Abstract
An extensive wind-tunnel investigation was conducted to determine airplane installation effects on isolated inlet performance. This investigation was accomplished by a series of tests involving several models to determine a) isolated inlet component internal performance, b) forebody flowfield, and c) installed inlet/forebody internal performance. The airplane system application for the results was a multimission strategic airplane. A semiempirical approach is developed which relates the isolated component performance of the inlet to the flowfield properties in the vicinity of its location on the airplane. Influence coefficients involving rates of change of inlet recovery with uniform changes in local flow properties such as Mach number, upwash, and sidewash and for induced gradients in Mach number are derived from the isolated inlet tests. These are then combined with the average local flow properties measured on the forebody to predict the installed inlet recovery. The comparison of predicted and measured installed inlet recovery suggests that experimentally derived influence coefficients obtained from component research can be used for airplane design accountability.
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