Flight
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 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 creates a pressure differential on a symmetric airfoil. The greater pressure differential on the airfoil will increase the magnitude of the aerodynamic force.
Lift and Stalls (1.37) List the Factors Affecting
Lift that the Pilot can Directly Control
The factors affecting lift that the pilot can control are angle of attack, velocity, density, surface area, and shape.
Lift and Stalls (1.38) Compare and
Contrast the Coefficients of
Lift Generated by
Cambered and Symmetric Airfoils
CAMBERED AIRFOILS
Positive camber
At zero angle of attack there is a positive coefficient of lift.
For a coefficient of lift of zero, the positive camber requires a negative angle of attack.
Negative camber
(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 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 creates a pressure differential on a symmetric airfoil. The greater pressure differential on the airfoil will increase the magnitude of the aerodynamic force.
Lift and Stalls (1.37) List the Factors Affecting
Lift that the Pilot can Directly Control
The factors affecting lift that the pilot can control are angle of attack, velocity, density, surface area, and shape.
Lift and Stalls (1.38) Compare and
Contrast the Coefficients of
Lift Generated by
Cambered and Symmetric Airfoils
CAMBERED AIRFOILS
Positive camber
At zero angle of attack there is a positive coefficient of lift.
For a coefficient of lift of zero, the positive camber requires a negative angle of attack.
Negative camber