| 摘要 |
There is provided a method to account for aircraft angle of attack effects in engine noise shielding in aircraft configurations having one or more engines mounted above a wing or a lifting body. The method includes computing a local flow field from a known standard full aircraft configuration oriented at a nonzero angle of attack. The method further includes computing a mean flow field in a test dataset from a small scale aircraft model test configuration oriented at a zero angle of attack. The method further includes matching the local flow field with the mean flow field to identify a selected noise measurement dataset. The method further includes rotating 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. |
