IHS ESDU Wing lift coefficient increment at zero angle of attack due to deployment of plain trailing-edge flaps at low speeds. 97011

Description
ESDU 97011 provides an empirical method for estimating delta C sub L0tw, 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 delta C sub L0tw 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.
  • Wing lift coefficient increment at zero angle of attack due to deployment of plain trailing-edge flaps at low speeds. - 97011 - IHS ESDU
    IHS ESDU
Description
ESDU 97011 provides an empirical method for estimating delta C sub L0tw, 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 delta C sub L0tw 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.

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Wing lift coefficient increment at zero angle of attack due to deployment of plain trailing-edge flaps at low speeds. - 97011 - IHS ESDU
IHS ESDU
London, United Kingdom
Wing lift coefficient increment at zero angle of attack due to deployment of plain trailing-edge flaps at low speeds.
97011
Wing lift coefficient increment at zero angle of attack due to deployment of plain trailing-edge flaps at low speeds. 97011
ESDU 97011 provides an empirical method for estimating delta C sub L0tw, 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 delta C sub L0tw 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.

ESDU 97011 provides an empirical method for estimating delta C sub L0tw, 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 delta C sub L0tw 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.

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Technical Specifications

  IHS ESDU
Product Category Standards and Technical Documents
Product Number 97011
Product Name Wing lift coefficient increment at zero angle of attack due to deployment of plain trailing-edge flaps at low speeds.
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