This problem has been solved!


Do you need an answer to a question different from the above? Ask your question!

Problem 3: The airfoil NACA 2418, considering a chord-based Reynolds number of: Re = 5. 105, has a lift coefficient of: CL = 0.25 at zero angle of attack. Assuming the C₂ - a slope of the first-order approximation, calculate the lift coefficient at 5°. а For the same airfoil in the same conditions, at C₁ = 0.15 the

image
Related Book For  answer-question

Fundamentals Of Aerodynamics

6th Edition

Authors: John Anderson

ISBN: 9781259129919