1. &l = 0 fi2 - 0 ;3 =o s; = 0 e; IO e; = 0
2. 6 cm Blade mass, m,f 47.48 kg Precone angle, &I 2.5 deg Autorotation inertia, IA-= 109.89 kg-m2 ,t? Coefficient of drag, c~ 1 0.008 Lift Curve slope, ahover 5.2 Rotor properties are given in Table 1. Aeroelastic optimization is performed at typical operating points of CT/~= 0.13 and R=565 rpm at sea level for hover and C~/a=0.05, a=458 rpm, and V = 300 knots at 16000 ft for forward flight. The lift curve slope of the airfoil is corrected to take care of compressibility effects as suggested by Ref. 18