The Pitot tube of an aircraft registers a pressure $p_{0}=54051 \mathrm{~N} / \mathrm{m}^{2} .$ The static pressure, density and the ratio of specific heats of the freestream are $p_{\infty}=45565 \mathrm{~N} / \mathrm{m}^{2}, \rho_{\infty}=0.6417 \mathrm{~kg} / \mathrm{m}^{3}$ and $\gamma=1.4,$ respectively. The indicated airspeed $(\mathrm{in} m / s)$ is
(A) 157.6
(B) 162.6
(C) 172.0
(D) 182.3
The Pitot tube of an aircraft registers a pressure $p_{0}=54051 \mathrm{~N} / \mathrm{m}^{2} .$ The static pressure, density and the ratio of specific heats of the freestream are $p_{\infty}=45565 \mathrm{~N} / \mathrm{m}^{2}, \rho_{\infty}=0.6417 \mathrm{~kg} / \mathrm{m}^{3}$ and $\gamma=1.4,$ respectively. The indicated airspeed $(\mathrm{in} m / s)$ is
(A) 157.6
(B) 162.6
(C) 172.0
(D) 182.3