ESDU 97009:2003
$62.40
Wing lift coefficient increment at zero angle of attack due to deployment of trailing-edge split flaps at low speeds
| Published By | Publication Date | Number of Pages |
| ESDU | 2003-11-01 | 22 |
ESDU 97009 provides an empirical method for estimating delta C sub 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 delta C sub 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.
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