Aerodynamics of Flight

The operational requirements of a large jet transport aircraft Chapter Summary necessitate large pitch trim changes. Some requirements are: In order to sustain an aircraft in flight, a pilot must understand • A large CG range how thrust, drag, lift, and weight act on the aircraft. By understanding the aerodynamics of flight, how design, • A large speed range weight, load factors, and gravity affect an aircraft during • The ability to perform large trim changes due to flight maneuvers from stalls to high speed flight, the pilot wing leading edge and trailing edge high-lift devices learns how to control the balance between these forces. For without limiting the amount of elevator remaining information on stall speeds, load factors, and other important • Maintaining trim drag to a minimum aircraft data, always consult the AFM/POH for specific information pertaining to the aircraft being flown. These requirements are met by the use of a variable incidence horizontal stabilizer. Large trim changes on a fixed-tail aircraft require large elevator deflections. At these large deflections, little further elevator movement remains in the same direction. A variable incidence horizontal stabilizer is designed to take out the trim changes. The stabilizer is larger than the elevator, and consequently does not need to be moved through as large an angle. This leaves the elevator streamlining the tail plane with a full range of movement up and down. The variable incidence horizontal stabilizer can be set to handle the bulk of the pitch control demand, with the elevator handling the rest. On aircraft equipped with a variable incidence horizontal stabilizer, the elevator is smaller and less effective in isolation than it is on a fixed-tail aircraft. In comparison to other flight controls, the variable incidence horizontal stabilizer is enormously powerful in its effect. Because of the size and high speeds of jet transport aircraft, the forces required to move the control surfaces can be beyond the strength of the pilot. Consequently, the control surfaces are actuated by hydraulic or electrical power units. Moving the controls in the flight deck signals the control angle required, and the power unit positions the actual control surface. In the event of complete power unit failure, movement of the control surface can be affected by manually controlling the control tabs. Moving the control tab upsets the aerodynamic balance, which causes the control surface to move. 5-51