Circumferential Nonuniform Heating During Transition on a Slender Cone at Hypersonic Mach Numbers.
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1967
- Accession Number
- AD0782278
Entities
People
- D. C. Wisler
- H. T. Nagamatsu
- R. E. Sheer Jr.
Organizations
- General Electric