Basic Studies of Wing-Body Interference at High Angles of Attack and Supersonic Speeds.
Abstract
The problem of computing the steady inviscid supersonic flows about thin wings having sharp subsonic leading edges and leading-edge separation is solved in this paper. Both wings alone or wings in the presence of the body are considered. To obtain an efficient procedure the steady Euler equations are used as the basic governing equations as opposed to the more complicated Navier-Stokes equation. The viscous effects, important near the sharp leading edges, are simulated by a Kutta condition applied at the leading edges of the wings. The rest of the flow field is essentially controlled by the inviscid equations. The equations, written in conservation form in generalized curvilinear coordinates, are approximated by MacCormack's second-order accurate predictor-corrector algorithm. The flow tangency conditions at the body surface are satisfied by Abbett's scheme and the outer bow-shock position by the Rankine-Hugoniot jump relations. Internal shock waves or tangentially discontinuities are captured. The slip surface emanating from the leading edge of the sharp wing excited nonlinear instabilities in the MacCormack's scheme, which were stabilized by special flow dependent fourth-order damping terms.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1979
- Accession Number
- ADA087134
Entities
People
- Goetz H. Klopfer
- Jack N. Nielsen
Organizations
- Nielsen Engineering & Research (United States)