A cooperative numerical investigation involving researchers from McDonnell Douglas Helicopter Systems (MDHS), the US Army Aeroflightdynamics Directorate (AFDD) and the NASA Ames Research Center (ARC) was conducted to identify the cause, as well as the solution(s), to a pilot‐reported
horizontal and vertical tail buffeting problem on the Longbow Apache AH‐64D helicopter in low speed descent flight. The investigation was conducted using the NASA Ames steady, three‐dimensional, compressible Euler code, “TIGER.” With the exception of the rotor, all
geometric details of the flight test aircraft were modeled. Grid adaptation of a Cartesian computational grid near and on the surface of the configuration was used to preserve geometric integrity and solution accuracy. Flowfield diagnostics were performed using a combination of streamwise
particle trajectories and cross flow vorticity plots. Numerical results indicated that two potential contributors, namely the blunt bases of the two side‐mounted extended forward avionics bays (EFABS) and the bases of the two channel‐like grooves created as a result of the attachment
of the EFABS to the fuselage, were responsible for the shedding of high levels of vorticity which convected downstream and impacted the surfaces of the empenage. To reduce the observed levels of shed vorticity, three geometric modifications to the baseline helicopter fuselage configuration
were made. A flight test program for the helicopter with a number of suggested modifications was conducted to verify their effectiveness on resolution of the tail buffet problem. Numerical results and supporting flight test data confirming the effectiveness of the geometric modifications are
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Document Type: Research Article
The Boeing Company, Mesa, Arizona
Publication date: 01 January 1999
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