Hypersonic,Turbulent, Cold-Wall, Skin-Friction and Heat-Transfer Measurements on an Axisymmetric Sharp Cone
Abstract
Turbulent skin-friction coefficients directly measured on an axisymmetric five-degree-half-angle sharp cone by two floating-element skin- friction balances at a free-stream Mach number of 7.9 are presented. Heat- transfer distributions are obtained simultaneously. These results yield directly the Reynolds analogy factor. Experimental data are used to evaluate four predictive methods. Except for the relatively low-Reynolds-number case, the directly measured sharp-cone Reynolds analogy factor is between 1.01 and 1.07, which is in good agreement with recent flat-plate measurements. Results indicate that the Stanton Number is essentially constant for one range and decreases by about 10 percent in another.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 15, 1973
- Accession Number
- AD0764059
Entities
People
- Kuei-yuan Chien
Organizations
- Naval Ordnance Laboratory