RESULTS OF RAMJET FACILITY MODEL TESTS AT MACH 11

Abstract

A test program was conducted to provide ramjet test facility bypass flow second throat diffusers pressure recovery data at a nominal nozzle exit Mach number of 11.0. During the tests, studies were made to determine the effects of Reynolds number, diffuser throat length, inlet capture, area, and other variables. The pressure recoveries obtained during the testing proved to be somewhat better than the original expectations. The peak junning pressure recovery was over 60% of free stream normal shock recovery with the adjustable diffuser. Starting pressure recoveries were somewhat lower and ranged mostly from 20% to 30% of normal shock.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1966
Accession Number
AD0484824

Entities

People

  • James L. Grunnet

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundaries
  • Boundary Layer
  • Combustion
  • Diffusers
  • Engineering
  • Engines
  • Government Procurement
  • Governments
  • Heat Transfer
  • Jet Engines
  • Measurement
  • Measuring Instruments
  • Ramjet Engines
  • Reynolds Number
  • Test Facilities
  • Throat

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.