Simulation of Flow Approaching the Chin Inlet of a Ramjet Missile

Abstract

A new Aerodynamic and Propulsion Test Unit (APTU) is being constructed at AEDC for testing air-breathing missiles that operate at supersonic Mach numbers. One type of missile configuration that may be tested in the APTU is that having a forward-located chin inlet. A technique for simulating the flow approaching a chin inlet is studied within the limitations of test body size, nozzle size, and diffuser performance expected in the APTU. Analytical techniques are presented for positioning the test body to obtain maximum altitude simulation and for estimating the general diffuser performance and starting conditions. A consideration of the flow processes that limit diffuser performance in a conventional test arrangement led to the concept of extending the diffuser over the test body.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1974
Accession Number
AD0783244

Entities

People

  • C. R. Tinsley
  • R. C. Bauer
  • W. W. Muse

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Breathing
  • Air Force
  • Altitude
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computer Programs
  • Contracts
  • Diffusers
  • Engineering
  • Flow Fields
  • High Pressure
  • Mach Number
  • Pressure Distribution
  • Simulations
  • Static Pressure
  • Steady State
  • Test Facilities

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Dynamics.
  • Military Engineering.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow