The drag of an airfoil at zero angle of attack is a function of density, viscosity, and velocity, in addition to a length parameter



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and D are the unknowns


c3



c3 is known
where
c4 is known
Solution Procedure:
(i) Assume a value for f
(ii) Calculate D from

(iii) Calculate

(iv) Calculate Re from

(v) Using and Re, determine f



(vi) Compare f obtained in (v) with f assumed in (i). If the two values are approximately the same, STOP. If not, repeat steps (ii) through (v) until convergence is attained

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