ESDU 97011
Wing lift coefficient increment at zero angle of attack due to deployment of plain trailing-edge flaps at low speeds.
Abstract:
ESDU 97011 provides an empirical method for estimating ΔCL0tw , the increment in lift coefficient at zero angle attack due to the deployment of full-span or part-span plain flaps on wings at low speeds. The increment ΔCL0tw is derived by using the method of ESDU 94028, but with a modified efficiency factor, to establish the characteristics of a plain flap on an aerofoil section that is representative of the wing. Factors are applied 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.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 97011 | |
---|---|
Format: |
|
Status: |
|
Previous Releases: | |
ISBN: |
|
The Data Item document you have requested is available only to subscribers or purchasers.
- Subscribers login here.
- If you are not an ESDU subscriber you can
- find out how to subscribe, or
- purchase this Data Item from the Standards Store.
This Data Item is complemented by the following software:
Name | Details | ||||||
---|---|---|---|---|---|---|---|
LiCrA-3D Toolbox Run |
|