ASYMPTOTIC HYPERSONIC FLOW THEORY FOR BLUNTED SLENDER CONES AND WEDGES.
Abstract
Inviscid hypersonic flow over slender, unyawed circular cones and wedges has been perturbed for the effect of nose bluntness far behind the nose. The resulting singular-perturbation problem is solved with matched inner and outer asymptotic expansions. For both plane and axisymmetric flows, the leading perturbation in surface pressure is an eigensolution which varies as the real part of downstream distance raised to complex powers. The imaginary parts of all exponents are multiples of a fundamental frequency, and all harmonics decay at a rate which depends on Mach number, specific heat ratio and body geometry. For blunted wedges, the perturbation equations are integrated in closed form generally. The displacement of the shock asymptote relative to the body asymptote was determined without approximation. For blunted cones, it is shown that logarithms do not appear where the afterbody is specified, unlike the inverse problem of flow behind a hyperboloidal shock. Three limiting axisymmetric cases are considered: infinite Mach number, specific heat ratio of unity, and a combination of these known as the NEWTONIAN SLENDER BODY limit. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1966
- Accession Number
- AD0800264
Entities
People
- John W. Ellinwood
Organizations
- The Aerospace Corporation