Hypersonic Wind Tunnel Study of a 15 deg-30 deg Half Angle Concave Biconic Model Up to High Angles of Attack.

Abstract

Heat transfer and pressure measurements have been measured on a 15 - 30 deg half angle biconic model with a blunt nosetip in the von Karman Institute Longshot free piston tunnel at Mach 15 and 20 Reynolds numbers between one and five million based on model base diameter. The test flow parameter closely simulated re-entry aerodynamic conditions. The angle of attack of the model was varied from 0 to 20 deg. Information derived from the measurements and also schlieren pictures enabled understanding of the effects of Mach number, Reynolds number and flow incidence on the flow over the model and the location and size of heat transfer peaks. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1979
Accession Number
ADA088129

Entities

People

  • Bryan E. Richards

Organizations

  • von Kármán Institute for Fluid Dynamics

Tags

Communities of Interest

  • Air Platforms
  • Cyber
  • Sensors
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Diameters
  • Fluid Dynamics
  • Heat Transfer
  • High Angles
  • Hypersonic Wind Tunnels
  • Mach Number
  • Measurement
  • Photographs
  • Photography
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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