Draw flowchart that will use the modern lift equation to calculate the average lift force of 5 input values provided below. The modern lift formula: lift in Newtons air density in velocity in Wing area in angel of the wing This formula is used to calculate the lift produced by airplane wings.

Sol50:

1. Define the constants: Pi = 3.1416
2. Initialize the total_lift to 0 and the count to 0
3. For i in range (1 to 5):

Read in the values of r, V, A, and angle of wing from the user

Calculate the lift using the modern lift equation

Add the lift to the total_lift

Increment the count by 1

1. End for loop
2. Calculate the average_lift by dividing the total_lift by the count
3. Display the value of average_lift

Note: The modern lift equation in step 5 can be represented as L = Cl * (r * V^2) / 2 * A.