Accession Number:

AD0783244

Title:

Simulation of Flow Approaching the Chin Inlet of a Ramjet Missile

Descriptive Note:

Final rept. 1 Jul 1972-30 Jun 1973

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Report Date:

1974-07-01

Pagination or Media Count:

43.0

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.

Subject Categories:

  • Guided Missiles
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE