Application of a Performance Modeling Technique to an Airplane with Variable Sweep Wings
Redin, Paul C. (1981) Application of a Performance Modeling Technique to an Airplane with Variable Sweep Wings. Technical Report NASA TP-1855, Research Engineering, NASA Dryden Flight Research Center.
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Abstract
A performance modeling concept previously applied to an F-104G and a YF-12C airplane was applied to an F-111A airplane. This application extended the concept to an airplane with variable sweep wings. The performance model adequately matched flight test data for maneuvers flown at different wing sweep angles at maximum afterburning and intermediate power settings. For maneuvers flown at less than intermediate power, including dynamic maneuvers, the performance model was not validated because the method used to correlate model and in-flight power setting was not adequate. Individual dynamic maneuvers were matched successfully by using adjustments unique to each maneuver.
| EPrint Type: | NASA Technical Publication |
|---|---|
| Keywords: | Computer modeling, TACT, F-111A airplane, Performance |
| Subjects: | (01 - 09) Aeronautics: (05) Aircraft Design, Testing And Performance Aircraft/Project: YF-12 Aircraft/Project: F-111 Aircraft/Project: F-104 |
| ID Code: | 654 |
| Deposited On: | 07 Febuary 2006 |
