METHOD OF DETERMINING EFFECTS OF HEAT CONDUCTION IN LEADING EDGE OF WIND TUNNEL MODELS.

Abstract

A technique is developed for correcting heat transfer data for conduction effects in the vicinity of the leading edges of wind tunnel models. A solution is obtained by solving the general heat equation as applied to a cylindrical leading edge under a step heat impulse by means of Fourier and Laplace transforms. The local temperature is found to be a power series in time for thin skin models. By comparison of wind tunnel data with the theory developed it was ascertained that only three terms in the series (second degree curve in time) adequately represented the data. The coefficient of the linear time term is shown to be directly proportional to the applied heating rate. This theory is applied to several hypersonic wind tunnel tests and results in the elimination of large conduction errors in the heat transfer coefficient data. (Author)

Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1963
Accession Number
AD0425468

Entities

People

  • Linn E. Miller
  • Wilbur L. Hankey Jr.

Tags

DTIC Thesaurus Topics

  • Coefficients
  • Equations
  • Heat Transfer
  • Heat Transfer Coefficients
  • Hypersonic Wind Tunnels
  • Leading Edges
  • Models
  • Power Series
  • Wind Tunnel Models
  • Wind Tunnel Tests
  • Wind Tunnels

Readers

  • Aerodynamics.
  • Approximation Theory.
  • Combustion and Flow Dynamics.

Technology Areas

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