Dynamics of Hydrofoils as Applied to Naval Propellers 



0,03 0.06 0,09 0.12 0.15 0.18 0.21 



Fig. 5 - Lift coefficient at shock-free entry 

 conditions versus f /c and t /c. 



'La = P K 



cannot be put into an explicit form. In other words, it is not possible to isolate 

 the individual influence exerted upon the lift coefficient c^^ by the angle of at- 

 tack and by the thickness ratio, respectively. 



There is consequently no possibility of building up an expression of the 

 same form as relation (6) 



'La - ''a 



1 + ^, 



„ t 



in which both the values of K^ and k" may be evaluated. Theoretically, the fol- 

 lowing relation holds good: 



'La 



2ni 



(9) 



1027 



