Lift and Stalls
(1.32)

Describe the Effect of
Altitude on Mach Number
and Critical Mach Number





As the altitude increases, the density changes resulting in
changing Mach numbers.
For constant Mach the equation is M = TAS / LSOS
For constant IAS the equation is IAS = TAS x √ρ/ρ0
For constant TAS the equation is TAS = IAS x √ρ0/ρ








Lift and Stalls
(1.35)
Describe the Effects
of Changes in Angle of
Attack on the Pressure Distribution
and Aerodynamic Force of
Cambered and Symmetric Airfoils










CAMBERED AIRFOIL
Increasing angle of attack on any airfoil causes the area of the streamtube above the wing to decrease. This produces a greater velocity increase above the wing than below the wing. The greater velocity increases the pressure differential on a cambered airfoil. The greater pressure differential on
the airfoil will increase the magnitude of the aerodynamic force.

SYMMETRIC......

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Title: Flight
Approximate Word Count: 563
Approximate Pages: 3 (250 words per double-spaced page)

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