Scale Model Propulsion Simulator for Supersonic Aircraft.
Final rept. 1 Jul 69-1 Jun 71,
TECH DEVELOPMENT INC DAYTON OHIO*
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The purpose of the program was to develop an engine simulator which will provide simultaneous simulation of the inlet and exhaust flow fields in a full span, supersonic aircraft wind tunnel model. The simulator was designed to match the engine characteristics of exhaust nozzle pressure ratio and nozzle flow function vs. inlet corrected airflow. This match will exist over the full mission profile of altitude and Mach number including the full reheat, full dry and part power dry operation. Aerodynamically, the unit consists of two basic elements A four-stage axial flow compressor with no bleed provisions, pressure ratio 2.8. A single-stage high pressure drive turbine. A portion of the turbine exhaust is throttled into the exhaust nozzle inlet and mixed with the compressor discharge flow to obtain the required exhaust flow. Temperature is not simulated in this model, but a hydrogen burner could be added at a later date. The limited compressor performance data obtained are summarized. Author
- Jet and Gas Turbine Engines