The total lift on the model airplane is calculated by finding the pressure difference between the top and bottom surfaces of the wing, then multiplying this difference by the wing's area and by 2 to account for both wings. The lift is 800 newtons.
Step-by-step explanation:
To calculate the total lift on the model airplane, we must apply the concept of pressure differential. Lift (L) can be calculated by the difference in pressure between the top (Ptop) and bottom (Pbottom) surfaces of the wings multiplied by the surface area (A) of one side of the wings. Since there are two wings, we multiply the result by 2 to get the total lift.
Step 1: Calculate the pressure difference.
ΔP = Pbottom - Ptop
ΔP = (9.0 x 10´4) N/m² - (8.8 x 10´4) N/m²
ΔP = 0.2 x 10´4 N/m²
Step 2: Calculate the lift generated by one wing.
L = ΔP × A
L = (0.2 x 10´4) N/m² × 2.0 m³
Step 3: Multiply by 2 to account for both wings.
Total lift = L × 2
Total lift = (0.2 x 10´4 N/m² × 2.0 m³) × 2
Total lift = 800 N
Therefore, the total lift on the model airplane is 800 newtons.