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`C_L = (2* "L" )/( A * 1.2754 * V ^2)`

Enter a value for all fields

The **Lift Coefficient** calculator rearranges the Force of Lift equation (L = ½•A•ρ•C_{L}•V²) to compute the lift coefficient of a wing based on measurable components.

**INSTRUCTIONS:** Choose units and enter the following:

- (
**L**) - Force of Lift - (
**A**) - Wing surface area - (
**V**) - Velocity of Air over Wing - (
**ρ**) - Density of air (default is the dry air density)

**Lift Coefficient (C _{L}):** The calculator returns the lift coefficient.

The formula for the lift coefficient used in this calculator is:

`C_L = (2*L)/(A*rho*V^2)`

where:

- C
_{L}= Lift Coefficient - L = Force of Lift
- A = Wing Surface Area
- V = Velocity of Air
- ρ = density of air.

Bernoulli's principle is based on the conservation of energy, which dictates that in a steady flow of a fluid (lacking any substantial turbulence) the sum of all mechanical energy along a line of flow, a streamline, is the same at all points on that flow path. This , in turn means the sum of the potential and kinetic energy must remain constant and so with increased velocity of the flow, there is an decrease in static pressure.

From this same Bernoulli's principle we can derive the equation to calculate the lift force on a wing surface (airfoil). When the air flowing past the top surface of an aircraft wing moves faster than the air flowing past the bottom surface, Bernoulli's principle defines a difference in pressure on the two surfaces of the wing, with the lower pressure being on the upper surface where the faster flow exists.

The difference in pressure sums to a net upwards lifting force, as calculated in this equation..

The **density of air**, ρ (Greek: rho) (air density), is the mass per unit volume of Earth's atmosphere. Air density, like air pressure, decreases with increasing altitude. It also changes with variation in temperature or humidity. At sea level and at 15 °C, air has a density of approximately 1.225 kg/m^{3} (0.001225 g/cm^{3}, 0.0023769 slug/ft^{3}, 0.0765 lbm/ft^{3}) according to ISA (International Standard Atmosphere).

- At IUPAC standard temperature and pressure (0 °C and 100 kPa), dry air has a density of 1.2754 kg/m
^{3}. - At 20 °C and 101.325 kPa, dry air has a density of 1.2041 kg/m
^{3}. - At 70 °F and 14.696 psi, dry air has a density of 0.074887lb
_{m}/ft^{3}.

- Correction Angle
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- Compute the distances between coordinates
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- Force of Drag
- Force of Lift
- Lift Coefficient
- vector (3D)
- Speed Needed for Takeoff
- Physics 105
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- Wing Surface Area
- Velocity of Air over the Wing

- Wikipedia - http://en.wikipedia.org/wiki/Density_of_air