Lift-curve slope and aerodynamic centre position of wings in inviscid subsonic flow.
Abstract:ESDU 70011 presents data for the lift-curve slope and aerodynamic centre position for wings with straight leading- and trailing-edges and streamwise tips in subsonic flow. The data were derived from lifting-surface theory and are presented in carpet form for βA up to 12, A tanΛ ½ up to 6 and taper ratio (λ) from 0 to 1, where A is aspect ratio, β is (1 - M2)½ where M is Mach number, and Λ½ is the half-chord sweep. The data can be applied to other than straight-tapered planforms by means of the equivalent wing planform concept (ESDU 76003 or ESDU 76015). Comparisons with a wide range of test data indicate that the lift-curve slope of wings on wing-body combinations is predicted to within about 5% and that aerodynamic centre position is predicted generally to within 0.03 of the aerodynamic mean chord.
A computer program of the method (ESDUpac A7011) is provided and includes an extension to cover wings with modestly swept forward half-chord lines.
For information, an improved form of the Helmbold-Diederich equation for wing lift-curve slope is given which provides predictions largely within ±2% of the values obtained from this Data Item for βA ≥ 1.5.
|Data Item ESDU 70011|
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|Figure 1a||Lift Curve Slope λ = 0|
|Figure 1b||Lift Curve Slope λ = 0.125|
|Figure 1c||Lift Curve Slope λ = 0.25|
|Figure 1d||Lift Curve Slope λ = 0.5|
|Figure 1e||Lift Curve Slope λ = 1|
|Figure 2a||Aerodynamic Centre A tan Λ1/2 = 0|
|Figure 2b||Aerodynamic Centre A tan Λ1/2 = 1|
|Figure 2c||Aerodynamic Centre A tan Λ1/2 = 2|
|Figure 2d||Aerodynamic Centre A tan Λ1/2 = 3|
|Figure 2e||Aerodynamic Centre A tan Λ1/2 = 4|
|Figure 2f||Aerodynamic Centre A tan Λ1/2 = 5|
|Figure 2g||Aerodynamic Centre A tan Λ1/2 = 6|