Summary

This app calculates the lift-curve slope and aerodynamic centre position for wings with straight  leading- and trailing-edges and streamwise tips in subsonic flow, using the method of ESDU 70011.

The method was derived from lifting-surface theory and is applicable for $\beta A$ up to 12,  $A \thinspace tan \thinspace \Lambda_{1/2}$ up to 6 and taper ratio ($\lambda$) from 0 to 1, where:

$A$	is aspect ratio,
$\beta$	is $(1 - M^2)^{1/2}$
$M$	is Mach number,
$\Lambda_{1/2}$	is the mid-chord sweep.

The method can be applied to other than straight-tapered planforms by means of the equivalent wing planform concept (see 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.

The program includes an extension to the method of ESDU 70011 to cover wings with modestly swept-forward mid-chord lines.

Note: The user should consult ESDU 70011 for full specification and discussion of the wing configurations and flow conditions covered by the data used in the derivation of the method, and additional advice on the applicability.

(See ESDU 70012 and its accompanying Toolbox app for the supersonic flow case.)