SUPERSONIC FREE-FLIGHT MEASUREMENT OF HEAT TRANSFER AND TRANSITION

Abstract

Heat-transfer coefficients in the form of Stan on number and boundary-layer transition data are presented for a 100-inch long 10 degree totalangle cone with a 1/16-inch tip radius over a range of Mach numbers from 1.8 to 3.5 a various wall-to-local-stream t mpera ur ra io The exp rimen al heat-transfer coefficients were in general slightly higher than theoretical values. A maximum transition Reynolds number of 33 x 10 to the 6th power was measured. (Author)

Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1961
Accession Number
AD0261371

Entities

Organizations

  • National Aeronautics and Space Administration

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Boundary Layer Transition
  • Coefficients
  • Flight
  • Fluid Mechanics
  • Free Flight
  • Heat Transfer
  • Heat Transfer Coefficients
  • Layers
  • Mach Number
  • Reynolds Number
  • Transitions

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Mechanics and Fluid Dynamics.
  • Snow Cover Descriptors for Reptiles and Their Illustrations.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow