A wind tunnel investigation of the engine exhaust and windstream flow interaction on a gunship helicopter model was conducted in the Langley V/STOL tunnel. The investigation utilized a flow visualization technique employing neutrally buoyant helium filled bubbles to determine the cause of exhaust shield overheating during cruising flight and to evaluate means of eliminating the problem. The flow patterns were recorded with still cameras and on television magnetic tape. Exhaust flow impingement on the exhaust shield during cruise was found to cause the problem. Several flow altering devices were evaluated to find suitable ways to correct the problem. A flow deflector located on the model cowling upstream of the exhaust provides an effective solution.
Wind tunnel investigation of a simulated gunship helicopter engine-exhaust-windstream interaction
1974-12-01
Report
No indication
English
An Experimental Wind Tunnel Investigation to Reduce the Drag on the AC-130U Gunship
British Library Conference Proceedings | 1999
|