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- W2080376060 abstract "A low-speed wind tunnel test was conducted in the NASA/Ames 40-x-80-foot wind tunnel to investigate the effect of engine/inlet flowfield interaction on inlet performance near flow separation. The effect of engine/inlet flowfield interaction was determined by comparing the performance of a large-scale subsonic inlet (CR = 1.26) close-coupled and remote-coupled to a TF-34 turbofan engine. The remote coupled inlet configuration removes the influence of the engine on the inlet flowfield and further, typifies conventional small-scale inlet test techniques which generally provide no simulation of turbomachinery effects. Test results indicated that engine interaction allows the inlet to operate with lower distortion levels at and beyond the separation angle-of-attack attained without engine interaction." @default.
- W2080376060 created "2016-06-24" @default.
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- W2080376060 date "1981-08-17" @default.
- W2080376060 modified "2023-10-02" @default.
- W2080376060 title "A large-scale investigation of engine influence on inlet performanceat angle-of-attack" @default.
- W2080376060 doi "https://doi.org/10.2514/6.1981-2481" @default.
- W2080376060 hasPublicationYear "1981" @default.
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