|Feb5-10, 05:45 PM||#1|
Lift and Drag coefficient equation in terms of pressure
I have been trying to find lift and drag coefficients in terms of pressure. So far I have found multiple equations. Below is what I have found after multiple research on the web. I am using these equations in LabVIEW. My input is going to be upper and lower surface pressure and I have to find cl and cd from pressure values in LabVIEW. Here are the equations for cd and cl.
lift coefficient= integral [cp,l(x) - cp,u(x)]d(x/c)
drag coefficient = 0.5*integral[cp*cos(x)]dx
I am not sure if these equations are right or wrong. If they are wrong, can you please provide correct equations? I need these for my MS project. I have been out of school for almost 5 years now and I do not remember all the basics from my BS degree as I have not used my BS knowledge at all in last 5 years.
|Feb5-10, 06:09 PM||#2|
Hint: lift is the closed loop integral of the pressure along the surface of the wing.
I'm quite shocked you're asking such a basic question at the masters level. This is quite literally an undergraduate lab course question.
|Feb5-10, 08:03 PM||#3|
Crack open a book on aerodynamics. Wikipedia and the internet are no substitute for real learning.
|coefficient, drag, lift, pressure, wings|
|Similar Threads for: Lift and Drag coefficient equation in terms of pressure|
|Lift and Drag component question||Aerospace Engineering||3|
|Fluid Mechanics - Drag coefficient and Pressure coefficient||Mechanical Engineering||1|
|Lift and Drag||Mechanical Engineering||1|
|lift and drag distribution||Engineering, Comp Sci, & Technology Homework||0|
|Projectile Motion with Lift and Drag||Classical Physics||2|