ON THE CALCULATION OF UNSTEADY NONLINEAR THREE-DIMENSIONAL SUPERSONIC FLOW PAST WINGS,
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1968
- Accession Number
- AD0668069
Entities
People
- J. J. Kacprzynski
Organizations
- Stanford University