AERODYNAMIC AND HEAT TRANSFER CHARACTERISTICS OF BASIC BODIES IN HYPERSONIC FLOW OF AIR AND OF COMBUSTION GAS MIXTURES
Abstract
Experimental results of pres re i tri ution on a blunted cone, a skirted hemisphere-cylinder model, and a blunt leading edge diamond airfoil, and corresponding heat transfer distributions of the latter two bodies are presented. Nominal test conditions were Mach Number equals 6.6 at stagnati n te perature 2500 R and unit Reynolds Number equals 2.8 x 10 to the 5th p wer per foot. To compare pressure ratios in the different media, the effects of water vapor condensation on free stream conditi ns must be accounted for. Maximum unexplained model pressure coefficient ifferences between media were as high as 25% along the skirt of the hemisphere-cylinder model, 10% on the blunt cone, 9% on wedge at alp a 15 degrees. Tests in all media showed a strong leading edge effect. Results show that in the test secti n the pitot pressure is little affected, but static pressure and Mach number are strongly affected by water vap r c n ensation. The stagnation point heat transfer rate measured in an airstream is nearly % higher than the Fay-Riddell theory; stagnation point data obtained in flow of simulated combustion products is nearly 22% lower than theory. Experimental results are given for angles of attack from 0 to 15 degrees; the data are compared with results from the Bertram-Feller theory and the reference enthalpy method. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1962
- Accession Number
- AD0274792
Entities
People
- K. O. Thompson
- R. Hermann
- W. L. Melnik
Organizations
- University of Minnesota