STAGNATION POINT HEAT TRANSFER FOR HYPERSONIC FLOW

Abstract

A design method is given for obtaining stagnation point heat transfer on a spherical nose in hypersonic flow. The heat transfer equation incorporates real gas effects through use of dissociated air properties and a fitted curve for the stagnation point velocity gradient. Comparison with numerical solutions of the compressible dissociated stagnation point heat transfer indicates agreement within plus or minus 5%. The derived equation for heat transfer is a function only of free stream Mach number, free stream pressure and body nose radius.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1956
Accession Number
AD0829017

Entities

People

  • Mary F. Romig

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Chemical Reactions
  • Compressible Flow
  • Differential Equations
  • Dissociation
  • Equations
  • Flow
  • Fluid Dynamics
  • Free Stream
  • Heat Transfer
  • Hypersonic Flow
  • Incompressible Flow
  • Mach Number
  • Stagnation Point
  • Thermal Conductivity
  • Transport Properties

Readers

  • Fluid Dynamics.

Technology Areas

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