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 ΔCL0tw , 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 ΔCL0tw 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.
|Data Item ESDU 97009|
- Aircraft Noise
- Fatigue - Endurance Data
- Fatigue - Fracture Mechanics
- Fluid Mechanics, Internal Flow
- Fluid Mechanics, Internal Flow (Aerospace)
- Heat Transfer
- Physical Data, Chemical Engineering
- Stress and Strength
- Transonic Aerodynamics
- Vibration and Acoustic Fatigue
- Wind Engineering
Aerospace Materials Data
Additional Engineering References