EVALUATION OF A THRUSTMETER FOR MEASURING IN-FLIGHT THRUST OF TURBOJET ENGINES.
NATIONAL AVIATION FACILITIES EXPERIMENTAL CENTER ATLANTIC CITY N J
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Laboratory tests indicated that 1 the gross thrust value computed theoretically from the measured pressures were within plus or minus 2.0 of the thrust stand measured gross thrust, 2 the thrustmeter gross thrust values were within plus or minus 3.0 of the thrust stand measured values, 3 the net thrust values computed theoretically from the measured pressures were within plus or minus 3.9 of the thrust stand measured net thrust, and 4 the thrustmeter net thrust values were within plus or minus 4.2 of the thrust stand measured net thrust. The gross thrust computer module malfunctioned for a series of tests at a simulated altitude condition of 40,000 feet and Mach 1.2. Flight test results indicated that the system functioned properly aboard the aircraft and was responsive to small changes in engine power setting. The thrustmeter gross thrust and net thrust values agreed with the computed gross and net thrust of the engine within plus or minus 2.2 and plus or minus 2.8 respectively. In measuring net thrust during the flight tests, some difficulty was encountered in obtaining consistent static pressure readings at the compressor inlet station thus causing errors in the computation of ram drag. Author
- Test Facilities, Equipment and Methods
- Jet and Gas Turbine Engines