In-Flight Flow Visualization Characteristics of the NASA F-18 High Alpha Research Vehicle at High Angles of Attack 892222
Surface and off-surface flow visualization techniques have been used to visualize the three-dimensional separated flows on the NASA F-18 high alpha research vehicle (HARV) at high angles of attack. Results near α = 25° to 26° and α = 45° to 49° are presented. Both the fore-body and leading-edge extension (LEX) vortex cores and breakdown locations were visualized using smoke. Fore-body and LEX vortex separation lines on the surface were defined using an emitted fluid technique. A laminar separation bubble was also detected on the nose cone using the emitted fluid technique and was similar to that observed in the wind-tunnel test, but not as extensive. Regions of attached, separated, and vortical flow were noted on the wing and the leading-edge flap using tufts and flow cones, and compared well with limited wind-tunnel results.
Citation: Fisher, D., Del Frate, J., and Richwine, D., "In-Flight Flow Visualization Characteristics of the NASA F-18 High Alpha Research Vehicle at High Angles of Attack," SAE Technical Paper 892222, 1989, https://doi.org/10.4271/892222. Download Citation
David F. Fisher, John H. Del Frate, David M. Richwine
NASA Ames Research Center Dryden Flight Research Facility Edwards, CA 93523-5000, PRC System Services Edwards, CA 93523-5000
Aerospace Technology Conference and Exposition
SAE Transactions Journal of Aerospace-V98-1