The performance and distortion levels of the right inlet of the F/A-18A High Alpha Research Vehicle were assessed during maneuvers with rapidly changing angle-of-attack at the NASA Dryden Flight Research Center, Edwards, California. The distortion levels were compared with those produced by current inlet-engine compatibility evaluation techniques. The objective of these analyses was to determine whether the results obtained for steady aerodynamic conditions were adequate to describe the inlet-generated distortion levels that occur during rapid aircraft maneuvers. Levels of inlet recovery, peak dynamic circumferential distortion, and peak dynamic radial distortion of dynamic maneuvers for a General Electric F404-GE-400 turbofan engine were compared with estimations based on steady aerodynamic conditions. The comparisons were performed at equivalent angle-of-attack, angle-of-sideslip, and Mach number. Results showed no evidence of peak inlet distortion levels being elevated by dynamic maneuver conditions at high angle-of-attack compared with steady aerodynamic estimations. The dynamic maneuvers were shown to be effective at identifying conditions when discrete changes in inlet behavior occur.
F/A-18A Inlet Flow Characteristics During Maneuvers with Rapidly Changing Angle of Attack
1997
24 pages
Report
No indication
English
Aerodynamics , Aircraft , Jet & Gas Turbine Engines , Research vehicles , Angle of attack , Turbofan engines , Aircraft maneuvers , Inlet flow , Flow characteristics , Wind tunnel tests , Pressure measurement , F-18 aircraft , Distortion , Sideslip , Dynamic characteristics , Pressure effects , Subsonic speed , Steady state , Data correlation
Forebody Flow Control for Extended High-Angle-of-Attack Maneuvers
Online Contents | 1998
|