Data for a light, single-engine, propeller driven aircraft in steady level flight at sea-level is as follows: velocity $V_{\infty}=40 \mathrm{~m} / \mathrm{s}$, weight $\boldsymbol{W}=13000 \mathrm{~N},$ lift coefficient $\boldsymbol{C}_{L}=0.65,$ drag coefficient $\boldsymbol{C}_{D}=$ $0.025+0.04 C_{L}^{2}$ and power available $P_{a v}=100,000 J / s$. The rate of climb possible for this aircraft under the given conditions (in $m / s)$ is
(A) 7.20
(B) 5.11
(C) 6.32
(D) 4.23

Question ID - 155943 :-

Data for a light, single-engine, propeller driven aircraft in steady level flight at sea-level is as follows: velocity $V_{\infty}=40 \mathrm{~m} / \mathrm{s}$, weight $\boldsymbol{W}=13000 \mathrm{~N},$ lift coefficient $\boldsymbol{C}_{L}=0.65,$ drag coefficient $\boldsymbol{C}_{D}=$ $0.025+0.04 C_{L}^{2}$ and power available $P_{a v}=100,000 J / s$. The rate of climb possible for this aircraft under the given conditions (in $m / s)$ is
(A) 7.20
(B) 5.11
(C) 6.32
(D) 4.23

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