Measured AEDC Tunnel B and Predicted Linear Stability Theory Transition Comparison Study for a 7-Degree Sharp Cone.

Abstract

The location of the stability region between the laminar and turbulent flow is of great importance in the design of high speed missiles and aircraft's. Heat transfer and skin friction vary greatly between laminar and turbulent, therefore, transition location is indispensable for predicting vehicle performance. The boundary layer stability of a sharp, 7-degree half angle cone with freestream Mach numbers of 6 and 8 was numerically investigated using linear stability theory computer program. Results were compared with wind tunnel tests results obtained at the AEDC Von Karman Hypersonic Tunnel B. Measured and computed frequencies agree well, indicating that linear stability theory properly describes the processes leading to transition at the AEDC Tunnel B.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1996
Accession Number
ADA310763

Entities

People

  • Albert A. Rougeux

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Boundary Layer Control
  • Computer Programs
  • Computers
  • Equations
  • Frequency
  • Heat Transfer
  • Hot Wire
  • Layers
  • Mach Number
  • Measurement
  • Phase Velocity
  • Two Dimensional
  • Wave Propagation
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Atmospheric Science / Meteorology, specifically Wind Wave Turbulence.
  • Combustion and Flow Dynamics.
  • Control Systems Engineering.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers