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Full-scale wind tunnel study of nacelle shape on cooling drag (1979)

Kroeger, R. A. ; Corsiglia, V. R. ; Katz, J.

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Publication Date: 2019-07-13

Description: Tests were made in the NASA-Ames 40- by 80 Foot Wind Tunnel of a wing semispan with a nacelle (no propeller) from a typical, general aviation twin-engine aircraft. Measurements were made of the effect on drag of the cooling air flow through the nacelle. Internal and external nacelle pressures were measured. It was found that the cooling flow accounts for about 13% of the estimated airplane drag and about 42% of the cooling flow drag is associated with the internal flow. It was concluded that improvements could be made by relocating both the inlet and the outlet of the cooling air.

Keywords: AIRCRAFT PROPULSION AND POWER

Type: AIAA PAPER 79-1820 , American Institute of Aeronautics and Astronautics, Aircraft Systems and Technology Meeting; Aug 20, 1979 - Aug 22, 1979; New York, NY

Format: text

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