Principles Of Flight Trivia Quiz

By changing the angle of attack of a wing, a pilot can control the airplane's lift, airspeed, and drag. The angle of attack refers to the angle between the wing's chord line and the direction of the oncoming airflow. By increasing or decreasing the angle of attack, the pilot can adjust the amount of lift generated by the wing. This, in turn, affects the airspeed of the aircraft. Additionally, changing the angle of attack also alters the amount of drag experienced by the airplane. Therefore, by adjusting the angle of attack, the pilot can control all three variables: lift, airspeed, and drag.

As the speed of an airplane increases, it causes more lift. This is because lift is directly proportional to the speed of the airplane. As the speed increases, the air flowing over the wings increases, creating more lift. Therefore, the correct answer is "The more lift it will cause."

All of these factors affect the stall speed of an aircraft. The stall speed is the minimum speed at which an aircraft can maintain level flight. Total weight affects the stall speed because a heavier aircraft requires a higher speed to generate enough lift to counteract the weight. Load factor, which is the ratio of the lift force to the weight of the aircraft, also affects the stall speed as it determines the amount of lift produced. The location of the center of gravity is important because it affects the stability and control of the aircraft, which in turn affects the stall speed.

The elevator controls the motion of the airplane for longitudinal stability. The elevator is located on the horizontal tail surface of the airplane and it is responsible for controlling the pitch motion of the aircraft. By changing the angle of the elevator, the pilot can control the nose-up or nose-down attitude of the airplane, which helps maintain stability during flight. This control surface is crucial for maintaining the desired altitude and preventing the airplane from pitching uncontrollably.

When an airplane leaves ground effect, it moves away from the ground and the cushioning effect of the air trapped between the airplane and the ground is lost. This results in a decrease in lift and an increase in induced drag. To compensate for the increased drag, the airplane requires more thrust. Therefore, the correct answer is that an airplane leaving ground effect will experience an increase in induced drag and require more thrust.

When an aircraft is in ground effect, it experiences a cushioning effect due to the ground surface. This effect reduces the downwash and increases the lift generated by the wings. To maintain the same lift while in ground effect, the plane needs a lower angle of attack. A lower angle of attack reduces the drag and allows the aircraft to maintain the same lift force with less resistance.

When the load factor is zero, it means that there is no force acting upon the occupants. In this case, they would feel weightless because there is no gravitational force or any other force pushing or pulling them in any direction. This is similar to the feeling of weightlessness experienced by astronauts in space where they are not influenced by the Earth's gravity.

Stall speed is the minimum speed at which an aircraft can maintain level flight. It is affected by several factors, including weight, load factor, and power. Weight plays a significant role as a heavier aircraft will require a higher speed to generate enough lift to counteract its weight. Load factor, which is the ratio of the lift force to the aircraft's weight, also affects stall speed. Higher load factors increase the stall speed. Additionally, power is a crucial factor as it determines the thrust produced by the engines, which affects the aircraft's ability to maintain level flight and avoid stalling.

Transonic airflow refers to the speed regime in which an aircraft is approaching the speed of sound. It occurs between Mach 0.8 and 1.2, which means that the aircraft is traveling at speeds between 80% and 120% of the speed of sound. In this regime, the airflow around the aircraft becomes highly turbulent and can cause significant drag and control issues. Therefore, it is important for aircraft designers and pilots to understand and account for transonic airflow when operating in this speed range.

As the airplane goes beyond the critical Mach number, there is a sudden decrease in the drag coefficient. This is because the critical Mach number is the speed at which the airflow over certain parts of the aircraft reaches the speed of sound. Beyond this point, the airflow becomes supersonic, causing a decrease in drag due to the shockwaves that form. This sudden decrease in drag coefficient allows the aircraft to fly faster with less resistance.