(Solved): Consider a commercial transport aircraft, powered by two turbofan engines, in a steady level flight ...

Consider a commercial transport aircraft, powered by two turbofan engines, in a steady level flight at 10,000 m altitude. Details of the aircraft at an instantaneous moment of the flight study are given as follow: Current Total Mass $=180,000\mathrm{kg}$, Wing Area $=360{\mathrm{m}}^2$, Wing Span $=60\mathrm{m}$, Maximum Lift-to-Drag Ratio $=15$, Equivalent Current Total Thrust at Sea Level Condition $=300\mathrm{kN}$, Span Efficiency Factor $=0.9$, Engine Installation Angle $=0^{?}$ Take the air densities equal to $1.225\mathrm{kg}/{\mathrm{m}}^3,0.9093\mathrm{kg}/{\mathrm{m}}^3$ and $0.414\mathrm{kg}/{\mathrm{m}}^3$ at sea level, $3000\mathrm{m}$ altitude and $10,000\mathrm{m}$ altitude, respectively. Assume the gravitational acceleration is $9.8\mathrm{m}/{\mathrm{s}}^2$ and speed of sound at $10,000\mathrm{m}$ is $299.5\mathrm{m}/\mathrm{s}$. - It is found out that the thrust of the aircraft at $3000\mathrm{m}$ is reduced to only $80\%$ of the thrust at sea level conditions. With this information, analyze whether the aircraft can actually fly in reality at the calculated maximum velocity from its current thrust setting at $10,000\mathrm{m}$ altitude. - The pilot of the aircraft wants to fly it at $160\mathrm{m}/\mathrm{s}$ at this $10,000\mathrm{m}$ altitude. Analyze whether this is a recommendable velocity for this aircraft to fly at this altitude.