The induced drag coefficient of the delta wing given in Fig. 8.59, according to Puckett and Stewart, reads as

\[
C_{D i}=\alpha C_{L}\left[1-m^{\prime} /\left(2(1-a) H(a) E\left(m^{\prime}\right)\right)\right]
\]

Find the induced drag of the wing given in Problem 8.17.

Fig. 8.59

Problem 8.17

A delta wing has an aspect ratio of 1. 

(i) Plot the coefficients \(K_{p}\) and \(K_{v}\) with respect to Mach number 

(ii) for \(M=2\), plot the lift coefficient wrt angle of attack. Comment on the limiting values involved in the graph.

Transcribed Image Text:

b a c.