Three Dimensional Supersonic Flow Over a Smooth Body with Shock-Producing Protuberance

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 conf...

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Bibliographic Details
Main Author: Scheuing,Richard A
Format: Report
Language:English
Subjects:
Aerodynamics
AIRCRAFT CANOPIES
CONICAL BODIES
EXTENDABLE STRUCTURES
FLOW FIELDS
Fluid Mechanics
NUMERICAL METHODS AND PROCEDURES
PROTUBERANCES
SHOCK WAVES
SMOOTH BODIES
THREE DIMENSIONAL FLOW
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Summary: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.