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8 ,---,---,----,-----,-----.--, 1.".50"\ 0.6 Conventional section (NACA 23015) Laminar-flow section (NACA 662-215) a a Lc---: ----,...

Problem 9.160, Introduction to Fluid Mechanics 7th Edition; Fox, Pritchard, McDonald; please see attached file
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1.8 ,---,---,----,-----,-----.--, 1.6 1.4 0.8 0.6 Conventional section (NACA 23015) 0.2 a vL~ --, 1.6 CI.".,= 1.50"\ 1.4 0.8 0.6 Laminar-flow section (NACA 66 2 -215) a V Lc---:----. .. ----, - OL---"-----'-----'----'---'---' o O'---. ....l. .----'----'-----'---- 4 8 12 16 20 0 4 8 12 16 Angle of attack, a (deg) Angle of attack, a (deg) (a) Lift coefficient vs. angle of attack 0.020 ...--. ..----.---,---<)---,.-, 0.016 Co 0.012 Conventional section (NACA 23015) 0.004 O'----L-~--~-~--~ o 0.020 ,---. ..---.---,----,-----;c-- 0.016 CD 0.012 0.008 O'-----'----'----'----. ..... L.--~ 4 8 12 16 20 0 4 8 12 16 Angle of attack, a (deg) Angle of attack, a (deg) (b) Drag coefficient vs. angle of attack Fig. 9.17 Lift and drag coefficients versus angle of attack for two airfoil sections of 15 pe thickness ratio at Re; = 9 x 10 6 . (Data from [21).) Laminar-flow section (NACA 66 2 -215) 2C
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