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Unformatted text preview: Spring 2004 Uniﬁed Engineering
Fluids Problems F8
F8. A wing is to have an elliptic circulation distribution.
�(y ) = �0 � 2y
� �2 The planform is to b e a straight taper, with root and tip chords deﬁned in terms of the
average chord cavg and the taper ratio r = ct /cr .
cr = cavg 2
1+r ct = cavg 2r
1+r a) Deﬁne the chord distribution c(y ) in terms of cavg and r . Assuming cavg /b = 0.125, draw the planforms for r = 0.75, 0.5, 0.25. b) Determine the spanwise c� (y ) distribution, and plot for r = 0.75, 0.5, 0.25. Note: Only the shape of the c� (y ) curve is of interest. All scaling constants like �0 , cavg , etc. can b e set to unity for plotting purposes. c) Local stall is obviously undesirable. If the airfoil is the same across the span, which taper ratio appears to b e most attractive for the purpose of giving the largest stall margin everywhere on the wing? ...
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This note was uploaded on 01/28/2012 for the course AERO 16.01 taught by Professor Markdrela during the Fall '05 term at MIT.
- Fall '05