Aerodynamic Heating of Cannon Launched Guided Projectiles.
Abstract
The object of this research is to investigate the rate of aerodynamic heat-transfer on the surface of blunt body of revolution, such as a cannon launched guided projectile, flying at supersonic speed. A mathematical model has been developed based on Illingworth-Stewartson transformation, and a perturbation technique and similarity analysis which describes the aerodynamic heating processes associated with supersonic flight of a bluntnose projectile. The governing equations are reduced to a set of coupled nonlinear ordinary differential equations in first, third, and fifth order of the transformed coordinates, respectively. The equations are ready to be solved by a standard numerical integration scheme. (Modified author abstract)
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1974
- Accession Number
- AD0782864
Entities
People
- D. C. Chou
Organizations
- University of Iowa