Melbourne Institute of Technology Fokker 70 Aircraft Lift Coefficient Paper B2(a) Calculate the lift coefficient of the aircraft.B2(b) Calculate the lift c

Melbourne Institute of Technology Fokker 70 Aircraft Lift Coefficient Paper B2(a) Calculate the lift coefficient of the aircraft.B2(b) Calculate the lift coefficient of the tailplane (Assume dynamic pressure is same at tail and wing)B2(c) Calculate the lift force produced by the tailplane.B2(d) Determine angle of attack of the tailplane with the tab undeflected.B2(e) Determine the elevator angle required to trim the aircraft with the tab undeflected.B2(f) Determine the stick position required to trim the aircraft with the tab undeflected.(3 marks) (4 marks) (3 marks) (6 marks) (6 marks) (3 marks) A Fokker 70 aircraft is trimmed for steady level flight at a speed of 200 m/s (TAS) at an altitude of 10,000 m above
sea level where the air density, p= 0.41351 kg.m”.
Relevant characteristics of the aircraft are tabulated below:
Mass
33,500 kg
Wing/body lift curve slope, AwB
5.8 per rad
Wing area, S
95.0 m²
Tailplane lift curve slope, ay
3.6
per
rad
Wing mean aerodynamic chord (MAC), T
4.0 m
Elevator lift curve slope, az
1.8 per rad
Tailplane area, ST
23.5 m²
Elevator tab lift curve slope, az
0.4
per
rad
Elevator MAC, CE
2.3 m
0.45@eff
Elevator area, SE
7.5 m²
-2°
-0.06
-0.08
Downwash angle at tail
aerodynamic centre, e
Tailplane setting angle, ir
Tailplane pitching moment curve
slope, bi
Elevator pitching moment curve
slope, b2
Elevator tab pitching moment curve
slope, bz
1.8 m
Wing/body pitching moment coefficient
about the aerodynamic centre, CMOWB
Distance from wing leading edge to WB
aerodynamic centre, how c
Distance from wing leading edge to CG of
aircraft, ha
Distance from wing body aerodynamic
centre to tailplane aerodynamic centre, 1
-0.05
0.5 m
-0.10
15.0 m
Elevator to stick gearing, se
2 rad/m
B2(a) Calculate the lift coefficient of the aircraft.
(3 marks)
B2(b) Calculate the lift coefficient of the tailplane (Assume dynamic pressure is same at tail and wing) (4 marks)
B2(c) Calculate the lift force produced by the tailplane.
(3 marks)
B2(d) Determine angle of attack of the tailplane with the tab undeflected.
(6 marks)
B2(e) Determine the elevator angle required to trim the aircraft with the tab undeflected.
(6 marks)
B2(f) Determine the stick position required to trim the aircraft with the tab undeflected.
(3 marks)

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