The maximum lift coefficient of plain wings at subsonic speeds.
Abstract:ESDU 89034 gives an empirical method for estimating the maximum lift of aerodynamically smooth straight-tapered wings with or without camber and/or twist but with high lift devices undeflected. Any shape of section or camber line, both of which may vary spanwise, can be treated. Linear spanwise variation of combined twist (geometric or camber induced) is assumed, but by means of an equivalent linear twist it can also be applied to wings with non-linear monotonic twist. It can also be applied to wings with cranked or curved edges by use of the equivalent straight-tapered wing concept of ESDU 76003. The method uses the approach of ESDU 83040 for an unswept, untwisted wing to locate the most highly loaded section. ESDU 84026 is used to find the maximum lift there which is then related to the wing overall lift. Corrections are applied as appropriate for sweep and twist effects and for the influence of Mach number and Reynolds numbers. The method has been tested against wing alone wind-tunnel data (including half models) extracted from the literature for a range of wing geometries (aspect ratios 2 to 12, sweeps up to 50 degrees, taper ratios 0.2 to 1.0) for Mach numbers to 0.8, and was found generally to predict the maximum lift coefficient to within 10 per cent. The calculation procedure is programmed in ESDUpac A9315, see ESDU 93015.
|Data Item ESDU 89034|
- 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