Accession Number : AD0782278

Title :   Circumferential Nonuniform Heating During Transition on a Slender Cone at Hypersonic Mach Numbers.

Descriptive Note : Technical information series,

Corporate Author : GENERAL ELECTRIC CO SCHENECTADY N Y RESEARCH AND DEVELOPMENT CENTER

Personal Author(s) : Nagamatsu,H. T. ; Wisler,D. C. ; Sheer,R. E. , Jr

Report Date : JUL 1967

Pagination or Media Count : 43

Abstract : An experimental investigation was conducted to study nonuniform heating rates during laminar boundary layer transition on a 4 foot 10 deg cone. The Mach number outside the boundary layer was 9.6 and the wall to stagnation temperature ratio was 0.214. Four sputtered platinum wedge heat transfer probes were used to survey the boundary layer at four angles 34.5 inches from the cone tip. For the transition and turbulent boundary layer there were indications of large nonuniform heating rates, and heating rates in the circumferential direction varied with time.

Descriptors :   *Laminar boundary layer, *Hypersonic characteristics, *Conical bodies, *Aerodynamic heating, Rates, Boundary layer transition, Turbulent boundary layer, Test methods, Nonuniform, Heat transfer, Oscillation, Probes, Angles

Subject Categories : Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE