AN INVESTIGATION OF THE EFFECTS OF SHOCK IMPINGEMENT ON A BLUNT LEADING EDGE

Abstract

Tests were conducted at hypersonic Mach numbers on a blunt leading edge model both with and without an impinging shock. The effects of Reynolds number, Mach number, leading edge sweep angle, and impinging shock strength on the temperature and pressure distribution for the leading edge were determined. The tests were conducted at nominal Mach numbers of 6, 8, and 10 unit Reynolds numbers of 580,000 to 3,550,000 per foot with a sweep angle range of 0 to 75 deg. Selected results which show the effect of shock generator angle and sweep angle at Mach 6 and 10 are presented.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1965
Accession Number
AD0466166

Entities

People

  • A. D. Ray
  • R. L. Palko

Organizations

  • Arnold Engineering Development Complex

Tags

DTIC Thesaurus Topics

  • Abstracts
  • Air Force
  • Contractors
  • Flow
  • Free Stream
  • Generators
  • Government Procurement
  • Governments
  • Heat Transfer
  • Heat Transfer Coefficients
  • Instrumentation
  • Leading Edges
  • Mach Number
  • Photography
  • Pressure Distribution
  • Reynolds Number
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Combustion Dynamics and Shock Wave Physics.

Technology Areas

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