The disk-gap-band parachute in the chapter-opener photo had a drag of 1600 lbf when tested at $15 \mathrm{mi} / \mathrm{h}$ in air at $20^{\circ} \mathrm{C}$ and 1 atm. (a) What was its drag coefficient? $(b)$ If, as stated, the drag on Mars is 65,000 lbf and the velocity is $375 \mathrm{mi} / \mathrm{h}$ in the thin Mars atmosphere, $\rho \approx 0.020 \mathrm{kg} / \mathrm{m}^{3}$
what is the drag coefficient on Mars? $(c)$ Can you explain the difference between $(a)$ and $(b) ?$