# How to determine the thickness of an airfoil?

In calculation or designing, how to determine the airfoil thickness? What is the guideline or consideration in designing airplane's wing? We all know that the bulge (the ticker in the airfoil) is required to apply Bernoulli principle, to create low pressure above the wing. But how to bind the round nose shape requirement to the design requirement. In this case, to make the airplane to be efficient (especially related to the power consumption).

This airfoil is required for an airplane as I explained here. Maximum weight will be 400kgs, and the maximum speed will be 200km/h.

• We all know that the bulge (the ticker in the airfoil) is required to apply Bernoulli principle, to create low pressure above the wing. You may want to read up on that assumption. See related questions on airfoil thickness, equal transit time fallacy and how wings generate lift – Sanchises Dec 9 '18 at 8:48
• Sorry, I may have misunderstood what you meant with "bulge". I edited the question and replaced "bulge" with thickness, is that what you mean or do you mean Nose Shape? – Koyovis Aug 6 at 6:01

• For good max $$C_L$$ a value from the sweet spot between 12 and 15 should be selected, see below = fig 7-9 from Torenbeek.