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Student Notes Solution - LSN 8 airfoils_1

Student Notes Solution - LSN 8 airfoils_1 - ME 387...

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Unformatted text preview: ME 387, Introduction to Applied Aerodynamics Spring 2010 STUDENT NOTES .. AA-8 You have been tasked with data reduction for a recent wind tunnel experiment on a new airfoil. The 2-D airfoil’s chord line is canted 12° with respect to the freestreamr flow of air. The conditions are SLS and your calculated Reynolds number is 3.0 x 106. The airfoil’s chord is 2 feet. Measured normal and axial forces per unit span are 152 Ib/ft and 4.9' lb/ft respectively. Calculate the 2-D lift and drag coefficients. (Answer: cl = 1.12, cd = 0.275) 7 o _ GEE/El & ’2 Adf C ” Z 94- 8 Z 0‘ OD 237% $193434; SL3 C“ ‘ ”M NEH; W; | ILL 13E; Al: LL”; ”)9 ELL: 0‘} Cg lo) Ca R": \IC Ll: N’LGS OlyA‘il‘nGa» DI: N’gmog1cA (5591 t I g? C , L, CA? ll: 2 in: fiaat‘ \)§L Wop-x +5 572M Ll : lg'l 1%.; (as i7,D « Lift ”7% m I)” ' D‘ 2 (Q/Lgm 11° + Lift mangle/{gig i,’ ; MW “/9. D”, as: ”m WNQ V5 V= limb” :. ‘M 09C. 0001373 {313: ' 7-? Maw-MW -—”\ V“: 13; ‘5 \\ memw_,..m_m \ C .r , nigh C -91.... w m WWW “’22 “2C % (0.002379%?)(233’973? 241? A «idle ‘ 2%1092378 §%)(zsrfi,g)2 (2410 r ””” T . M» \EEE) Q :7 (12?? saws M14“; 22 ...
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