Bernoulli's Equation and Lift Formula

The explaination (definition) of Bernoulli’s Equation:

Bernoulli’s Equation states that in fluid flow, an increase in velocity occurs simultaneously with decrease in pressure.

Bernoulli's Equation Assumes:

points 1 and 2 lie on a streamline,

the fluid has constant density,

the flow is steady, and

there is no friction.

The Equation for lift is:

L=(1/2) d v² s CL

Where the variables are:

L = Lift

d = density of the air. This change with altitude.

v = velocity of an aircraft (feet per second)

s = the wing area of an aircraft (square feet)

CL = Coefficient of lift (determined by airfoil type and angle of attack)

Tables and Charts:

Coefficient of Lift /Angle of Attack Table

I.C.A.O. Standard Atmosphere Table

Altitude          Density     Speed of Sound
(Feet)             (d)         (Knots)
        0          .002377          661.7
1,000          .002308          659.5
2,000          .002241          657.2
3,000          .002175          654.9
4,000          .002111          652.6
5,000          .002048          650.3
6,000          .001987          647.9
7,000          .001927          645.6
8,000          .001868          643.3
9,000          .001811          640.9
10,000          .001755          638.6
15,000          .001496          626.7
20,000          .001266          614.6
25,000          .001065          602.2
30,000          .000889          589.5
35,000          .000737          576.6
36,089          .000706          573.8
40,000          .000585          573.8
45,000          .000460          573.8
50,000          .000362          573.8
55,000          .000285          573.8

1 knot = 1 nautical mile per hour = 6,076 ft per hour
1 mph = 1 mile per hour = 5,280 feet per hour

These definitions are based on Boeing Education’s “Forces of Flight” lesson plans and Wikipedia. Tables and charts found on the NASA Aerodynamics website.