MEASUREMENT AND EMPIRICAL CORRELATION OF TRANSPIRATION-COOLING PARAMETERS ON A 25-DEGREE CONE IN A TURBULENT BOUNDARY LAYER IN BOTH FREE FLIGHT AND A HOT-GAS JET

Abstract

Transpiration-cooling parameters are presented for a turbulent boundary layer on a cone configuration with a total angle of 25 degrees which was tested in both free flight and in an ethylene-heated high-temperature jet at a Mach number of 2.0. The flight-tested cone was flown to a maximum Mach number of 4.08 and the jet tests were conducted at stagnation temperatures ranging from 937 to 1,850 R. In general, the experimental heat transfer was in good agreement with the theoretical values. Inclusion of the ratio of local stream temperature to wall temperature in the nondimensional flow rate parameter enabled good correlation of both sets of transpiration data. The measured pressure at the forward station coincided with the theoretical pressure over a sharp cone; however, the measured pressure increased with distance from the nose tip. (Author)

Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1961
Accession Number
AD0264882

Entities

People

  • Bernard Rashis
  • Thomas E. Jr. Walton

Organizations

  • National Aeronautics and Space Administration

Tags

DTIC Thesaurus Topics

  • Alkenes
  • Boundaries
  • Boundary Layer
  • Ethylenes
  • Flight
  • Flow Rate
  • Free Flight
  • Heat Transfer
  • High Temperature
  • Hot Gases
  • Layers
  • Mach Number
  • Measurement
  • Nose Tips
  • Stagnation Temperature
  • Turbulent Boundary Layer

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Combustion and Flow Dynamics.
  • Fluid Mechanics and Fluid Dynamics.