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 ΔC_L0tw , 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 ΔC_L0tw 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.

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 97009
Status:	Amendment (A), 01 Nov 2003 Published in Release 2004-01
Previous Releases:	ESDU 97009
ISBN:	978 1 86246 013 3

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.