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Obtain the location of the center of pressure and aerodynamic center for a NACA 0009 airfoil by assuming that the thin airfoi

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from thin alofoil theory C r= sa r CG) de 1.9 S160) sine do [f=% (1–1050)] in polar-co-ordinat Vco) 2 Va (Hos o xa [a= angleoCoefficient of lift le = L Y la Va? Ce 2x Sa Vd ² x π c xa Sa Va 2c Ce = 2ТТ Moment about LE Mib (pee unit span) - So Verx pMLE 11 Sd Vd ² x Tlx xc² Coefficient of moment Cmme CALE MILE Yz Sd Vd 2 c2 CALE -TX CmLE = - Xcp * CL С Xcp Location of centquarter chood Cml/4= 9 CALE t Cmc/a + -la t ald Cmela centae ocaus Mis means the aerody aerodynamic et quarter chood point Xc

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