STAGNATION POINT HEAT TRANSFER MEASUREMENTS IN HYPERSONIC LOW REYNOLDS NUMBER FLOWS
Abstract
Measurements have been made of heat transfer rates at the stagnation point of cylinders and spheres for hypersonic flow at Reynolds numbers from 5 to 500 based on nose radius. A comparison of the measurements with the predictions of Probstein and Kemp, Ferri, Zakkay and Ting, and H. K. Cheng is considered. It is concluded that, within the experimental error, ordinary boundary layer theory can be used to predict the heat transfer rates down to stagnation point Reynolds numbers of twenty. At this point, the heat transfer rate increases somewhat as predicted, reaching the free molecule value at a Reynolds number between two and three.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 05, 1962
- Accession Number
- AD0282735
Entities
People
- Robert L. Varwig
Organizations
- The Aerospace Corporation