Abstract
This paper discusses the method of evaluating supersonic-aircraft inlet steady-state pressure defects and random pressure fluctuations (turbulence) used for the purpose of establishing inlet engine compatibility for the TF30 engine. This technique has evolved from TF30/F-111 compatibility studies over the last several years and has resulted in a unique yet practical method of determining engine-inlet compatibility associated with applications of the TF30 series. A review is made of the development of a distortion factor for steady-state inlet pressure distortion, its basic inability to handle the dynamic pressure variations, the evaluation of this turbulence, and development of a technique to evaluate turbulence effect on engine stability margin.
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