An Inviscid Computational Method for Supersonic Inlets.

Abstract

An extension to the SWINT code is described which permits inviscid calculations to be performed on the supersonic portion of inlet flow fields. Also described is an interface program which rezones the external flow field applied to several examples. A listing of the extension to SWINT and the interface program are provided in the Appendices along with a set of user instructions and a sample case. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Mar 22, 1984
Accession Number
ADA145997

Entities

People

  • A. B. Wardlaw Jr.
  • D. Shumway
  • F. Baltakis

Organizations

  • Naval Ordnance Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Air Force
  • Aircrafts
  • Boundary Layer
  • Bow Shock
  • Coefficients
  • Computational Fluid Dynamics
  • Computational Science
  • Discontinuities
  • Equations
  • Errors
  • Flow Fields
  • Free Stream
  • Plastic Explosives
  • Shape
  • Static Pressure
  • Three Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Computer Science.

Technology Areas

  • Hypersonics