Accession Number : AD0845724

Title :   Comparison of Laminar and Turbulent Cone Boundary Layer Flow with and without Pressure Gradient.

Descriptive Note : Technical rept. 1 Jan 66-31 Dec 67,

Corporate Author : GENERAL ELECTRIC CO PHILADELPHIA PA MISSILE AND SPACE DIV

Personal Author(s) : Graber, B. C. ; Softley, E. J. ; Weber, H. E.

Report Date : JUN 1968

Pagination or Media Count : 43

Abstract : This report presents a comparison of laminar and turbulent boundary layer data at a local Mach number of 10 for a nominal zero pressure gradient flow versus a highly favorable pressure gradient flow. The data is obtained in similar shock tunnel facilities on a 5 degree half angle, sharp cone. Surface heat transfer and boundary layer total pressure profiles are measured and compared. Various theoretical prediction methods are compared to the turbulent heat transfer results with the reference enthalpy approach giving the best results. Analysis of the data indicates a significant contribution to both laminar and turbulent boundary layer surface heat transfer due to a favorable pressure gradient while comparison of the boundary layer total pressure profiles indicates local boundary layer similarity. (Author)

Descriptors :   (*CONICAL BODIES, HYPERSONIC CHARACTERISTICS), (*TURBULENT BOUNDARY LAYER, CONICAL BODIES), (*LAMINAR BOUNDARY LAYER, CONICAL BODIES), BOUNDARY LAYER TRANSITION, LAMINAR FLOW, HEAT TRANSFER, COOLING, PRESSURE, TURBULENCE, SLENDER BODIES, SKIN FRICTION, AERODYNAMIC HEATING, MATHEMATICAL PREDICTION, ERRORS, ENTHALPY, VELOCITY, SHEAR STRESSES, MACH NUMBER, REYNOLDS NUMBER, REENTRY VEHICLES, MODEL TESTS, HYPERSONIC FLOW.

Subject Categories : Fluid Mechanics
      Unmanned Spacecraft

Distribution Statement : APPROVED FOR PUBLIC RELEASE