The Similarity Law for Hypersonic Flow About Slender Three-Dimensional Shapes
Abstract
The similarity law for steady, inviscid hypersonic flow about slender three-dimensional shapes is derived in terms of customary aerodynamic parameters. To have similarity of flow, the law states that the lateral dimensions of the shapes in question and their angles with respect to the flight direction must be inversely proportional to their flight Mach numbers. A direct consequence of this law is that the ratio of the local static pressure to the free-stream static pressure is the same at corresponding points in similar flow fields. The law is applied to the determination of simple expressions for correlating the forces and moments acting on related shapes operating at hypersonic speeds. The shapes considered are wings, bodies, and wing-body combinations. In the special case of inclined bodies of revolution, these expressions are extended to include some significant effects of the viscous cross force. Results of a limited experimental investigation of the pressures acting on two inclined cones are found to check the law as it applies to bodies of revolution. Further investigation is necessary, however, to determine the range of applicability of the law.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1951
- Accession Number
- ADA382389
Entities
People
- A. J. Eggers Jr.
- Frank M. Hamaker
- Stanford E. Neice
Organizations
- National Aeronautics and Space Administration