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  • 1
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    The compressibility rule for drag of airfoil noses (1976)
    In:  CASI
    Details
    Publication Date: 2010-11-08
    Description: It is shown that the drag of any semi-infinite airfoil section in purely subsonic inviscid flow follows precisely the Prandtl-Glauert compressibility rule. The result for the parabola has application to leading edge corrections in thin airfoil theory.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 619-623
    Format: text
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  • 2
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    A Comparison of the Aerodynamic Characteristics of Eight Sailwing Airfoil Sections (1979)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The operational characteristics of sailwings are discussed with emphasis placed on the importance of the trailing edge cable tension. The three dimensional aerodynamic characteristics were obtained from wind tunnel tests, and the results compared to determine the magnitude of the aerodynamic penalties paid for various structural simplifications. For the sectional thickness ratios, it is concluded that, while the basic double-membraned sailwing has exceptional aerodynamic performance, even superior for some applications to the conventional hardwing, any notable deviation from this configuration results in an unacceptably large performance penalty.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center The Sci. and Technol. of Low Speed and Motorless Flight, Pt. 1; p 155-176
    Format: application/pdf
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  • 3
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    Force and moment data from a wind-tunnel test of a tilt-nacelle V/STOL propulsion system with an attitude control vane (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A large scale, tilt nacelle V/STOL propulsion system, with an attitude control vane assembly mounted in the exhaust, was tested. The effectiveness of the control vane as well as the aerodynamic characteristics of the entire propulsion system were determined. The results, in the form of tabulated coefficients, for both the vane forces and moments and the total forces and moments produced by the propulsion system are presented.
    Keywords: AERODYNAMICS
    Type: NASA-TM-81157 , A-8013
    Format: application/pdf
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  • 4
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    Simulation of the pressure field near a jet by randomly distributed vortex rings (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Fluctuations of the pressure field in the vicinity of a jet are simulated numerically by a flow model consisting of axially symmetric vortex rings with viscous cores submerged in a uniform stream. The time interval between the shedding of successive vortices is taken to be a random variable with a probability distribution chosen to match that from experiments. It is found that up to 5 diameters downstream of the jet exit, statistics of the computed pressure field are in good agreement with experimental results. Statistical comparisons are provided for the overall sound pressure level, the peak amplitude, and the Strouhal number based on the peak frequency of the pressure signals.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 17; June 197
    Format: text
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  • 5
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    Wind tunnel investigation of a large-scale upper surface blown-flap model having four engines (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Investigations were conducted in the Ames 40- by 80-Foot Wind Tunnel to determine the aerodynamic characteristics of a large-scale subsonic jet transport model with an upper surface blown flap system. The model had a 25 deg swept wing of aspect ratio 7.28 and four turbofan engines. The lift of the flap system was augmented by turning the turbofan exhaust over the Coanda surface. Results were obtained for several flap deflections with several wing leading-edge configurations at jet momentum coefficients from 0 to 4.0. Three-component longitudinal data are presented with four engines operating. In addition, longitudinal and lateral data are presented with an engine out. The maximum lift and stall angle of the four engine model were lower than those obtained with a two engine model that was previously investigated. The addition of the outboard nacelles had an adverse effect on these values. Efforts to improve these values were successful. A maximum lift of 8.8 at an angle-of-attack of 27 deg was obtained with a jet thrust coefficient of 2 for the landing flap configuration.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-62419 , A-6003
    Format: application/pdf
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  • 6
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    Aerodynamic Characteristics of an A-4B Aircraft with Simulated and Actual Gunfire Damage to One Wing (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The aerodynamic characteristics of a damaged McDonnell Douglas A-4B aircraft were studied in the Ames Research Center's 40- by 80-Foot Wind Tunnel. A standard fuselage and three different wings were used. The first wing tested was an undamaged one in which holes had been cut and detachable cover plates installed. Removal of one or more cover plates gave one of fourteen different simulated damage cases. The other two wings tested were damaged by actual gunfire at an Air Force range.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-73119 , A-6519
    Format: application/pdf
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  • 7
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    The development of methods for predicting and measuring distribution patterns of aerial sprays (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The capability of conducting scale model experiments which involve the ejection of small particles into the wake of an aircraft close to the ground is developed. A set of relationships used to scale small-sized dispersion studies to full-size results are experimentally verified and, with some qualifications, basic deposition patterns are presented. In the process of validating these scaling laws, the basic experimental techniques used in conducting such studies, both with and without an operational propeller, were developed. The procedures that evolved are outlined. The envelope of test conditions that can be accommodated in the Langley Vortex Research Facility, which were developed theoretically, are verified using a series of vortex trajectory experiments that help to define the limitations due to wall interference effects for models of different sizes.
