AN APPROXIMATE ANALYSIS OF THE TWO-DIMENSIONAL, SUPERSONIC FLOW PAST A PLANE WALL WITH SUPER-CRITICAL HEAT ADDITION IN A NORMAL PLANE

Abstract

An analysis is performed to determine approximately the flow field and the normal forces acting for the two-dimensional, supersonic, zero angle-of-attack flow about a flat plate with super-critical heat addition (i.e., with thermal choking downstream) at a normal finite-height heater plane on one side of the flat plate. The results of the analysis have possible application to the design of an external thrust and/or lift producing device for airborne supersonic vehicles. Charts for the determination of the pertinent flow-field parameters and the normal force coefficients as a function of the rate of heat addition and free-stream Mach number, are presented for Mach numbers ranging from 2.0 to 7.0.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1959
Accession Number
AD0654450

Entities

People

  • Henry W. Wollard

Organizations

  • Johns Hopkins University

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Coefficients
  • Combustion
  • Flow Fields
  • Fluid Dynamics
  • Fluid Flow
  • Free Stream
  • Geometry
  • Mach Number
  • Mass Flow
  • Physics
  • Physics Laboratories
  • Pressure Distribution
  • Shock Waves
  • Standing Waves
  • Static Pressure
  • Supersonic Flow
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Thermal Physics or Thermal Science.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow