ESDU 96032:1996

$89.05

Wing lift coefficient increment at zero angle of attack due to deployment of leading-edge devices at low speeds

Published By	Publication Date	Number of Pages
ESDU	1996-11-01	24

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Category: ESDU

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ESDU 96032 provides an empirical method developed from that for aerofoil sections in ESDU 94027 to 94031. It applies to leading-edge flaps, drooped leading edges, slats and vented Krueger flaps, and sealed slats and Krueger flaps. For wings with full-span leading-edge devices a factor, dependent on planform geometry, is applied to allow for three-dimensional effects. For part-span leading-edge devices, additional factors are introduced dependent on the device and wing geometry. The method applies for leading-edge sweep less than 47 degrees and Reynolds numbers based on aerodynamic mean chord greater than 0.6E-6. The experimental data are predicted to within 0.02 in lift coefficient based on wing area. A worked example illustrates the use of the data.


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Published Code	ESDU
Published By	ESDU
Publication Date	1996-11-01
Pages Count	24
Language	English
File Size	348.2 KB

ESDU 96032:1996

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