Question

There is an aircraft that has a mass of 1251Kg. Flying at a cruising velocity of 71 m/s, and knowing that its Lift force is equal to L= 0.5 ​ rhoV 2 SC L ​ , where V is its resultant velocity, rho air density, S aircraft's wing surface equals to 15 m 2 , and C L ​ the lift coefficient equals to 0.38 ; find the maximum height the aircraft can sustain straight level flight, this is, that it can carry its own weight,

Answer 1

To find the maximum height the aircraft can sustain straight level flight, we need to calculate the lift force balanced with the weight. We can use the given equations and values to find the lift force and determine the maximum height.

Step-by-step explanation:

To find the maximum height the aircraft can sustain straight level flight, we need to determine the lift force that the aircraft can generate to balance its weight. The lift force can be calculated using the equation L = 0.5 ρV2SCL, where ρ represents the air density, V is the resultant velocity, S is the wing surface area, and CL is the lift coefficient. Given the aircraft's mass of 1251 kg and using the equation F = mg, where g represents the acceleration due to gravity, we can find the weight of the aircraft, which is the force that needs to be balanced by the lift force.

Using the given values for the wing surface area (S = 15 m2), air density (ρ = 1.29 kg/m3), cruising velocity (V = 71 m/s), and lift coefficient (CL = 0.38), we can calculate the lift force. With the lift force and weight of the aircraft, we can determine the maximum height the aircraft can sustain straight level flight.