7) If a laminar boundary layer has a measured geometric thickness of 5 mm, give an
estimate of the displacement thickness.
8) Could the following lift polar ($C_l$ vs $\alpha$) for a symmetrical airfoil with thickness have
been determined using a numerical method based only on distributing discrete vortices on
the chord line? Support your answer.
$C_1$
$\alpha$
9) Will the pitching moment coefficient ($C_{mc/4}$) measured at the c/4 location of the wing
of an aircraft increase, decrease or remain the same as the aircraft transitions from high
speed cruise to (low speed) landing if the airfoil section is a NACA 0012. Support your
answer.
10) A wing of aspect ratio 6 and operating at a 2 degree angle of attack has a spanwise
loading defined crudely by a lifting line with three Fourier coefficients: $A_1 = 0.014$, $A_3 =$
$0.0003$, $A_5 = 0.0006$. Find the lift coefficient and induced drag coefficient for this wing:
