A Multiple Zone Method for Supersonic Tactical Missiles
Abstract
A practical means of predicting the inviscid flow field about a supersonic missile is to numerically solve the steady, three-dimensional Euler equations. A major problem encountered in steady, supersonic calculations is the treatment of complex cross-sectional geometries which arise in conjunction with configurations featuring fins, inlets and tails. An alternative approach for treating complex missile and aircraft configurations is a multiple zone strategy. A multiple zone computational method applicable to finned bodies is supersonic flight is described. At each cross-section, the computational domain is broken into a number of zones, each of which can be described using a simple mapping. The zones are chosen to ensure that the bow shock, fin and body surfaces coincide with zone edges. At zone interfaces, the mesh may be discontinuous in a direction normal to the edge. Along zone edges, surfaces are allowed to form or disappear during the computation. The surface edges which form at points where surfaces appear or disappear are treated using a local analysis. The resulting algorithm is applicable to a wide range of configurations including interior as well as exterior supersonic flow fields. Calculations are compared to experiment for several different missile shapes. Keywords: Numerical methods.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1986
- Accession Number
- ADA175938
Entities
People
- A. B. Wardlaw
- F. J. Priolo
- J. M. Solomon
Organizations
- Naval Ordnance Laboratory