Determine lift coefficient, Mechanical Engineering

A thin spanwise symmetrical wing has an aspect ratio of 10 and a straight edges with  taper ratio (tip chord / root chord) of 0.8 and root chord of 1 m. This wing does not have geometric or aerodynamic twist and it has symmetrical airfoil profile.

a.  Compute, using 4 terms in the expansion, the spanwise efficiency factor,  e, and plot its drag polar if its zero-lift drag is 0.01. 

Hint: Since this wing is spanwise symmetrical, only odd-n terms matter, and thus 4 term- expansion here really means 4 terms involving

odd n's only. For this problem, it will be easier to use software like Excel or MATLAB  to solve the simultaneous algebraic equations.

b.  Determine  lift coefficient and induced-drag coefficient of the wing at an angle of attack of 4o.

Posted Date: 4/2/2013 6:40:20 AM | Location : United States







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