A wind tunnel experiment was conducted in the NASA Langley Research Center (LaRC) Unitary Plan Wind Tunnel (UPW7) to determine the effects of passive surface porosity on vortex flow interactions about a general research fighter configuration at supersonic speeds. Optical flow measurement and flow visualization techniques were used and included pressure-sensitive paint (PSP), schlieren, and laser vapor screen (LVS). These techniques were combined with force and moment and conventional electronically-scanned pressure (ESP) measurements to quantify and to visualize the effects flow-through porosity applied to a wing leading-edge extension (LEX) mounted to a 65 deg cropped delta wing model.
Effects of Passive Porosity on Interacting Vortex Flows at Supersonic Speeds
Flow Visualization ; 2000 ; Edinburgh, Scotland, United Kingdom
2000-01-01
Preprint
No indication
English
Vortex Flows at Supersonic Speeds
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