Turbulent-Heat-Transfer Measurements at a Mach Number of 2.06

Abstract

Turbulent-heat-transfer measurements were obtained through the use of an axially asymmetric annular nozzle which consists of an inner shaped center body and an outer cylindrical sleeve. Measurements taken along the outer sleeve gave essentially flat-plate results that are free from wall interference and corner effects for a Mach number of 2.06 and for a Reynolds number range of 1.7 x 10(exp 6) to 8.8 x 10(exp 7). The heat-transfer coefficients are in good agreement with available data from V-2 rockets and also check the Rubesin theory and the Van Driest theory for a Mach number of 2.0 and for a ratio of inner-surface to free-stream temperature of 1.8. The temperature-recovery factors are approximately 0.5 percent lower than the factors given in NACA TN 2077 for a Mach number of 2.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1955
Accession Number
ADA377282

Entities

People

  • Bernard Rashis
  • Maurice J. Brevoort

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Annular Nozzles
  • Boundary Layer
  • Coefficients
  • Equations
  • Free Stream
  • Heat Transfer
  • Heat Transfer Coefficients
  • Heat Transmission
  • Mach Number
  • Measurement
  • Reynolds Number
  • Specific Heat
  • Stagnation Temperature
  • Static Pressure
  • Surface Temperature
  • Thermal Conductivity

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.