Lift Force Calculator

Lift Force Calculator:

Enter the values of Lift Coefficient, Cl, Area, A_(m2), Density, d_(kg/m3)and Velocity squared, V_(m/s)to determine the value Lift Force, Fl_(N).

Enter Lift Coefficient :
Enter Area:		m2
Enter Density:		kg/m3
Enter Velocity:		m/s
Result -Lift Force:		N

Lift Force :

Lift force is the aerodynamic force exerted at a right angle to the direction of motion of an object as it moves through a fluid, usually air.It is responsible for lifting aircraft into the sky and is generated due to the pressure difference between the upper and lower surfaces of a wing or airfoil.

This pressure difference arises due to the variation in airflow speed, explained by Bernoulli’s principle.Lift is influenced by various factors including the wing’s shape (airfoil), the angle of attack, the object’s velocity, the density of the fluid, and the surface area in contact with the airflow.

As the fluid velocity increases over the wing, the pressure on top decreases, generating a net upward force.Lift is essential in aviation, sports, and fluid mechanics to understand and control object motion in air or other fluids.

The coefficient of lift (Cl) is a dimensionless value that represents the influence of wing shape and the angle of attack on lift. The lift force rises with an increase in velocity, surface area, or fluid density.

Airplanes are designed with wings that maximize lift while minimizing drag to improve flight efficiency.Lift is also relevant in designing turbine blades, cars (to reduce lift), and sports balls (to manipulate trajectories).

Proper understanding and calculation of lift are essential in mechanical, aerospace, and civil engineering.The fluid density (d) is typically measured in kg/m³, and velocity (V) in m/s.

The wing area (A) is usually in square meters (m²), and the lift force (Fl) is in Newtons (N).The formula calculates the total lift produced based on these variables under steady conditions.

Lift Force, Fl_(N)in Newton equals the Lift Coefficient, Cl multiplied by the Area, A_(m2)in metres multiplied by the product of Density, d_(kg/m3)in kilograms per cubic metres and Velocity squared, V_(m/s)in metres per second divided by 2.

Lift Force, Fl_(N) = Cl * A_(m2)* (d_(kg/m3)* V²_(m/s)) / 2

Fl_(N) = lift force in Newtons, N.

Cl = lift coefficient.

A_(m2)= area in square metres, m².

d_(kg/m3)= density in kilograms per cubic metres, kg/m³.

V_(m/s)= velocity in metres per second.

Lift Force Calculation:

1. A plane wing has a lift coefficient (Cl) of 1.2, an area (A) of 20 m², a velocity (V) of 60 m/s, and air density (d) of 1.225 kg/m³. Calculate the lift force.

Given: Cl = 1.2, A_(m2)= 20m², d_(kg/m3)= 1.225kg/m³, V_(m/s)= 60m/s.

Lift Force, Fl_(N) = Cl * A_(m2)* (d_(kg/m3)* V²_(m/s)) / 2

Fl_(N) = 1.2 * 20 * (1.225 * 60²) / 2

Fl_(N) = 1.2 * 20 * 4410 / 2

Fl_(N) = 105840 / 2

Fl_(N) = 52920N.

2. A wing generates a lift force (Fl) of 25,000 N, has an area (A) of 15 m², velocity (V) of 50 m/s, and air density (d) of 1.2 kg/m³. Find the lift coefficient (Cl).

Given: Fl_(N) = 25000N, A_(m2)= 15m², d_(kg/m3)= 1.225kg/m³, V_(m/s)= 50m/s.

Lift Force, Fl_(N) = Cl * A_(m2)* (d_(kg/m3)* V²_(m/s)) / 2

Cl = 2 * Fl_(N) / A_(m2)* d_(kg/m3)* V²_(m/s)

Cl = 2 * 25000 / 15 * 1.225 * 50²

Cl = 50000 / 45000

Cl = 1.111.