NEWTONIAN FLOW OVER A STATIONARY BODY IN UNSTEADY FLOW,
Abstract
The equations governing either two-dimensional or axisymmetric, unsteady hypersonic flow over a stationary body are developed on the hypothesis of a thin shock layer. These approximate equations are integrated to obtain a formal generalization of the Newton-Busemann formula for the pressure on the body. It is found that, just as in steady flow, tangential velocity, integrated mass flux, and entropy are conserved by fluid particles within the shock layer; however, retarded-time effects render specific applications more complicated. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 03, 1964
- Accession Number
- AD0604892
Entities
People
- J. W. Miles
Organizations
- The Aerospace Corporation