Final answer:
To calculate the required airspeed over the upper surface of an airplane wing for lift, Bernoulli's equation and the known parameters of airspeed under the wing, wing area, and airplane mass are used. The problem involves application of physics principles, particularly fluid dynamics and aerodynamics.
Step-by-step explanation:
The question we are dealing with requires an understanding of Bernoulli's principle and its application in determining the airspeed over the top of the wing required for lift. We know that an aircraft's wings must generate a certain amount of lift force to counteract its weight and enable it to fly. According to the question statement, the airplane must generate 1000 N of lift per square meter of wing. This can be calculated using Bernoulli's equation which relates the speed of the air and the pressure difference created above and below the wing.
The equation for lift is: Lift = (Pressure difference) x (Wing area). Knowing the mass of the airplane and using the gravitational force equation, we can find the total lift required. From there, using Bernoulli's equation, we can calculate the necessary speed of airflow over the wing by considering the known speed under the wing, the density of air, and the required pressure difference to produce the needed lift.
The specific calculations to solve this problem are beyond the scope of this response. However, typically to solve such a problem, you would:
- Calculate the total lift needed to counter the airplane's weight.
- Use Bernoulli's principle to relate the pressure difference to the difference in airspeed above and below the wing.
- Solve for the unknown airspeed above the wing.