The following formulas are commonly used by engineers to predict the lift and drag of an airfoil: where L and Dare the lift and drag forces, V is the airspeed, S is the wing span, is the air density, and CL and CD are the lift and drag coefficients. Both CL
The following formulas are commonly used by engineers to predict the lift and drag of an airfoil: where L and Dare the lift and drag forces, V is the airspeed, S is the wing span, is the air density, and CL and CD are the lift and drag coefficients. Both CL
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
Problem 1.1MA
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Question 7
The following formulas are commonly used by engineers to predict the lift and drag of an airfoil:
where L and Dare the lift and drag forces, V is the airspeed, S is the wing span, is the air density, and CL and CD are the lift and drag coefficients. Both CL and CD depend on α , the angle of attack, the angle between the relative air velocity and the airfoil’s chord line.
Wind tunnel experiments for a particular airfoil have resulted in the following formulas.
where α is in degrees.
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