Leeside Crossflow Modeling in Euler Space-Marching Computations

Abstract

A simple method has been developed to model crossflow separation for inviscid (Euler type) computations by suppressing the crossflow velocity near the body surface. The method has been validated for a tangent-ogive-cylinder body of circular cross-section and shown to be useful at supersonic speeds at low to intermediate angles of incidence (M < 5, alpha < 20 deg). At low March numbers (M < 3) the method offers a significant improvement in the inviscid leeside surface pressure distributions and also yields improved predictions of aerodynamic coefficients. In this report the algorithm for a tangent-ogive- cylinder body is described and comparisons of numerical and experimental data are presented.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1986
Accession Number
ADA175903

Entities

People

  • A. B. Wardlaw Jr.
  • F. P. Baltakis
  • J. M. Allen

Organizations

  • Naval Ordnance Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Aircrafts
  • Algorithms
  • Boundary Layer
  • Coefficients
  • Computational Fluid Dynamics
  • Computations
  • Earth Sciences
  • Engineering
  • Experimental Data
  • Geography
  • Geometry
  • Mach Number
  • Mechanical Engineering
  • Molecular Dynamics
  • Physics Laboratories
  • Pressure Distribution

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Computational Fluid Dynamics (CFD)
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Space
  • Space - Hall-Effect Thruster