Accession Number : AD0668069

Title :   ON THE CALCULATION OF UNSTEADY NONLINEAR THREE-DIMENSIONAL SUPERSONIC FLOW PAST WINGS,

Descriptive Note : Final rept.,

Corporate Author : STANFORD UNIV CALIF DEPT OF AERONAUTICS AND ASTRONAUTICS

Personal Author(s) : Kacprzynski,J. J.

Report Date : JAN 1968

Pagination or Media Count : 65

Abstract : A comprehensive study is made of factors influencing the accuracy of predicted thickness effects on the flow due to oscillatory motion of a sweptback wing in supersonic flight. For a delta planform with its leading edge swept at or near the Mach angle, the streamlines and velocity pattern due to thickness are found to be highly three-dimensional. Based on this observation, improvements are suggested to previous approximate second-order theories for the unsteady loading. Numerical examples are presented for 45 degree delta wings of 5% and 10% thicknesses, which indicate a substantial difference between the linearized and nonlinear lifting potential distributions. Although a greater volume of computation is needed to guarantee adequate accuracy, practical means are described for the complete numerical solution of problems of this type. (Author)

Descriptors :   (*SWEPTBACK WINGS, SUPERSONIC CHARACTERISTICS), (*DELTA WINGS, *THREE DIMENSIONAL FLOW), FLOW FIELDS, NONLINEAR SYSTEMS, LEADING EDGES, THICKNESS, OSCILLATION, MATHEMATICAL PREDICTION, ANGLE OF ATTACK, FLUTTER, LIFT, ACCURACY, AEROELASTICITY, NUMERICAL ANALYSIS

Subject Categories : Aerodynamics
      Aircraft
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE