Laminar-Boundary-Layer Heat-Transfer Characteristics of a Body of Revolution with a Pressure Gradient at Supersonic Speeds

Abstract

Local rates of heat transfer have been measured over the negative Pressure gradient region of a pointed body of revolution with a fineness ratio of 6:l,% a vertex angle of 370, and a contour generated' by rotating a segment of a parabola. data have been obtained with a lazainar boundary layer at three 3eynolds numbers at a mach number of 1.49 and two reynolds numbers at a mach number of 2.18. The results of this investigation indicate that the heat transfer characteristics of the parabolic body can be predicted by employing the theoretical relationship between Nusselt nun% ber and %ynolds number for conical bodies.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1950
Accession Number
ADA380440

Entities

People

  • Richard Scherrer
  • William R. Wimbrow

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Boundary Layer
  • Conical Bodies
  • Equations
  • Geometry
  • Heat Transfer
  • Laminar Boundary Layer
  • Mach Number
  • Measurement
  • Measuring Instruments
  • Parabolic Bodies
  • Pressure Distribution
  • Pressure Gradients
  • Reynolds Number
  • Surface Temperature
  • Temperature Gradients
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.

Technology Areas

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