Max L/D Ratio: Aircraft Drag Polar Explained

[Engineering77744]

TL;DR Summary

Would like help as to the method rather than the answer please. Classes havent been very clear therefore everything is self taught. Many thanks.

' The Drag polar for an aircraft is given by:

CD = 0.025 + 0.08 C^2L

What is the maximum Lift to Drag ratio '

Would like help as to the method rather than the answer please. Classes haven't been very clear therefore everything is self taught. Many thanks. ' The Drag polar for an aircraft is given by:

CD = 0.025 + 0.08 C^2L What is the maximum Lift to Drag ratio '

 

[jrmichler]

Given that you are trying to understand the concept, a good approach is to:

1) Plot the curve of $C_L$ vs $C_D$,
then
2) Calculate and plot L/D as a function of $C_L$.

When finished with that, search drag polar. The Wikipedia Drag Curve article looks pretty good.