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Experimental and numerical study of the British Experimental Rotor Programme bladeWind-tunnel tests on the British Experimental Rotor Programme (BERP) tip are described, and the results are compared with computational fluid dynamics (CFD) results. The test model was molded using the Lynx-BERP blade tooling to provide a semispan, cantilever wing comprising the outboard 30 percent of the rotor blade. The tests included both surface-pressure measurements and flow visualization to obtain detailed information of the flow over the BERP tip for a range of angles of attack. It was observed that, outboard of the notch, favorable pressure gradients exist which ensure attached flow, and that the tip vortex also remains stable to large angles of attack. On the rotor, these features yield a very gradual break in control loads when the retreating-blade limit is eventually reached. Computational and experimental results were generally found to be in good agreement.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Brocklehurst, Alan
(Westland Helicopters, Ltd. Yeovil, United Kingdom)
Duque, Earl P. N.
(NASA Ames Research Center; U.S. Army, Aeroflightdynamics Directorate, Moffett Field CA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1990
Subject Category
Report/Patent Number
AIAA PAPER 90-3008
Meeting Information
Meeting: AIAA Applied Aerodynamics Conference
Location: Portland, OR
Country: United States
Start Date: August 20, 1990
End Date: August 22, 1990
Accession Number
Distribution Limits

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