A Wind Tunnel Study of a Sting-Mounted Circulation Control Wing

This wind tunnel study investigated the feasibility of testing a sting mounted circulation control wing. A 20% thick, 8.5% cambered rectangular wing was designed, built, and tested in the AFIT 5-ft wind tunnel. Lift, drag, equivalent drag, and pitching moment coefficients were obtained at Reynolds n...

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Bibliographische Detailangaben
1. Verfasser:	Trainor, John W
Format:	Report
Sprache:	eng
Schlagworte:	Aerodynamics AIR FLOW AIR SUPPLIES BLOWERS CIRCULATION CONTROL WING COEFFICIENTS DISPLAY SYSTEMS DRAG FEASIBILITY STUDIES FLOW FLOW VISUALIZATION FREE STREAM IMPINGEMENT JET FLOW MOMENTS MOMENTUM NYLON PITCH(MOTION) THESES TRAILING EDGES V/STOL VERTICAL TAKEOFF AIRCRAFT WIND TUNNELS WINGS
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Beschreibung
Zusammenfassung:	This wind tunnel study investigated the feasibility of testing a sting mounted circulation control wing. A 20% thick, 8.5% cambered rectangular wing was designed, built, and tested in the AFIT 5-ft wind tunnel. Lift, drag, equivalent drag, and pitching moment coefficients were obtained at Reynolds numbers of 600,000 and 900,000. The force and moment results achieved indicate supercirculation was not present. Flow visualization with nylon tufts displayed extreme flow disruption at the trailing edge, due to free-stream impingement on both the sting and blowing air supply hoses. The available blowing air supply was not strong enough to produce a jet flow with the momentum needed to overcome this disruption. Wing model design changes were recommended to alleviate this problem.