Accession Number : ADA116262

Title :   Transonic Airfoils with a Given Pressure Distribution,

Corporate Author : ARIZONA UNIV TUCSON ENGINEERING EXPERIMENT STATION

Personal Author(s) : Hassan,A ; Seebass,A Robert ; Sobieczky,H

PDF Url : ADA116262

Report Date : Jun 1981

Pagination or Media Count : 46

Abstract : An inverse design procedure for airfoils, based on hodograph techniques, has been developed. For subcritical flows the subsonic portion of the pressure distribution is prescribed; for supercritical flows the stream function on the sonic line is given instead of the supercritical portion of the pressure distribution. In the special variables we use, the equation for the stream function may be solved iteratively using a fast Poisson solver, for the subsonic portion of the flow; for supercritical flows, the supersonic portion is calculated using a characteristic calculation. The results are then mapped back to the physical plane to determine the airfoil shape. Both subcritical and supercritical results are presented. The show good agreement with the direct computation of the flow past the designed airfoil. (Author)

Descriptors :   *Transonic airfoils, *Computer aided design, *Supercritical airfoils, *Pressure distribution, Algorithms, Supercritical flow, Subsonic flow, Transonic flow, Shock waves, Wings, Inviscid flow, Viscous flow, Boundary layer, Equations of motion

Subject Categories : Theoretical Mathematics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE