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):

Report Date:

1968-01-01

Pagination or Media Count:

65.0

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

Subject Categories:

  • Aerodynamics
  • Aircraft
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE