The Lift Coefficient calculator rearranges the(L = ½•A•ρ•CL•V²) to compute the lift coefficient of a wing based on measurable components.
INSTRUCTIONS: Choose units and enter the following:
Lift Coefficient (CL): 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)`
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/m3 (0.001225 g/cm3, 0.0023769 slug/ft3, 0.0765/ft3) according to ISA (International Standard Atmosphere).