Space Shuttle Windward Streamline Laminar Viscous Shock-Layer Flows at Angle of Attack--Comparison of Theory and Experiment,

Abstract

Comparisons have been made between a perfect gas laminar viscous shock layer method and experimental data from the AEDC/vKF Hypersonic Tunnels. The test model was the Rockwell International 139 Shuttle Orbiter, and the data taken included wall pressure distributions, heat-transfer distributions, stagnation temperature and pitot pressure profiles through the shock layer. Comparisons were made at Mach numbers of 8, 11 and 14, with Reynolds numbers ranging from 520,000 to 1.0 x 10 to the 7th power per foot and angles of attack from 0 to 45 degrees. Comparisons showed good to excellent agreement except at very low angles of attack where the axisymmetric solution did not model well the flat bottom of the orbiter.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
May 01, 1976
Accession Number
ADA042843

Entities

People

  • Alvin L. Murray
  • Clark H. Lewis
  • John D. Waskiewicz

Organizations

  • Virginia Tech

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Differential Equations
  • Engineering
  • Equations
  • Experimental Data
  • Flow
  • Geometry
  • Heat Transfer
  • Low Angles
  • Mach Number
  • Partial Differential Equations
  • Pressure Distribution
  • Reynolds Number
  • Skin Friction
  • Stagnation Temperature
  • Two Dimensional
  • Virginia

Fields of Study

  • Physics

Readers

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

Technology Areas

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