Accession Number:

AD0514891

Title:

Simulation of Supersonic Flow over a Scale Model Missile with Aft-Mounted Inlets Using an Axisymmetric Jet Stretcher.

Descriptive Note:

Final rept. 1 Jan-30 Jun 70,

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AIR FORCE STATION TENN

Personal Author(s):

Report Date:

1971-04-01

Pagination or Media Count:

90.0

Abstract:

A complex 0.4-scale model of a Boeing air-to-ground missile having two aft-mounted inlets was utilized with a Mach 2.5 jet stretcher to determine the capability of the jet stretcher to provide accurate forebody and inlet flow simulation at 0-deg angle of attack. Basically, the jet stretcher is an aerodynamically tailored device which replaces a known streamline in the supersonic flow field about the vehicle forebody with a boundary layer corrected wall. Absolute verification of the design and fabrication procedures of the Mach 2.5 jet stretcher or its performance at design conditions was not obtained because of a Mach 2.5 nozzle flow anomaly. However, accurate inlet flow simulation using the Mach 2.5 jet stretcher was obtained. Off-design Mach number tests at Mach 2.35 and 2.70 indicate that a single jet stretcher design will provide accurate flow simulation over this range of Mach numbers, provided that the jet stretcher axial position can be optimized. Accurate flow simulation at an off-design angle of attack of 6 deg was not possible with the jet stretcher designed for 0-deg angle of attack. Author

Subject Categories:

  • Test Facilities, Equipment and Methods
  • Air- and Space-Launched Guided Missiles
  • Fluid Mechanics
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE