Lift equals weight and thrust equals drag.
During the transition from straight-and-level flight to a climb, the angle of attack is increased and lift is momentarily increased.
During a steady climb, the angle of climb depends on excess thrust.
A propeller rotating clockwise, as seen from the rear, creates a spiraling slipstream that tends to rotate the aircraft to the left around the vertical axis, and to the right around the longitudinal axis.
The four forces acting on an airplane in flight are lift, weight, thrust, and drag.
Lift produced by an airfoil is the net force developed perpendicular to the relative wind.
When are the four forces that act on an airplane in equilibrium?
During unaccelerated flight.
Which action will result in a stall?
Exceeding the critical angle of attack.
The reason for variations in geometric pitch (twisting) along a propeller blade is that it permits a relatively constant angle of attack along its length when in cruising flight.
If the aircraft's nose remains in the new position after the elevator control is pressed forward and released, the aircraft displays neutral static stability.
If the aircraft's nose initial tends to return to its original position after the elevator control is pressed forward and released, the aircraft displays positive static stability.
As altitude increases, the indicated airspeed at which a given airplane stalls in a particular configuration will remain the same regardless of altitude.
The angle of attack at which an airplane wing stalls will remain the same regardless of gross weight.
The angle of attack of a wing directly controls the distribution of positive and negative pressure acting on the wing.
The need to slow an aircraft below VA is brought about by the following weather phenomenon: