Carina Aerothermal Test at Mach 8

Abstract

The test articles were scale models of the Carina Space Recovery Vehicle. Carina is an axisymmetric model of a blunt, low lift-to-drag reentry vehicle. Surface pressure, heat transfer, force and moment, base pressure, and oil flow visualization data were acquired on four model configurations of the Carina Space Recovery Vehicle. The test was conducted in the AEDC Hypersonic Wind Tunnel B at Mach 8 and free-stream Reynolds number of 0.75, 1.0, and 2.0 million per foot. Angle of attack was varied from 0 to 20 deg at roll angles of -180 to 180 deg.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1991
Accession Number
ADA238561

Entities

People

  • M. G. Hammond

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Advanced Electronics
  • Air Platforms
  • Human Systems
  • Space

DTIC Thesaurus Topics

  • Air Force
  • Base Pressure
  • Boundary Layer
  • Flow
  • Flow Visualization
  • Free Stream
  • Heat Transfer
  • Heat Transfer Coefficients
  • Hypersonic Wind Tunnels
  • Pressure Measurement
  • Recovery Vehicles
  • Reynolds Number
  • Surface Temperature
  • Test Facilities
  • Vehicles
  • Visualizations
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow
  • Space
  • Space - Hall-Effect Thruster