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- W2022721261 abstract "A semispan wing and nacelle of a typical general aviation twin-engine aircraft was tested to evaluate the cooling capability and drag of several nacelle shapes; the nacelle shapes included cooling air inlet and exit variations. The tests were conducted in the Ames Research Center's 40- by 80-Foot Wind Tunnel. It was found that the cooling air inlet geometry of opposed piston engine installations has a major effect on inlet pressure recovery, but only a minor effect on drag. Exit location showed a large effect on drag, especially for those locations on the sides of the nacelle where the suction characteristics were based on interaction with the wing surface pressures." @default.
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- W2022721261 date "1980-06-30" @default.
- W2022721261 modified "2023-09-25" @default.
- W2022721261 title "Study of cooling air inlet and exit geometries for horizontally opposed piston aircraft engines" @default.
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