Patent ID: 8532961

Claim:
A method to account for aircraft angle of attack effects in engine noise shielding tests in aircraft configurations having one or more engines mounted above a wing or a lifting body, the method implemented using a computer software program product stored on a computer readable storage medium on a computer, the method comprising: computing with a computer software program product stored on a computer readable storage medium on a computer a local flow field from a full aircraft configuration oriented at a nonzero angle of attack to obtain a computed overall local flow output computed from one or more local flow parameters comprising a Mach number distribution, a velocity vector field, a total pressure, and a total temperature, the full aircraft configuration comprising a hybrid wing body aircraft having one or more engines mounted above a wing or a lifting body of the hybrid wing body aircraft; computing with the computer software program product on the computer a mean flow field in a test dataset from an aircraft model test configuration oriented at a zero angle of attack to obtain one or more test conditions comprising a Mach number distribution, a velocity vector field, a total pressure, and a total temperature, the aircraft model test configuration comprising one or more engines mounted over a flat plate; comparing with the computer software program product on the computer the local flow field with the mean flow field to identify a selected noise measurement dataset; and, rotating with the computer software program product on the computer the selected noise measurement dataset in a far field directivity rotation angle to match the nonzero angle of attack, thus resulting in engine noise shielding results for the full aircraft configuration at the nonzero angle of attack.