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.
Study of cooling air inlet and exit geometries for horizontally opposed piston aircraft engines
Joint Propulsion Conference ; 1980 ; Hartford, CT
01.06.1980
Aufsatz (Konferenz)
Keine Angabe
Englisch
Engineering Index Backfile | 1957
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