Accession Number : AD0658322

Title :   MEASUREMENTS OF HYPERSONIC TURBULENT HEAT TRANSFER ON A HIGHLY COOLED CONE,

Corporate Author : NAVAL ORDNANCE LAB WHITE OAK MD

Personal Author(s) : Wilson,Donald M.

Report Date : 17 JUL 1967

Pagination or Media Count : 63

Abstract : Turbulent boundary layer heat transfer rates were measured on a thin-walled slender cone at a free-stream Mach number of 5.0. Wall to stagnation temperature ratios from 0.15 to 0.40 were obtained by pre-cooling the model using liquid nitrogen. Tests at a wide range of Reynolds numbers were conducted by varying the tunnel supply pressure; thus providing data for both laminar and mixed laminar-turbulent types of boundary layers. The experimental results obtained were compared with existing theories which predict convective heat transfer coefficients. These comparisons indicate that the data corresponding to a 760R supply temperature verify the predictions of Winkler and Cha; however, data acquired at a supply temperature of 1160R substantiate the predictions of Spalding and Chi. (Author)

Descriptors :   (*CONICAL BODIES, *HEAT TRANSFER), (*HYPERSONIC FLOW, HEAT TRANSFER), TURBULENT BOUNDARY LAYER, COOLING, REYNOLDS NUMBER, SLENDER BODIES, MEASUREMENT

Subject Categories : Aerodynamics
      Fluid Mechanics
      Thermodynamics

Distribution Statement : APPROVED FOR PUBLIC RELEASE