FORCE BALANCE DETERMINATION OF INLET PERFORMANCE FOR ADVANCED VEHICLE APPLICATIONS TO ORBITAL VELOCITIES USING INTERNAL DRAG MEASUREMENTS,

Abstract

The problem of determining performance levels of supersonic/hypersonic combustion inlet models is presented. Previous approaches to this problem are discussed and g40thod involving force balance determination of the internal drag is proposed. Results of a computational procedure formulated for calculating inlet performance levels from measured internal drag values are presented. Effects of chemical reactions and exit flow profile nonuniformity are accounted for. Levels of anticipated accuracy, using this technique, are adequate for present applications over a Mach Number range of 8 to 25. (Author)

Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1963
Accession Number
AD0426728

Entities

People

  • Paul H. Kutschenreuter

Tags

DTIC Thesaurus Topics

  • Accuracy
  • Air Force
  • Air Force Facilities
  • Chemical Reactions
  • Combustion
  • Engineering
  • Mach Number
  • Measurement
  • Motion
  • Physical Properties

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Combustion and Flow Dynamics.
  • Operations Research

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow
  • Space
  • Space - Hall-Effect Thruster
  • Space - Orbital Debris