Flow Disturbanced Due to Wall Irregularities in Two-Dimensional Supersonic Flow. The Magnitude and Lateral Extent of Disturbance For Mach Numbers Between 1.05 and 1.25

Abstract

A method is presented for computing the lateral extent of a weak shock wave due to a small wedge-shaped irregularity of a wall in two-dimensional supersonic flow. Computations have been carried out over the Mach number range 1.05 to 1.25 for angular irregularities of the wall of 0.1 to 0.4 degrees. The entropy change in the shock wave as well as the influence of the wall boundary layer were assumed to be negligible.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1950
Accession Number
ADA377320

Entities

People

  • Jean G. Goppert

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Boundaries
  • Boundary Layer
  • Computations
  • Flow
  • Free Stream
  • Geometry
  • Layers
  • Mach Number
  • Security
  • Shock
  • Shock Waves
  • Supersonic Flow
  • Two Dimensional
  • Waves
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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