Lift coefficient increment at low speeds due to full-span split flaps.
Abstract:ESDU 74009 gives curves of lift coefficient increment as a function of wing thickness/chord ratio and flap deflection for a flap chord/wing chord ratio of 0.4. A second graph provides a correction factor for other flap chord/wing chord ratios less than 0.4. An equation corrects those data from two-dimensional to three-dimensional. The curves are based on a correlation of available experimental data that predicts the lift increment in two-dimensional flow to within 10 per cent. The three-dimensional correction has been compared with experimental data from 12 sources and predicts the lift increment to within 10 per cent also. To correct the data for application to part-span flaps ESDU 74012 is used.
|Data Item ESDU 74009|
- 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