consider an airfoil at 12o angle of attack. the normal and axial force coefficients are 1.2 and 0.03, respectively. calculate the lift and drag coefficients.



Answer :

The coefficient of lift is 1.17

C1 = Cn cos α - Ca sin α

Here, α

Cn is the normal force coefficient, and Ca is Substitute 12· for the axial force coefficient for α

C1 = 1.2cos12.-0.03sin 12.

= 1.16

≈1.17

What is the coefficient of normal force?

The Greek letter mu () typically serves as a symbol for it. From a mathematical perspective, = F/N, where F is the normal force and N is the frictional force. The coefficient of friction has no dimensions because both F and N are measured in force units like newtons or pounds.

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