An Approximate Method for Determining the Displacement Effects and Viscous Drag of Laminar Boundary Layers in Two-Dimensional Hypersonic Flow

Abstract

A simplified approximate theory is presented by means of which the laminar boundary layer over an insulated two-dimensional surface may be calculated, a linear velocity profile being assumed, and an estimate made of its effect in changing the pressure distribution over the profile upon which the boundary layer is formed. Skin friction is also determined. Comparisons of results from this theory are made with experimental results at a Mach number of 6.86 and a Reynolds number of 980,000.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1952
Accession Number
ADA377170

Entities

People

  • Mitchel H. Bertram

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Boundary Layer
  • Differential Equations
  • Equations
  • Flow Fields
  • Fluid Dynamics
  • Free Stream
  • Hypersonic Flow
  • Laminar Boundary Layer
  • Mach Number
  • Pressure Distribution
  • Pressure Gradients
  • Pressure Measurement
  • Skin Friction
  • Stagnation Temperature
  • Static Pressure
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Microelectronics
  • Microelectronics - Graphene