Calculation Techniques for Inviscid Two-Dimensional Supersonic Airflow.

Abstract

Techniques for calculating the change in properties of inviscid supersonic airflow passing over or through various two-dimensional bodies are discussed in this report. Low supersonic (M less than 4) airflows and high supersonic (M greater than 4) airflows are considered separately. Flow phenomena considered include normal shock waves, oblique shock waves, insentropic expansions, and conical shock waves for cones at zero degrees angle of attack. The adjustments required for swept wings are also discussed. Printouts of computer subroutines designed to carry out the described calculation procedures are included in an appendix to the report. Examples describing the use of the calculation techniques and computer subroutines for a swept wing, and for two typical ramjet inlets are included. A final appendix includes charts that can be used as calculation aids for airflows at Mach numbers up to 4. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1979
Accession Number
ADA085327

Entities

People

  • M. Brian Bergsten

Organizations

  • Air Force Research Laboratory

Tags

Communities of Interest

  • Energy and Power Technologies
  • Materials and Manufacturing Processes
  • Space

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Air Force
  • Air Force Facilities
  • Back Pressure
  • Computational Fluid Dynamics
  • Computer Programs
  • Computers
  • Fluid Dynamics
  • Fluid Mechanics
  • Mach Number
  • Pressure Distribution
  • Procedures (Computers)
  • Ramjet Engines
  • Static Pressure
  • Swept Wings
  • Thermodynamic Properties
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Computer Science.
  • Structural Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers