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  • AERODYNAMICS  (460)
  • 1985-1989
  • 1975-1979  (460)
  • 1940-1944
  • 1925-1929
  • 1976  (460)
  • 1
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    Inviscid transonic flow computations with shock fitting (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: First- and second-order numerical procedures for calculating two-dimensional transonic flows that treat shock waves as discontinuities are discussed. This short communication illustrates their application to a simple but non-trivial problem for which there are limited theoretical results.
    Keywords: AERODYNAMICS
    Type: Symposium Transsonicum II; Sep 08, 1975 - Sep 13, 1975; Goettingen
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Pressure distribution on a 1- by 3-meter semispan wing at sweep angles from 0 deg to 40 deg in subsonic flow (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A 1- by 3-meter semispan wing of taper ratio 1.0 with NACA 0012 airfoil section contours was tested in the Langley V/STOL tunnel to measure the pressure distribution at five sweep angles, 0 deg, 10 deg, 20 deg, 30 deg, and 40 deg, through an angle-of-attack range from -6 deg to 20 deg. The pressure data are presented as plots of pressure coefficients at each static-pressure tap location on the wing. Flow visualization wing-tuft photographs are also presented for a wing of 40 deg sweep. A comparison between theory and experiment using two inviscid theories and a viscous theory shows good agreement for pressure distributions, normal forces, and pitching moments for the wing at 0 deg sweep.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-8307 , L-10969
    Format: application/pdf
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  • 3
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    Correlation of full-scale helicopter rotor performance in air with model-scale Freon data (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was conducted in a transonic dynamics tunnel to measure the performance of a 1/5 scale model helicopter rotor in a Freon atmosphere. Comparisons were made between these data and full scale data obtained in air. Both the model and full scale tests were conducted at advance ratios between 0.30 and 0.40 and advancing tip Mach numbers between 0.79 and 0.95. Results show that correlation of model scale rotor performance data obtained in Freon with full scale rotor performance data in air is good with regard to data trends. Mach number effects were found to be essentially the same for the model rotor performance data obtained in Freon and the full scale rotor performance data obtained in air. It was determined that Reynolds number effects may be of the same magnitude or smaller than rotor solidity effects or blade elastic modeling in rotor aerodynamic performance testing.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-8323 , L-10844
    Format: application/pdf
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  • 4
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    A numerical study of viscous flow around an airfoil (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An integrodifferential method, previously formulated in terms of velocity and vorticity vectors, is reformulated in terms of stream function and vorticity for two-dimensional incompressible viscous flows. The reformulated integrodifferential method is shown to retain the distinguishing feature of the previous formulation in permitting the confinement of the solution field to the viscous region of the flow and consequently offers great computational advantages. The application of this procedure in a study of an incompressible flow around an impulsively started 9% thick symmetric Joukowski airfoil at an angle of attack of 15 deg and a Reynolds number of 1000 is discussed. Numerical results are presented and compared with available finite-difference results.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 76-337 , Fluid and Plasma Dynamics Conference; Jul 14, 1976 - Jul 16, 1976; San Diego, CA
    Format: text
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  • 5
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    An experimental investigation of a two and a three-dimensional low speed turbulent boundary layer (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental studies of a two and a three-dimensional low speed turbulent boundary layer were conducted on the side wall of a boundary layer wind tunnel. The 20 ft. long test section, with a rectangular cross section measuring 17.5 in. x 46 in., produced a 3.5 in. thick turbulent boundary layer at a free stream Reynolds number. The three-dimensional turbulent boundary layer was produced by a 30 deg swept wing-like model faired into the side wall of the test section. Preliminary studies in the two-dimensional boundary layer indicated that the flow was nonuniform on the 46 in. wide test wall. The nonuniform boundary layer is characterized by transverse variations in the wall shear stress and is primarily caused by nonuniformities in the inlet damping screens.
