 0.814, 1.65, and 65.3(41.1 lb/sec/sq ft of annulus area), respectively. Stall margin for design speed was 6.4 percent based on the weight flow and pressure ratio values at peak efficiency and just prior to stall.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2448 , E-6503
    Format: application/pdf
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  • 99
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    A parametric study of planform and aeroelastic effects on aerodynamic center, alpha- and q- stability derivatives. Appendix D: Procedures used to determine the mass distribution for idealized low aspect ratio two spar fighter wings (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The procedures used to establish the mass matrices characteristics for the fighter type wings studied are given. A description of the procedure used to find the mass associated with a specific aerodynamic panel is presented and some examples of the application of the procedure are included.
    Keywords: AERODYNAMICS
    Type: NASA-CR-112232 , CRINC-FRL-72-014-APP-D
    Format: application/pdf
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  • 100
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    A parametric study of planform and aeroelastic effects on aerodynamic center, alpha- and q- stability derivatives. Appendix C: Method for computing the aerodynamic influence coefficient matrix of nonplanar wing-body-tail configurations (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Expressions are derived for computing the aerodynamic influence coefficient matrix for nonplanar wing-body-tail configurations. An aerodynamic influence coefficient is defined as the load in lbs. induced on a panel as a result of a unit angle of attack on another panel. Fuselage, wing and tail thickness are assumed to be small with the result that the thickness effect on the flow-field is negligible. The method for determining the aerodynamic influence coefficient matrix is based on the lifting solution to the small perturbation, steady potential flow equation.
    Keywords: AERODYNAMICS
    Type: NASA-CR-112231 , CRINC-FRL-72-013-APP-C
    Format: application/pdf
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