Evaluation of a Simplified Gross Thrust Calculation Technique Using Two Prototype F100 Turbofan Engines in an Altitude Facility. Technical Report NASA Technical Paper TP-1482, Research Engineering, NASA Dryden Flight Research Center
Kurtenbach, Frank J. (1979) Evaluation of a Simplified Gross Thrust Calculation Technique Using Two Prototype F100 Turbofan Engines in an Altitude Facility. Technical Report NASA Technical Paper TP-1482, Research Engineering, NASA Dryden Flight Research Center.
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Abstract
A simplified gross thrust calculation technique was evaluated in an altitude facility using two prototype F100-PW-100 engines. The technique relies on afterburner duct pressure measurements and empirical corrections to an ideal one-dimensional flow analysis to determine thrust. This report presents a comparison of the calculated and facility measured thrust values. It also compares the simplified model with the engine manufacturer's gas generator model. The evaluation was conducted over a range of Mach numbers from 0.80 to 2.00 and at altitudes from 4020 meters to 15,240 meters. The effects of variations in inlet total temperature from standard day conditions were explored. Engine conditions were varied from those normally scheduled for flight. The technique was found to be accurate to a twice standard deviation of 2.89 percent, with accuracy a strong function of afterburner duct pressure difference.
| EPrint Type: | Other |
|---|---|
| Keywords: | Engine performance, Gross thrust |
| Subjects: | (01 - 09) Aeronautics: (07) Aircraft Propulsion And Power |
| ID Code: | 1113 |
| Deposited On: | 11 October 2006 |
| Additional Information: | 30 pages. |
