The drag coefficient of an aircraft can be expressed as: CD = 0.020 + 0.125CZ. It...

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The drag coefficient of an aircraft can be expressed as: CD = 0.020 + 0.125CZ. It flies at an altitude of 9,000m at a speed of M = 0.85. It has a weight of 111kN and a wing area of 35m². a) In straight and level flight at M = 0.85, find the coefficients of lift and drag. b) Find the thrust required in kN. c) If Cmax = 1.75, find the stall speed as an equivalent airspeed and a true airspeed in knots at 9,000m. The drag coefficient of an aircraft can be expressed as: CD = 0.020 + 0.125CZ. It flies at an altitude of 9,000m at a speed of M = 0.85. It has a weight of 111kN and a wing area of 35m². a) In straight and level flight at M = 0.85, find the coefficients of lift and drag. b) Find the thrust required in kN. c) If Cmax = 1.75, find the stall speed as an equivalent airspeed and a true airspeed in knots at 9,000m.

Answer rating: 100% (QA)

Given CD 0020 0125CL2 drag coefficient equation Altitude 9000m Speed M 085 Weight 111 kN ... View the full answer