ESDU 97009
Wing lift coefficient increment at zero angle of attack due to deployment of trailing-edge split flaps at low speeds.
Abstract:
ESDU 97009 provides an empirical method for estimating ΔCL0tw , the increment in lift coefficient at zero angle of attack due to the deployment of full-span or part-span split flaps on wings at low speeds. The increment ΔCL0tw is derived by using the method of ESDU 94029 to establish the characteristics of a split flap on an aerofoil section that is representative of the wing, taken at mid-span of the flap panel, and applying factors to allow for planform geometry and part-span effects. The method has been found to be accurate to within +/-15% for 98% of the data studied.A computer program of the method is included as part of ESDU LiCrA Toolbox apps and ESDUpacs A9931 and B9931 from (ESDU 99031). See the 'Software' tab, above.
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This Data Item is complemented by the following software:
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Toolbox LiCrA-3D Run |
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