THE LAMINAR BOUNDARY LAYER ON A CONE IN A SUPERSONIC AIR STREAM AT ZERO ANGLE OF ATTACK

Abstract

This report demonstrates that the integration of the equations for the laminar boundary layer on a cone in a supersonic air stream can be reduced to the equations for the flat plate. The simple result is obtained, that on the cone the boundary layer is different by 1/square root of 3 as compared to the plate. The mean friction coefficient and the heat transfer coefficient are greater by the factor 2/3 times the square root of 3.

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Document Details

Document Type
Technical Report
Publication Date
Nov 13, 1947
Accession Number
AD0604783

Entities

People

  • H. Wendt
  • W. Hantzsche

Organizations

  • RAND Corporation

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Coefficients
  • Differential Equations
  • Enthalpy
  • Equations
  • Flow
  • Friction
  • Hard Copy
  • Heat Transfer
  • Heat Transfer Coefficients
  • Laminar Boundary Layer
  • Layers
  • Potential Flow
  • Square Roots

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Ocean-Atmosphere Mesoscale Modeling, Data Assimilation, and Flux Boundary Layers

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers