ESTIMATION OF TURBULENT HEAT TRANSFER AT THE SONIC POINT OF A BLUNT-NOSED BODY.

Abstract

An equation is derived from a turbulent-boundary-layer analysis for the convective heat transfer at the sonic point of a blunt-nosed body in terms of conditions at the sonic point. The analysis is continued to give the heat transfer in terms of conditions at the stagnation point for the case of a perfect gas (which is straightforward) and for the dissociated air flow occurring at hypersonic flight velocities. For rapid estimation purposes, a 'very approximate solution' is developed for hypersonic speeds which involves only the free-stream velocity and density and the radius of curvature at the sonic point. The results obtained from the different solutions are compared for a sample calculation. As part of the dissociated air flow solution, a method for determining the flow conditions at the sonic point in terms of an average isentropic exponent is presented. Using this method and an assumed Newtonian pressure distribution, an equation is derived for the inviscid-flow velocity gradient at the sonic point. (Author)

Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1957
Accession Number
AD0829019

Entities

People

  • Merwin Sibulkin

Tags

DTIC Thesaurus Topics

  • Air Flow
  • Boundary Layer
  • Equations
  • Flow
  • Fluid Dynamics
  • Fluid Flow
  • Free Stream
  • Heat Transfer
  • Hypersonic Flight
  • Inviscid Flow
  • Layers
  • Pressure Distribution
  • Stagnation Point
  • Turbulent Boundary Layer

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flight
  • Hypersonics - Hypersonic Flow