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  • Data
  • Other Sources  (8)
  • Aerodynamics
  • Aircraft Design, Testing and Performance
  • 1980-1984  (8)
  • 1950-1954
  • 1981  (8)
  • 1
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    Effects of Horizontal-Control Planform and Wing-Leading-Edge Modification on Low-Speed Longitudinal Aerodynamic Characteristics of a Canard Airplane Configuration (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An investigation at low subsonic speeds has been conducted in the Langley 300-MPH 7- by 10-foot tunnel. The basic wing had a trapezoidal planform, an aspect ratio of 3.0., a taper ratio of 0.143, and an unswept 80-percent-chord line. Modifications to the basic wing included deflectable full-span and partial-span leading-edge chord-extensions. A trapezoidal horizontal control similar in planform to the basic wing and a 60 deg sweptback delta horizontal control were tested in conjunction with the wing. The total planform area of each horizontal control was 16 percent of the total basic-wing area. Modifications to these horizontal controls included addition of a full-span chord-extension to the trapezoidal planform and a fence to the delta planform.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TM-X-549 , L-1372
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Hang Gliders (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Francis M. Rogallo and his wife Gertrude researched flexible controllable fabric airfoils with a delta, V-shaped, configuration for use on inexpensive private aircraft. They were issued a flex-wing patent and refined their designs. Development of Rogallo wings, used by U.S. Moyes, Inc. substantially broadened the flexible airfoil technology base which originated from NASA's reentry parachute. The Rogallo technology, particularly the airfoil frame was incorporated in the design of a kite by John Dickenson. The Dickenson kite served as prototype for the Australian Moyes line of hang gliders. Company no longer exists.
    Keywords: Aircraft Design, Testing and Performance
    Type: Spinoff 1981; 79
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Temperature stabilized linkage (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A temperature compensated passive linkage for interconnecting two members having different coefficients of expansion. Preferably the linkage is utilized for interconnecting the stabilizer of a plane with its elevator. The stabilizer may be a graphite epoxy composite while the elevator may consist of aluminum-fiberglass. The differences in the rate of expansion of the two members is compensated by the linkage of the invention which in turn will move a side load hinge fitting to minimize aerodynamic and mechanical problems.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Calculation of Unsteady Transonic Flow Over an Airfoil (1981)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An implicit finite-difference solver for either the Euler equations or the "thin-layer" Navier-Stokes equations was used to calculate a transonic flow over the NACA 64A010 airfoil pitching about its one-quarter chord. An unsteady automatic grid-generation procedure that will improve significantly the computational efficiency of various unsteady flow problems is described. The calculated results for both inviscid and viscous flows at Mach number 0.8 over the airfoil oscillating with reduced frequency referenced to one-half chord, 0.2, are compared with experimental data measured in the Ames 11 x 11 ft Transonic Wind Tunnel. Nonlinear, unsteady effects of the flow on the surface pressure variations, shock-wave excursions, and overall airloads are examined. Good agreements between the results of computations and experiments were obtained. In the shock-wave region, however, the results of the viscous-flow computations showed closer agreement with the experimental data.
    Keywords: Aerodynamics
    Type: AIAA Paper 79-1554 , AIAA Journal; 19; 6; 684-690|Fluid and Plasma Dynamics; Jul 23, 1979 - Jul 25, 1979; Williamsburg, VA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Alleviation of Spin-Entry Tendencies through Localization of Wing-Flow Separation (1981)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Studies have been made on several wing leading-edge modifications applicable at present to single-engine light aircraft, which produce stabilizing vortices at stall and beyond. These vortices have the effect of fixing the stall pattern of the wing such that the various portions of the wing upper surface stall nearly symmetrically. The lift coefficient produced is maintained at a high level to angles of attack significantly above the stall angle of the unmodified wing, and the divergence in roll usually is reduced to a controllable level. It is hypothesized that these characteristics will help prevent inadvertent spin entry after a stall. Results are presented from recent large-scale wind-tunnel tests of a typical light aircraft, both with and without the modifications. The data indicate (hot the static stall and poststall characteristics of this aircraft, in a typical landing-approach condition, are noticeably improved when it suitable leading-edge modification is employed; and also that no appreciable aerodynamic penalties are evident in the normal flight envelope.
    Keywords: Aerodynamics
    Type: NASA/TM-81-207529 , NAS 1.15:207529 , AIAA Paper 78-1476R , Journal of Aircraft; 18; 2; 69-75|Aircraft Systems and Technology Conference; Aug 21, 1978 - Aug 23, 1978; Los Angeles, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Lift Enhancing Surfaces on Several Advanced V/STOL Fighter/Attack Aircraft Concepts (1981)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An analysis of the relative influences of for-ward lift-enhancing surfaces on the overall lift and drag characteristics of three wind-tunnel models representative of V/STOL fighter/attack aircraft is presented. Two of the models are canard-wing configurations and one has a wing leading-edge extension (LEX) as the forward lifting surface. Data are taken from wind-tunnel tests of each model covering Mach numbers from 0.4 to 1.4. Overall lift and drag characteristics of these models and the generally favorable interactions of the forward surfaces with the wings are highlighted. Results indicate surface that larger LFX's and canards generally give greater lift and drag improvements than ones that are smaller relative to the wings.
    Keywords: Aerodynamics
    Type: NASA/TM-81-207514 , NAS 1.15:207514 , AIAA Paper 81-1675 , Aircraft Systems and Technology Conference; Aug 11, 1981 - Aug 13, 1981; Dayton, OH; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Full-Scale Wind-Tunnel Study of the Effect of Nacelle Shape on Cooling Drag (1981)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Tests were made in the Ames 40 by 80 ft Wind Tunnel of a semispan wing with a nacelle (no propeller) from a typical, general aviation twin-engine aircraft. Measurements were made of the effect on drag of the flow of cooling air through the nacelle. Internal and external nacelle pressures were measured. It was found that the cooling airflow accounts for about 13% of the total estimated airplane drag during both cruise and climb. The now of cooling air through the nacelle accounts for 30% of the airflow drag component during cruise and 42% during climb; the balance, in both cruise and climb, is attributed to [he external shape of the nacelle. It was suggested that improvements could possibly be made by relocating both the inlet and the outlet for the cooling air.
    Keywords: Aerodynamics
    Type: NASA/TM-81-207547 , NAS 1.15:207547 , AIAA Paper 79-1820R , Aircraft Systems and Technology Meeting; Aug 20, 1979 - Aug 22, 1979; New York, NY; United States|Journal of Aircraft; 18; 2; 82-88
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Transonic Flow Past a Symmetrical Airfoil at High Angle of Attack (1981)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The results of an experimental investigation of shock-induced stall and leading-edge stall on a 64A010 airfoil section are presented. Advanced nonintrusive techniques - laser velocimetry and holographic interferometry - were used in characterizing the inviscid and viscous flow regions. The measurements include Mach contours of the inviscid now regions, and mean velocity, flow direction, and Reynolds shear stress profiles in the separated regions. The experimental observations of this study are relevant to efforts to improve surface-pressure prediction methods for airfoils at or near stall.
    Keywords: Aerodynamics
    Type: NASA/TM-81-207541 , NAS 1.15:207541 , AIAA Paper 79-1500R , Journal of Aircraft; 18; 1; 7-14|Fluid and Plasma Dynamics Conference; Jul 23, 1979 - Jul 24, 1979; Williamsburg, VA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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