ESDU 94031
Increments in aerofoil lift coefficient at zero angle of attack and in maximum lift coefficient due to deployment of a doubleslotted or tripleslotted trailingedge flap, with or without a leadingedge highlift device, at low speeds.
Abstract:
ESDU 94031 presents an estimation method based on the theory for a thin hinged plate modified using empirical correlation factors to account for the geometry of practical aerofoils and highlift devices. Some allowance for the effects of chord extension was made by using flap chord ratio and lift coefficients based on aerofoil extended chord but further adjustments were required to adapt to the considerable departure for slotted flaps from the model, possibly involving large chord extensions. The data for aerofoils with trailingedge flaps deployed from which the methods were developed were extracted from windtunnel tests reported in the literature covering a wide range of practical geometries. Fewer data were available for aerofoils with both leading and trailingedge devices deployed. The methods apply to Reynolds numbers greater than a million and freestream Mach numbers less than 0.2. The predicted and test data for the lift coefficient increments correlated to within 15 per cent. The use of the methods is illustrated by worked examples. To obtain results for an aerofoil with both leadingedge devices and slotted flaps deployed, ESDU 84026 is used in conjunction with this document and ESDU 94027.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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Data Item ESDU 94031  

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