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On a reciprocating engine aeroplane, with increasing altitude at constant gross mass, angle of attack and configuration, the TAS:
  • A
    Increases.
  • B
    Decreases.
  • C
    Remains constant.
  • D
    Increases and then decreases.

The dynamic pressure (IAS) relies on density and true airspeed, therefore it becomes evident that a reduction in density necessitates a higher true airspeed to generate the required lift. In simpler terms:

L = CL x 1/2 P x V2 x S

where:

  • CL is the coefficient of lift, representing the angle of attack and airfoil configuration (e.g., slats, flaps).
  • ρ is the air density.
  • V2 is the squared velocity of the aircraft.
  • S is the wing area.

To maintain a consistent lift when density decreases, the true airspeed (V) must increase.

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