The BAe 146-100 specifications are given in table Q.1. MTOW [kg] Wing Area [m2] CL_Max_ CL_Min...

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The BAe 146-100 specifications are given in table Q.1. MTOW [kg] Wing Area [m2] CL_Max_ CL_Min Max. Manoeuvring Speed-EAS [kts] Max. Operating Speed EAS [kts] dc₁/da 38136 77.3 Flaps Retracted 1.6 -0.8 235 a) Sketch the V-n diagram for this aircraft. 270 5.3 Table Q.1 Flaps 18° 3.0 170 170 5.3 [10 marks] b) What would you expect to happen to the trim of the aircraft, if it is hit by a vertical upwards gust? [8 marks] c) The fatigue limit for a critical component in the aircraft described above is +/- 200 MPa, based on a mean stress of 60 MPa. For a typical flight length of 1000 km at an altitude of 9 km, predict the total damage fraction for this component when subject to a vertical gust encounter with a spectrum of 5 m/s. Use a gust alleviation factor of 0.8. The BAe 146-100 specifications are given in table Q.1. MTOW [kg] Wing Area [m2] CL_Max_ CL_Min Max. Manoeuvring Speed-EAS [kts] Max. Operating Speed EAS [kts] dc₁/da 38136 77.3 Flaps Retracted 1.6 -0.8 235 a) Sketch the V-n diagram for this aircraft. 270 5.3 Table Q.1 Flaps 18° 3.0 170 170 5.3 [10 marks] b) What would you expect to happen to the trim of the aircraft, if it is hit by a vertical upwards gust? [8 marks] c) The fatigue limit for a critical component in the aircraft described above is +/- 200 MPa, based on a mean stress of 60 MPa. For a typical flight length of 1000 km at an altitude of 9 km, predict the total damage fraction for this component when subject to a vertical gust encounter with a spectrum of 5 m/s. Use a gust alleviation factor of 0.8.