    Keywords: AERODYNAMICS
    Type: NASA-CR-158787 , ARL-79-1
    Format: application/pdf
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  • 8
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    Effects of inlet airframe integration on the inlet of an upper surface blowing four-engine STOL aircraft (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Inlet and nacelle static pressures were measured on a 0.55-scale model of the Quiet Short-Haul Research Airplane (QSRA) in the Ames Research Center's 40- by 80-Foot Wind Tunnel. This model is powered by four JT-15D engines located above the wing with closely spaced adjacent inlets. A fifth JT-15D engine in the fuselage provides boundary-layer control air. Each inlet was instrumented with four to eight rows of axial pressure taps located between X/R approximately plus or minus 1. The tests simulated a broad range of aircraft operating conditions, including engine-out, with lift coefficients from 0.8 to 10.0. Results indicate that the inlets perform well under most operating conditions with little interaction between inlets when the aircraft is moving. Potential problem areas identified are high sideslip angle during approach and an interaction effect between adjacent inlets with high mass flows in static conditions.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 78-959 , Joint Propulsion Conference; Jul 25, 1978 - Jul 27, 1978; Las Vegas, NV; US
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  • 9
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    Structure of the conical flowfield about external axial corners (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A theoretical and experimental investigation of the flowfield about symmetrical and asymmetrical external axial corners formed by the juncture of swept compressive wedges is presented. A study is made of the nature of inviscid cross flow stagnation points and their dependence on certain flow parameters is derived. The importance of imposing the physically relevant boundary condition for numerical simulations is discussed. For the asymmetrical wedge configuration, the proper boundary condition along the axial corner is shown to be a conical analog of Prandtl-Meyer flow. Further insight into the flow structure is revealed by the experimental results.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 78-59 , Aerospace Sciences Meeting; Jan 16, 1978 - Jan 18, 1978; Huntsville, AL
    Format: text
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  • 10
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    Aerodynamic effects of an attitude control vane on a tilt-nacelle V/STOL propulsion system (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: One possible technique for obtaining longitudinal control on a tilt-nacelle V/STOL aircraft is the use of a variable attitude vane assembly mounted in the propulsion system exhaust. Deflecting the vane produces large forces and moments without depending on forward speed of the aircraft. Tests are carried out in the Ames 40 by 80 ft wind tunnel on a large-scale tilt-nacelle V/STOL propulsion system with and without a variable attitude control vane assembly. Aerodynamic characteristics are analyzed in terms of nacelle aerodynamics, vane aerodynamics, and vane-induced effects on the nacelle aerodynamics. It is shown that the aerodynamic forces due to the nacelle without the vane can be a significant part of the total forces produced by the propulsion system. The control vane effectively produces large changes in pitching moment which are accompanied by significant changes in total lift and drag. The vane has a substantial effect on the propulsion-system aerodynamics. Other pertinent results are also given.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 79-1855 , American Institute of Aeronautics and Astronautics, Aircraft Systems and Technology Meeting; Aug 20, 1979 - Aug 22, 1979; New York, NY
    Format: text
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