When rolling the aircraft the up-going wing will experience more drag than the down-going wing. This will result in a yawing moment that directly opposes the desired direction of turn. (i.e.: rolling left will cause a right yaw.)

A stall strip, usually located close to the wing root, causes the airflow to separate at a lower angle of attack and ensures that the wing root stalls before the wing tips.

The Boeing 737 has an all moving horizontal stabilizer.

Forward motion forces air into the intake which is a convergent duct where it is compressed (causing a temperature rise).

Fuel is added and combustion takes place increasing the volume. The expanding gasses accelerate to the atmosphere through the exhaust duct nozzle producing a propulsive jet.

Profile drag, also known as pressure drag or form drag, is the drag caused by the separation of the boundary layer from a surface and the wake created by that separation.

It is primarily dependent upon the shape of the object and increases directly with speed as the faster an aircraft moves the more air molecules collide with it.

No, VMCG is defined as the minimum control speed on the ground, with one engine inoperative (critical engine on two engine airplanes), takeoff power on other engine(s), using aerodynamic controls only for directional control and thus only applicable to ME aircraft.

The angle between between the chord line and the aircraft's longitudinal axis. It's a fixed angle for wings, but variable for variable incidence tailplanes.

A wing stalls because the airflow over the wing’s upper surface separates when the critical angle of attack is reached or exceeded. This causes a reduction in the lift generated by the aerofoil

Dangers of flying into thunderstorms:

Severe wind shear and turbulence (with a risk of structural problems, loss of altitude, loss of airspeed) Severe icing Hail Lightning strikes (with a risk of damage to electrical systems) Radio Communications and Navigation interference from static electricity in thunderstorms

Induced drag and its wing tip vortices are a direct consequence of the creation of lift by the wing.

Since the Coefficient of Lift is large when the Angle of Attack is large, induced drag is inversely proportional to the square of the speed whereas all other drag is directly proportional to the square of the speed.

The effect of this is that induced drag is relatively unimportant at high speed in the cruise and descent where it probably represents less than 10% of total drag. In the climb, it is more important representing at least 20% of total drag. At slow speeds just after take off and in the initial climb, it is of maximum importance and may produce as much as 70% of total drag.

Finally, when looking at the potential strength of wing tip vortices, all this theory on induced drag must be moderated by the effect of aircraft weight. Induced drag will always increase with aircraft weight.