    Keywords: AERODYNAMICS
    Type: NASA-CR-153244 , TR-AE-76-2
    Format: application/pdf
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  • 6
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    Acoustic-loads research for powered-lift configurations (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Data presented from large-scale model tests with jet engines having thrusts of 9 kN (2000 lb) and 36 kN (8000 lb) include acoustic loads for an externally blown wing and flap induced by a TF34 jet engine, an upper surface blown (USB) aircraft model in a wind tunnel, and two USB models in static tests. Comparisons of these results with results from acoustic loads studies on configurations of other sizes are made and the implications of these results on interior noise and acoustic fatigue are discussed.
    Keywords: AERODYNAMICS
    Type: Powered-Lift Aerodyn. and Acoustics; p 429-443
    Format: application/pdf
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  • 7
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    Wind shear and turbulence around airports (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A two part study was conducted to determine the feasibility of predicting the conditions under which wind/turbulence environments hazardous to aviation operations exist. The computer model used to solve the velocity temperature, and turbulence distributions in the atmospheric boundary layer is described, and the results of a parameteric analysis to determine the expected range of wind shear and turbulence to be encountered in the vicinity of airports are given. The second part describes the delineation of an ensemble of aircraft accidents in which low level wind shear and/or turbulence appeared to be causative factors. This set of accidents, encompassing a wide range of meteorological conditions, should prove useful in developing techniques for reconstructing hazardous wind environments for aircraft safety investigation purposes.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2752 , M-185
    Format: application/pdf
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  • 8
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    Estimates of the low-level wind shear and turbulence in the vicinity of Kennedy International Airport on 24 June 1975 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A study was conducted to estimate the type of wind and turbulence distributions which may have existed at the time of the crash of Eastern Airlines Flight 66 while attempting to land. A number of different wind and turbulence profiles are predicted for the site and date of the crash. The morning and mid-afternoon predictions are in reasonably good agreement with magnitude and direction as reported by the weather observer. Although precise predictions cannot be made during the passage of the thunderstorm which coincides with the time of the accident, a number of different profiles which might exist under or in the vicinity of a thunderstorm are presented. The profile that is most probable predicts the mean headwind shear over 100 m (300 feet) altitude change and the average fluctuations about the mean headwind distribution. This combination of means and fluctuations leads to a reasonable probability that the instantaneous headwind shear would equal the maximum value reported in the flight recorder data.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2751 , M-183
    Format: application/pdf
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  • 9
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    Three-dimensional boundary layers approaching separation (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The theory of semi-similar solutions of the laminar boundary layer equations is applied to several flows in which the boundary layer approaches a three-dimensional separation line. The solutions obtained are used to deduce the nature of three-dimensional separation. It is shown that in these cases separation is of the "ordinary" type. A solution is also presented for a case in which a vortex is embedded within the three-dimensional boundary layer.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Advan. in Eng. Sci., Vol. 4; p 1409-1421
    Format: application/pdf
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  • 10
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    Streamline curvature effects on turbulent boundary layers (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A theoretical tool has been developed for predicting, in a nonempirical manner, effects of streamline curvature and coordinate-system rotation on turbulent boundary layers. The second-order closure scheme developed by Wilcox and Traci has been generalized for curved streamline flow and for flow in a rotating coordinate system. A physically based straightforward argument shows that curvature/rotation primarily affects the turbulent mixing energy; the argument yields suitable curvature/rotation terms which are added to the mixing-energy equation. Singular-perturbation solutions valid in the wall layer of a curved-wall boundary layer and a fully developed rotating channel flow demonstrate that, with the curvature/rotation terms, the model predicts the curved-wall and the rotating coordinate system laws of the wall. Results of numerical computations of curved-wall boundary layers and of rotating channel flow show that curvature/rotation effects can be computed accurately with second-order closure.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 76-353 , Fluid and Plasma Dynamics Conference; Jul 14, 1976 - Jul 16, 1976; San Diego, CA
    Format: text
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