An Inviscid Computational Method for Tactical Missile Configurations,
Abstract
A finite difference method suitable for the design of finned bodies in supersonic flight is described. Efficient numerical calculations are achieved using a thin fin approximation which neglects fin thickness but retains a description of the fin surface slope. The resulting algorithm is suitable for treating relatively thin, straight fins with sharp edges which may be deflected. Methods for treating the fin leading and trailing edges are described which are dependent on the Mach number of the flow normal to the leading edge. The leading and trailing edge analysis varies from exact to empirical as the normal component varies from a supersonic to subsonic. A procedure for modeling body crossflow separation using a Kutta condition is described which yields a reasonable leeside vortex structure. Calculations are compared to experiment for body-alone, body-wing, body-tail and body-wing-tail configurations. The computer program, developed in this study, is described in a separate report.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1981
- Accession Number
- ADA116904
Entities
People
- A. B. Wardlaw Jr.
- F. P. Baltakis
- J. M. Solomon
- L. B. Hackerman
Organizations
- Naval Ordnance Laboratory