THE MEASUREMENT AND COMPARISON WITH THEORY OF HEAT TRANSFER FROM SIMILAR LAMINAR BOUNDARY LAYERS TO AERODYNAMIC BODIES IN SUPERSONIC AND HYPERSONIC GAS STREAMS
Abstract
This analysis describes the experimental measurement of small rates of heat transfer to wind tunnel models from laminar compressible similar boundary layers at supersonic and hypersonic free stream Mach numbers. Wind tunnel models were developed having surface Mach number distributions corresponding to those required by the similar boundary layer solutions of Cohen and Reshotko (AD-53 921). Then a method, using fairly simple equipment, was tested for measuring isothermal heat transfer to cold wind tunnel models with good accuracy and repeatability. Measurements were made of the recovery temperature and heat transfer rates on cold models with similar boundary layers in both favorable and adverse pressure gradients at a free stream Mach number of two. Tests were also conducted at a free stream Mach number of eleven on a hot body having a favorable surface pressure gradient compatible with the similarity requirement. The assumptions of the similarity analysis were fulfilled in varying degrees by the different test configurations. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1961
- Accession Number
- AD0273311
Entities
People
- Wm. G. Reinecke
Organizations
- Princeton University