The airfoil would be symmetric and the axis of revolution would be its chord line.
Edit1: To clarify the question, suppose we have a NACA 0010. Then, using for example XFoil, I'm able to get, for example, Cd(AoA). Now, I take the airfoil, and I create a body of revolution, with the axis of revolution being the chord line of the airfoil, with the resulting body being like a teardrop. I want to know if there is a way to correlate my 2D Cd(AoA) to the 3D Cd(AoA) of the body I created, so I can predict some of its aerodynamics (with some degree of accuracy) without having to run 3D CFD analysis on it.