An Investigation of Two Variations of the Gas Generator Method to Calculate the Thrust of the Afterburning Turbofan Engines Installed in an F-111A Airplane. Technical Report NASA Technical Note TN D-6297, Research Engineering, NASA Dryden Flight Research Center
Burcham Jr., Frank W. (1971) An Investigation of Two Variations of the Gas Generator Method to Calculate the Thrust of the Afterburning Turbofan Engines Installed in an F-111A Airplane. Technical Report NASA Technical Note TN D-6297, Research Engineering, NASA Dryden Flight Research Center.
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Abstract
The NASA Flight Research Center investigated two variations of the gas generator method for calculating the net thrust of the afterburning turbofan engines installed in an F-111A airplane. An influence coefficient study and two ground thrust tests were performed. It was found that the gas generator method can be successfully applied to an afterburning turbofan engine. At static conditions with two engines operating, plus or minus 2 percent accuracy can be achieved for most power settings using either the method based primarily on nozzle total pressure area (PTA) or the method based primarily on nozzle total temperature and weight flow (TTW). For in-flight conditions the influence coefficient results indicated that the accuracy of the TTW method was about plus or minus 3 percent, whereas the accuracy of the PTA method was about plus or minus 5 percent for a military power setting. With either calculation method, additional errors in calculated thrust of plus or minus 2 percent could result from high inlet flow distortion. If accurate thrust values are required, both thrust calculation methods should be used.
| EPrint Type: | Other |
|---|---|
| Keywords: | Afterburning turbofan engine, F-111A airplane, Gas generator method, Thrust measurement |
| Subjects: | (01 - 09) Aeronautics: (07) Aircraft Propulsion And Power Aircraft/Project: F-111 |
| ID Code: | 815 |
| Deposited On: | 16 March 2006 |
| Additional Information: | 31 pages. |
