Three Dimensional Supersonic Flow Over a Smooth Body with Shock-Producing Protuberance.
Abstract
The investigation is directed primarily at the second order solution of the three dimensional, supersonic flow field around an arbitrarily-shaped body which, although otherwise of smooth contour, has a protuberance that generates a shock wave and substantially disturbs the flow downstream. Such configurations occur for example, in fuselage-canopy combinations. The calculation of the flow field about a body with no local protuberance is considered first, the solution being based on the so-called method of near-characteristics. Typical numerical results are presented for circular and elliptic cones, tangent ogives of circular and elliptic cross section, and a representative non-axisymmetric compression surface. Comparisons with results from conical flow theories and with experimental data are made wherever possible. The theoretical analysis and computational procedure evolved for the primary body is then extended to permit the addition of the shock-producing protuberance. This approach enable the flow upstream of the secondary shock to be considered uniform.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1971
- Accession Number
- AD0728501
Entities
People
- Richard A. Scheuing
Organizations
- Grumman