THE FLOW ABOUT THE LEADING EDGE OF A SWEPT BLUNT PLATE AT HYPERSONIC SPEEDS

Abstract

As part of a fundamental study of hypersonic wings, some detailed pressure distribution and heat transfer results were obtained over sections of the leading edge region of a blunt plate at sweep angles from zero to 75 degrees. The tests were carried out in a Helium hypersonic wind tunnel at Mach numbers from 7 to 17. Some effects of the apex or upstream boundary of the plate on the leading edge regions under study were determined at various stations along the leading edge. The leading edge regions examined showed deviations from normal Mach number considerations at high sweep angles over the entire Mach number range studied.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1962
Accession Number
AD0290942

Entities

People

  • C. C. Horstman
  • I. E. Vas

Organizations

  • Princeton University

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Boundaries
  • Boundary Layer
  • Computational Fluid Dynamics
  • Data Reduction
  • Equations
  • Heat Transfer
  • Heat Transfer Coefficients
  • Hypersonic Wind Tunnels
  • Leading Edges
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Swept Wings
  • United States
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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