Question

P.14.6 An aircraft weighing 238,000 N has wings 88.5 m² 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 $C_M cdot c = (0.427C_L - 0.061)$ 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 m². During a pull-out from a dive with zero thrust at 215 m/s EAS when the flight path is at 40° 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/s². Calculate the maneuver load factor both at the CG and at the tailplane CP, the forward inertia coefficient, and the tail lift. Answer: n = 3.78(CG), n = 5.19 at TP, f = -0.370, P = 18,925 N

          P.14.6 An aircraft weighing 238,000 N has wings 88.5 m² 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 $C_M cdot c = (0.427C_L - 0.061)$ 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 m². During a pull-out from a dive with zero
thrust at 215 m/s EAS when the flight path is at 40° 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/s². Calculate
the maneuver load factor both at the CG and at the tailplane CP, the forward inertia coefficient, and
the tail lift.
Answer:
n = 3.78(CG), n = 5.19 at TP, f = -0.370, P = 18,925 N

P.14.6 An aircraft weighing 238,000 N has wings 88.5 m² in area, for which CD = 0.0075 + 0.045CL^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 CM cdot c = (0.427CL - 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 m². During a pull-out from a dive with zero
thrust at 215 m/s EAS when the flight path is at 40° 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/s². Calculate
the maneuver load factor both at the CG and at the tailplane CP, the forward inertia coefficient, and
the tail lift.
Answer:
n = 3.78(CG), n = 5.19 at TP, f = -0.370, P = 18,925 N

Added by Carolyn D.

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