Explanation:
The changes can be made in airplane longitudinal control to maintain altitude while the airspeed is being decreased is
We can increase the angle of attack this would compensate for the decreasing lift. As the angle of attack directly controls the distribution of pressure on the wings. Moreover, increase in angle of attack will also cause the drag to increase.
Answer:
The normal force will be "122.8 N".
Explanation:
The given values are:
Weight,
W = 100 N
Force,
F = 40 N
Angle,
θ = 35.0°
As we know,
⇒ 
On substituting the given values, we get
⇒ 
⇒ 
⇒ 
Strange as it may seem, I don't think ANY of those choices will work. Anybody else ?
Answer:
Where's the question or the picture???
