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  • AIRCRAFT DESIGN, TESTING AND PERFORMANCE  (3)
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  • 1
    facet.materialart.
    Unknown
    Geometric analysis of wing sections (1995)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper describes a new geometric analysis procedure for wing sections. This procedure is based on the normal mode analysis for continuous functions. A set of special shape functions is introduced to represent the geometry of the wing section. The generators of the NACA 4-digit airfoils were included in this set of shape functions. It is found that the supercritical wing section, Korn airfoil, could be well represented by a set of ten shape functions. Preliminary results showed that the number of parameters to define a wing section could be greatly reduced to about ten. Hence, the present research clearly advances the airfoil design technology by reducing the number of design variables.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-110346 , A-950049 , NAS 1.15:110346
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Aerodynamic design of a Coanda induced force and thruster anti-torque system (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A general method of analysis of the external and internal aerodynamics of a generic Coanda induced circulation anti-torque system is presented. The technique gives moment about the yaw axis and download induced on the boom as well as the force developed by an aft jet. The external flows including downwash, wake swirl and the boom circulation are considered. The internal flow and losses through the duct, fan, blown slots, cascades and nozzle are considered on a step-by-step basis. Limited comparison is made with open data where available.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AHS Annual Forum; May 06, 1991 - May 08, 1991; Phoenix, AZ; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Model tilt-rotor hover performance and surface pressure measurement (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A test of a small scale 3-bladed model rotor, with geometry typical of that used on tilt rotor aircraft, was conducted in the Army Aeroflightdynamics Directorate's anechoic hover chamber. The purpose was to determine the hover performance of the rotor and investigate the pressure distributions on a blade at various collective pitch angles and tip speeds. The measured pressures indicate that the rotor did not stall for high collective pitch angles up to theta sub c = 25 deg. This is clearly a 3-D effect since 2-D theory predicts flow separation at these high angles. The flow near the trailing edge separated above theta sub c = 25 deg which caused a sharp increase in power.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AHS, Annual Forum; May 21, 1990 - May 23, 1990; Washington, DC; United States
    Format: text
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    NASA TECHNICAL REPORTS
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