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Analytical Studies on the Effects of Cooling Flows on Light Aircraft Drag
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English
Abstract
A source-paneling body analysis computer program was modified to permit arbitrary panels to be opened to receive or exhaust cooling air flow. It was found that exhausting the cooling air into concave regions such as before the windshield or behind the canopy resulted in decreased drag, probably because of the streamlining effects of the airflow. This suggests that the drag of single-engine light aircraft could be reduced by redesigning the cowl to entrap air below the propeller axis and exhaust the cooling portion of it (but not the engine exhaust) through flush ports in front of the windshield.
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Authors
Citation
Fox, S. and Smetana, F., "Analytical Studies on the Effects of Cooling Flows on Light Aircraft Drag," SAE Technical Paper 810577, 1981, https://doi.org/10.4271/810577.Also In
References
- Fox S. R. Smetana F. O. “An Analytical Study of Optimum Cowl Shapes and Flow Port Locations for Minimum Drag with Effective Engine Cooling.” NASA CR-159379, CR-159380 November 1980
- Hess J. L. Smith A. M. O. “Calculation of Nonlifting Potential Flow about Arbitrary Three-Dimensional Bodies.” Douglas Aircraft Company Report No. ES-40622 March 1962
- Hess J. L. Smith A. M. O. “Calculation of Potential Flow About Arbitrary Bodies.” Progress in Aeronautical Sciences 8 1 138 Pergamon Press, New York 1967
- Smetana F. O. Summey D. C. Smith N. S. Carden R. K. “Light Aircraft Lift, Drag, and Moment Prediction - A Review and Analysis.” NASA CR-2523 May 1975 480 pages