IL.XIV.F.S4

From the FAA library

• Pilot's Handbook of Aeronautical Knowledgep. 5-36
  Chapter 5: Aerodynamics of Flight › Load Factors › Load Factors and Flight Maneuvers

  Spins Load Factors and Flight Maneuvers Critical load factors apply to all flight maneuvers except unaccelerated straight flight where a load factor of 1 G is always present. Certain maneuvers considered in this section are known to involve relatively high ... load factors. Full application of pitch, roll, or yaw controls should be confined to speeds below the maneuvering speed. Avoid rapid and large alternating control inputs, especially in combination with large changes in pitch, roll, or yaw (e.g., large sideslip…

• Pilot's Handbook of Aeronautical Knowledgep. 5-32
  Chapter 5: Aerodynamics of Flight › Load Factors

  varies with different aircraft depending on the airframe, engine, and propeller combinations, as well as other design features. To maintain positive control of the aircraft in all flight conditions, the pilot must apply the flight controls as necessary to compensate ... these varying values. Figure 5-51. Asymmetrical loading of propeller (P-factor). Load Factors In aerodynamics, the maximum load factor (at given bank angle) is a proportion between lift and weight and has a trigonometric relationship. The load factor…

• Pilot's Handbook of Aeronautical Knowledgep. 5-34
  Chapter 5: Aerodynamics of Flight › Load Factors › Load Factors and Stalling Speeds

  Load Factors and Stalling Speeds Any aircraft, within the limits of its structure, may be stalled at any airspeed. When a sufficiently high AOA is imposed, the smooth flow of air over an airfoil breaks up and separates, producing ... this effect has revealed that an aircraft’s stalling speed increases in proportion to the square root of the load factor. This means that an aircraft with a normal unaccelerated stalling speed of 50 knots can be stalled…

• Pilot's Handbook of Aeronautical Knowledgep. 5-23
  Chapter 5: Aerodynamics of Flight › Aerodynamic Forces in Flight Maneuvers › Forces in Turns

  when making constant altitude turns is that the vertical component of lift must be equal to the weight to maintain altitude. At a given airspeed, the rate at which an aircraft turns depends upon the magnitude of the horizontal component ... lift. It is found that the horizontal component of lift is proportional to the angle of bank—that is, it increases or decreases respectively as the angle of bank increases or decreases. As the angle of bank is increased…

• Pilot's Handbook of Aeronautical Knowledgep. 5-36
  Chapter 5: Aerodynamics of Flight › Load Factors › Stalls

  Stalls The normal stall entered from straight-and-level flight, or an unaccelerated straight climb, does not produce added load factors beyond the 1 G of straight-and-level flight. As the stall occurs, however, this load factor ... reduced toward zero, the factor at which nothing seems to have weight. The pilot experiences a sensation of “floating free in space.” If recovery is effected by snapping the elevator control forward, negative load factors (or those that impose…

• Pilot's Handbook of Aeronautical Knowledgep. 5-34
  Chapter 5: Aerodynamics of Flight › Load Factors › Load Factors in Steep Turns

  Load Factors in Steep Turns At a constant altitude, during a coordinated turn in any aircraft, the load factor is the result of two forces: centrifugal force and weight. [Figure 5-52] For any given bank angle, the ROT varies ... with the airspeed—the higher the speed, the slower the ROT. This compensates for added centrifugal force, allowing the load factor to remain the same. Figure 5-52. Two forces cause load factor during turns. Figure 5-53 reveals…