ESDU 96032: Wing lift coefficient increment at zero angle of attack due to deployment of leading-edge devices at low speeds.

Abstract:

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.

Format: PDF, with software.

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 96032
Status:	Original, issued 01 Nov 1996 Published in Release 2000-03 (init)
Previous Releases:	None available
ISBN:	978 0 85679 996 9

The Data Item document you have requested is available only to subscribers.

Subscribers login here.
If you are not an ESDU subscriber find out how to subscribe.

This Data Item is complemented by the following software:

Toolbox Apps

Name

Details

ESDU LiCrA-3D Toolbox 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.

This program is only available to subscribers.