Performance Technology Program (PTP-S II). Volume III. Inviscid Aerodynamic Predictions for Ballistic Reentry Vehicles with Ablated Nosetips

Abstract

A three-dimensional inviscid time-dependent blunt body flow field code is developed for calculation of hypersonic flow over ablated reentry vehicle nosetips. The code is formulated in a coordinate system that is based on a sequence of conformal mappings and is capable of being aligned with arbitrary nosetip shapes. This procedure includes a finite difference scheme that permits the automatic calculation of embedded shocks in an approximate manner. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1979
Accession Number
ADA108845

Entities

People

  • Darryl W. Hall

Tags

Communities of Interest

  • Air Platforms
  • Cyber
  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aerodynamics
  • Altitude
  • Boundary Layer
  • Bow Shock
  • Cartesian Coordinates
  • Computational Fluid Dynamics
  • Computational Science
  • Conformal Mapping
  • Coordinate Systems
  • Differential Equations
  • Equations Of Motion
  • Fluid Dynamics
  • Fluid Flow
  • Geometry
  • Pressure Distribution
  • Three Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Computer Vision.
  • Missile Defense Systems.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers