Aerodynamic Heating of Supersonic Blunt Bodies
Abstract
The object of the research is to investigate the rate of aerodynamic heat transfer on the surface of a blunt body of revolution flying at supersonic speed. A mathematical model, based on Illingworth-Stewartson transformation and a perturbation technique with a similarity analysis, which describes the aerodynamic heating processes associated with supersonic flight of a blunt-nose projectile has been developed. The governing transport equations are reduced to a set of coupled nonlinear ordinary differential equations in first, third, and fifth order of the transformed coordinates. The equations were solved by a standard numerical integration scheme. Results describing velocity and temperature, profiles inside the boundary layer, skin friction and local heat transfer rates are presented.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1974
- Accession Number
- ADA001135
Entities
People
- David C. Chou
- Theodore F. Smith
Organizations
- University of Iowa