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An aircraft is designed with lift coefficient of 1.1 during steady level flight. If dynamic pressure is set to be 25.65 Pa then find weight of aircraft during this flight condition.

An aircraft is designed with lift coefficient of 1.1 during steady level flight. If dynamic pressure is set to be 25.65 Pa then find weight of aircraft during this flight condition. Correct Answer 28.215 N per unit area

Given, steady level flight. Lift coefficient CL=1.1, q=25.65Pa. Since, area is not mentioned we will find weight as per unit area. Weight can be given by, W = q*S*CL = 25.65*1.1 = 28.215 N per area.

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