Wing lift coefficient increment at zero angle of attack due to deployment of plain trailing-edge flaps at low speeds.
Abstract:ESDU 97011 provides an empirical method for estimating ΔCL0tw , the increment in lift coefficient at zero angle attack due to the deployment of full-span or part-span plain flaps on wings at low speeds. The increment ΔCL0tw is derived by using the method of ESDU 94028, but with a modified efficiency factor, to establish the characteristics of a plain flap on an aerofoil section that is representative of the wing. Factors are applied 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.
|Data Item ESDU 97011|
|Toolbox LiCrA-3D Run||