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Cooling Air Inlet and Exit Geometries on Aircraft Engine InstallationsA semispan wing and nacelle of a typical general aviation twin-engine aircraft was tested to evaluate the cooling capability and drag or several nacelle shapes; the nacelle shapes included cooling air inlet and exit variations. The tests were conducted in the Ames Research Center 40 x 80-ft 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 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.
Document ID
Document Type
Reprint (Version printed in journal)
Katz, Joseph (NASA Ames Research Center Moffett Field, CA United States)
Corsiglia, Victor R. (NASA Ames Research Center Moffett Field, CA United States)
Barlow, Philip R. (NASA Ames Research Center Moffett Field, CA United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1982
Publication Information
Publication: Journal of Aircraft
Volume: 19
Issue: 7
Subject Category
Aircraft Propulsion and Power
Report/Patent Number
AIAA Paper 80-1242
NAS 1.15:208073
Meeting Information
Joint Propulsion(Hartford, CT)
Distribution Limits
Work of the US Gov. Public Use Permitted.

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NameType 19980214918.pdf STI