Ummmm.....I'm presuming this is what you are looking for:
L = 0.5*(rho)*(V^2)*(Planform Area)*Cl
D = 0.5*(rho)*(V^2)*(Planform Area)*Cd
where L = Lift
D = Drag
rho = fluid (air?) density
V = relative freestream velocity of working fluid
Cheers,
GRUE:
Two points....
"Air acts as a fluid and therefore is incompressable at speeds below the speed of sound.."
How can you say this? Where did you go to school? Air (or any other gas for that matter), although behaves as a fluid, is extremely susceptable to compressibility...
MRM:
Bernouli does not apply for supersonic flows over a body. Shockwaves form in front of the body, instantaneously changing flow properties (pressure, temperature, etc.) from what are "freestream" to the properties over the body. However, I do believe that it is still a valid...
Freefly190:
Winglets aide in the reduction of wingtip vorticies. As I'm sure you know, aircraft are able to fly due to the physics of Bernouli's principle and airfoil shape....high pressure below the wing; low pressure above it. On a "standard" wing, of say a Cessna, the pressure...
