Axk'iC^''^.^:^) 



Yamazaki 



A,k'i(^',^.^;^) =■ 



VC202 + <f' 2 +^2_ 2^'^COS [^+ 277(k' - 1)/N]^ 



3z/^i//{^V- ^ sin [>//+ 277(k' - 1)/N]} 

 yj,2^2 +^'2 +^2 _ 2^'^ COS [0+ 277 (k' - 1)/TM]^ 



y COS [0+2 77 (k' - 1)/N] 



77.20^2 + ^-2 +^2_ 2^'^COS [0+ 277(k' - 1)/N]^ 



3i^^' sin [0+ 277(k' - 1)/N] {^'0- ^ sin [0+ 277(k'- 1)/N]} 

 + . 



yj,202+^'2 +^2_ 2^'^ COS [0+ 277(k'- 1)/N]^ 

 '/'O = ^m(^') - %(^) + ^(^') ^'-^(^) ^ • .,,..,: . (120) 



Substituting Eqs. (116) and (117) into Eqs. (112) we get 



1 1 



V* -1 f i/l - ^ V dv V* - - f l/^ ~ ^ V dv V* =y V* 6'"^*= 



""1 "1 n 



(121) 



Hence, from Eqs. (52) and (53) we get the section lift coefficient C^L(f,s) and 

 the section viscous drag coefficient Cp^: 



> G (^) e "^ 



^ (122) 



e(^)Wi;(^, -s^)y^'2 + ^2 ^ ^ 



Substituting Eqs. (109), (110), (114), and (116) into Eqs. (85) and (86), and 

 referring to Eqs. (121), we obtain the force and moment acting on the propeller 

 as 



%x - ^FxO + *^FxD ' %y " ^FyO + ^FyD ' %z ' ^FzO "'' ^FzD 



where 



(123) 



^Bk=l n.n' -1 (124) 



(Cont) 



58 



