Wind Tunnel Testing of a Windshield Material for Supersonic Aircraft

Abstract

Wind tunnel tests of windshield material intended for use on supersonic aircraft were conducted in the von Karman Facility Hypersonic Wind Tunnel B at a free-stream Mach number of 6 and tunnel stilling chamber conditions of 146 psia and 495 F. The wedge technique was used to provide a local Mach number of 2.5 over the windshield specimen. Selected results are presented to illustrate the test techniques and typical data obtained.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1981
Accession Number
ADA103383

Entities

People

  • A. S. Hartman
  • D. W. Stallings

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms
  • Space

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Cameras
  • Data Reduction
  • Digital Data
  • Flow Fields
  • Heat Transfer
  • Heat Transfer Coefficients
  • Instrumentation
  • Mach Number
  • Measurement
  • Photographs
  • Photography
  • Pressure Measurement
  • Test Facilities
  • Test Fixtures
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Combustion and Flow Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow