Flow, from a Disturbed Area. 441 



+ 1. 



c(w-d) 



dz = 1 ^_ b ~_ Vw c (b -^ ) \ .... (5), 



dw q " s/\ 



IV 



,\ = and ^ — > and the rigid boundary 



BC is described. 



In general C will not coincide with C but, since 0<d< 1 

 the constants may be adjusted so that CB = C'B if required. 

 It is important to notice that q has at least one turning value 

 over BC ; , viz. at values of w given by 



(l-bs/w)(b-^w) 2 =r 2c{l-w){b^^-d), 



This is in agreement with experiments on the pressure 

 behind an aerofoil. 



c{w-d) 



dz __ — i(b—Vw) ( 6 _ v^; 2 /g\ 



= —tt/2, gi=0 5 and # — >0 as w—^b' 2 . 



The point w = 6 2 lies inside the domain B . 

 Hence the semi-infinite straight boundary CD' is 

 described. 



(iii.) Examinatiqn of the solution. 



Since the w-plane is cut along the positive real axis, and 

 w = 0, 1 and b 2 are excluded by small circles, 



•*-$ • • " s) 



+ -' v /v / (<?-l)'- , + f--T*-'l)- (9) 

 v2 



iv = t (io) 



