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Effect of propeller slipstream on the drag and performance of the engine cooling system for a general aviation twin-engine aircraftThe pressure recovery of incoming cooling air and the drag associated with engine cooling of a typical general aviation twin-engine aircraft was investigated experimentally. The semispan model was mounted vertically in the 40- by 80-Foot Wind Tunnel at Ames Research Center. The propeller was driven by an electric motor to provide thrust with low vibration levels for the cold-flow configuration. It was found that the propeller slipstream reduces the frontal air spillage around the blunt nacelle shape. Consequently, this slipstream effect promotes flow reattachment at the rear section of the engine nacelle and improves inlet pressure recovery. These effects are most pronounced at high angles of attack, that is, climb condition. For the cruise condition those improvements were more moderate.
Document ID
19800059145
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Katz, J.
(NASA Ames Research Center Moffett Field, CA, United States)
Corsiglia, V. R.
(NASA Ames Research Center Moffett Field, CA, United States)
Barlow, P. R.
(NASA Ames Research Center Moffett Field, Calif., United States)
Date Acquired
August 10, 2013
Publication Date
August 1, 1980
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 80-1872
Meeting Information
Meeting: Aircraft Systems Meeting
Location: Anaheim, CA
Start Date: August 4, 1980
End Date: August 6, 1980
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
80A43315
Distribution Limits
Public
Copyright
Other

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