An aircraft weighing 238000 N has wings 885 m2 in area for w

An aircraft weighing 238,000 N has wings 88.5 m^2 in area, for which C_D = 0.0075 +0.045C_L^2. The extra-to-wing drag coefficient based on wing area is 0.0128 and the pitching moment coefficient for all parts excluding the tailplane about an axis through the CG is given by C_M middot c = (0.427C_L - 0.061) m. The radius from the CG to the line of action of the tail lift may be taken as constant at 12.2 m. The moment of inertia of the aircraft for pitching is 204,000 kg m^2. During a pull-out from a dive with zero thrust at 215 m/s EAS when the flight path is at 40 degree to the horizontal with a radius of curvature of 1525 m, the angular velocity of pitch is checked by applying a retardation of 0.25 rad/s^2. Calculate the maneuver load factor both at the CG and at the tailplane CP, the forward inertia coefficient, and the tail lift.

Solution

Ans is 3.78(CG)

n = 5.19 at TP

f = -0.370

P = 18925 N

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