ESDU 91014: Maximum lift of wings with trailing-edge flaps

Abstract:

ESDU 91014 gives a method that involves the calculation of two components: the increment in maximum lift coefficient due to flaps is added to the maximum lift coefficient for the wing with flaps undeployed determined from ESDU 89034. The first component is calculated using ESDU 94028, ESDU 94029, ESDU 94030 or ESDU 94031 (for plain, split, single-slotted or multiple-slotted trailing-edge flaps, respectively) applied to the most highly loaded section, factored for the effects of aspect ratio, taper ratio and wing sweep in addition to flap part-span effects. The method was developed using wind-tunnel data from many sources for a wide range of planform parameters (aspect ratios from 3 to 9 and leading-edge sweep up to 50 degrees) for which it was found to correlate the predicted increment generally within 10 per cent and the maximum lift of the wing with flaps deployed to within 5 per cent. It applies for freestream Mach numbers less than 0.25 for plain, split or single- or multi-slotted flaps. Sketches of predictions plotted against test results illustrate the quality of the estimation and a detailed worked example illustrates the use of the method.

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.

Indexed under:

Details:

Data Item ESDU 91014
Format:	PDF with software with interactive graphs
Status:	Amendment (A), 01 Aug 1995 Published in Release 2000-03 (init)
Previous Releases:	None available
ISBN:	978 0 85679 776 7

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This Data Item is complemented by the following software:

Toolbox Apps

Name

Details

Toolbox LiCrA-3D Run

Title

ESDU LiCrA: 3D Lift Curve Aerodynamics for Wings and Wing/Body Combinations

Version

1.0

Details

LiCrA 3D calculates the maximum lift coefficient, the lift coefficient at zero angle of attack and the lift curve of straight-tapered wings with or without high-lift devices deployed at low speeds. The basic wing (no devices deployed) may have camber and twist. The program includes methods that allow for the presence of a fuselage.

For completeness, calculations can be made for the wing when there are no high-lift devices deployed but the prediction of the shape of the non-linear part of the lift curve should be treated with caution because it employs a technique developed for use when high-lift devices are deployed. The method is intended for use only for free-stream Mach numbers up to about 0.25. No allowance is made for ground effect.

If required, it will also calculate the spanwise position of the section of the basic wing that has the peak loading due to angle of attack.

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This Data Item contains 4 interactive graph(s) as listed below.

Graph	Title
Figure 1	Variation of η_p with λ and η‾
Figure 2	Variation of μ_p with λ and η¯
Figure 3a	Part-span factor for plain and split flaps
Figure 3b	Part-span factor for slotted flaps

ESDU 91014

Maximum lift of wings with trailing-edge flaps at low speeds.