The Anglo-French Concorde supersonic transport has an ogival delta wing with an aspect ratio of 1.7. Assuming a triangular planform shape, estimate the low-speed lift coefficient for this wing at an angle of attack of 25°.

Low-speed lift coefficient, \(C_{L} = C_{N}\cos\alpha\) 

\[\alpha = 25^{\circ} = 0.4363\,rad\]

\[\frac{C_{N}}{\left ( S/d \right )^{2}} = 2\pi \left ( \frac{\alpha }{S/d} \right )+4.9\left ( \frac{\alpha }{S/d} \right )^{1.7}\]

\[\frac{\alpha }{S/d} = \frac{0.4363}{0.425} = 1.0266\]

\[\frac{C_{N}}{\left (0.425 \right )^{2}} = 2\pi \left (1.0266 \right )+4.9\left (1.0266 \right )^{1.7}\]

\[\Rightarrow C_N=2.09\]

\[\Rightarrow C_{L} = 2.09\left ( \cos 25^{\circ} \right )=1.89\]