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  • 1
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    Approximate analytic solution for the position and strength of shock waves about cones in supersonic flow (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Approximate solution for position and strength of shock waves about cones in steady supersonic flow
    Keywords: AERODYNAMICS
    Type: ; ADEMIE DES SCIENCES
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Numerical studies of unsteady transonic flow over oscillating airfoil (1985)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: A finite difference solution to the Navier-Stokes equations combined with a time varying grid generation technique was used to compute unsteady transonic flow over an oscillating airfoil. These computations were compared with experimental data (obtained at Ames Research Center) which form part of the AGARD standard configuration for aeroelastic analysis. A variety of approximations to the full Navier-Stokes equations was used to determine the effect of frequency, shock wave motion, flow separation, and airfoil geometry on unsteady pressures and overall air loads. Good agreement is shown between experiment and theory with the limiting factor being the lack of a reliable turbulence model for high Reynolds number, unsteady transonic flows.
    Keywords: AERODYNAMICS
    Type: AGARD Transonic Unsteady Aerodyn. and its Aeroelastic Appl.; 22 p
    Format: text
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  • 3
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    Experimental studies of scale effects on oscillating airfoils at transonic speeds (1981)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: Scale effects are discussed with reference to a conventional airfoil (NACA 64A010) and a supercritical airfoil (NLR 7301) at mean flow conditions that support both weak and strong shock waves. During the experiment the Reynolds number was varied from 3 x 10 to the sixth power at time history data are presented over the range of reduced frequencies that are important in aeroelastic applications. The experimental data show that viscous effects are important in the case of the supercritical airfoil at all flow conditions and in the case of the conventional airfoil under strong shock wave conditions. Some frequency dependent viscous effects were also observed.
    Keywords: AERODYNAMICS
    Type: AGARD Boundary Layer Effects on Unsteady Airfoils; 13 p
    Format: text
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  • 4
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    The critical role of computational fluid dynamics in rotary-wing aerodynamics (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The field of helicopter rotor aerodynamics is basically the study of unsteady aerodynamic flows in a rotating and translating coordinate system. Current trends in this field are briefly reviewed by examining recent advances in lifting-surface theory, wake modeling, panel methods, and finite-difference models. Examples are used to illustrate selected current methods and some indications of promising future directions are highlighted.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 86-0336
    Format: text
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  • 5
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    Experimental studies of scale effects on oscillating airfoils at transonic speeds (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental data are presented on the effect of Reynolds number on unsteady pressures induced by the pitching motion of an oscillating airfoil. Scale effects are discussed with reference to a conventional airfoil (NACA 64A010) and a supercritical airfoil (NLR 7301) at mean-flow conditions that support both weak and strong shock waves. During the experiment the Reynolds number was varied from 3,000,000 to 12,000,000 at a Mach number and incidence necessary to induce the required flow. Both fundamental frequency and complete time history data are presented over the range of reduced frequencies that is important in aeroelastic applications. The experimental data show that viscous effects are important in the case of the supercritical airfoil at all flow conditions and in the case of the conventional airfoil under strong shock-wave conditions. Some frequency-dependent viscous effects were also observed.
    Keywords: AERODYNAMICS
    Type: NASA-TM-81216 , A-8259
    Format: application/pdf
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  • 6
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    Two-dimensional transonic testing with splitter plates (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The use of splitter plates for two dimensional transonic testing in wind tunnels was investigated on a 12% biconvex airfoil section over the Mach number range 0.6 to 1.0. Measured pressure distributions were compared to transonic theory and to other experiments, including an investigation in the same facility without splitter plates. The results of the experiment show the best agreement with theory over the entire transonic Mach number range.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1153 , A-7221
    Format: application/pdf
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  • 7
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    Experimental unsteady aerodynamics of conventional and supercritical airfoils (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental data on the unsteady aerodynamics of oscillating airfoils in transonic flow are presented. Two 0.5 m-chord airfoil models - an NACA 64A010 and an NLR 7301 - were tested in the NASA-Ames 11 by 11 foot Transonic Wind Tunnel at Mach numbers to 0.85, at chord Reynolds numbers to 12 million and at mean angles of attack to 4 deg. The airfoils were subjected to both pitching and plunging motions at reduced frequencies to 0.3 (physical frequencies to 53 Hz). The new hardware and the extensive use of computer-experiment integration developed for this test are described. The geometrical configuration of the model and the test arrangement are described in detail. Mean and first harmonic data are presented in both tabular and graphical form to aid in comparisons with other data and with numerical computations.
    Keywords: AERODYNAMICS
    Type: NASA-TM-81221 , A-8294
    Format: application/pdf
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  • 8
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    Visualization of quasi-periodic unsteady flows (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A self-synchronizing schlieren flow visualization technique has been developed to study unsteady periodic flows which may result from aeroelastic effects. The technique allows the experimentalist to stroboscopically 'freeze' the streak line pattern at any phase in one period of the motion by driving the schlieren light source with an electronically processed synchronizing signal that is derived by measuring a periodic flow variable with a convenient sensor. Results for the visualization of the near-wake behind an oscillating airfoil at low speeds which show an ordered series of discrete vortices and a curious short-wave-length wake disturbance are examined. Results are also presented for edge tone sound generation.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 78-502 , Structures, Structural Dynamics and Materials Conference; Apr 03, 1978 - Apr 05, 1978; Bethesda, MD
    Format: text
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  • 9
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    Propagation of plane waves in a variable area duct carrying a compressible subsonic flow (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A complete numerical solution is obtained for plane wave propagation in a variable-area duct which carries a mean compressible flow. The equation solved is a matrix formulation of the equations first derived by Tsien in 1952. Sample calculations are presented for four particular flow configurations: (1) a duct-nozzle-duct combination with the acoustic wave traveling with the flow, (2) a duct-nozzle-duct combination with the acoustic wave traveling against the flow, (3) an inlet-nozzle-duct configuration with the acoustic wave traveling against the flow, and (4) a duct-nozzle-exit configuration with the acoustic wave traveling with the flow. For each of these cases, the variation of energy flux with frequency is shown for particular geometry and flow condition.
    Keywords: AERODYNAMICS
    Type: Meeting of the Acoustical Society of America; Apr 23, 1974 - Apr 26, 1974; New York, NY
    Format: text
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  • 10
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    Unsteady aerodynamics of conventional and supercritical airfoils (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The unsteady aerodynamics of a conventional and a supercritical airfoil are compared by examining measured chordwise unsteady pressure time-histories from four selected flow conditions. Although an oscillating supercritical airfoil excites more harmonics, the strength of the airfoil's shock wave is the more important parameter governing the complexity of the unsteady flow. Whether they are conventional or supercritical, airfoils that support weak shock waves induce unsteady loads that are qualitatively predictable with classical theories; flows with strong shock waves are sensitive to details of the shock-wave and boundary-layer interaction and cannot be adequately predicted.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-0734 , Structures, Structural Dynamics, and Materials Conference; May 12, 1980 - May 14, 1980; Seattle, WA
    Format: text
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