Maneuvering Aerothermal Technology (MAT) Program. A Method for Coupled Three-Dimensional Inviscid and Integral Boundary Layer Calculations

Abstract

A procedure is developed for computing the complete flow field over maneuvering reentry vehicles by coupling a finite difference inviscid flow field code to an integral boundary layer procedure. Viscous calculations are performed along inviscid surface streamlines, which are explicitly computed in the inviscid code. The detailed inviscid flow field solution is used to accurately define the required boundary layer edge properties. The boundary layer procedure can treat laminar, transitional, or turbulent flows, and surface roughness and mass addition effects. Approximate techniques are provided to define the wall temperatures and mass addition rates of ablating heatshields.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1982
Accession Number
ADA123468

Entities

People

  • Alvin L. Murray
  • Calvin J. Wolf
  • Darryl W. Hall
  • Thomas B. Harris

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Ablative Materials
  • Ballistic Missiles
  • Boundary Layer
  • Boundary Layer Flow
  • Experimental Data
  • Fluid Dynamics
  • Geometry
  • Graphitic Materials
  • Heat Flux
  • Heat Transfer
  • Mach Number
  • Pressure Distribution
  • Radial Velocity
  • Surface Temperature
  • Thermodynamics
  • Three Dimensional
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Missile Defense Systems.