<=> 



READ INPUTS, PROPELLER GEOMETRY, RPM, THRUST (OR POWER) 



a, ADVANCE SPEED, APPROXIMATE TAN (3 ; 

 LEADING-EDGE CAVITY THICKNESS, BASIC CAMBER SHAPE, ETC. 



INFINITE CAVITY SUPERCAVITATING CASCADE THEORY 

 (DRAG-LIFT RATIO, FOIL CAVITY SHAPES, SHOCK FREE ANGLES, 



PRESSURE DISTRIBUTIONS, ETC.) 



FINITE CAVITY, CORRECTIONS FOR VARIOUS CAVITY LENGTHS 



(TO STORE THE RESULTS) 



I 



OBTAIN LIFTING LINE CALCULATIONS, 

 INDUCED VELOCITIES, C L a/C L 



NEW TAN 0j USING 

 NEWTON RAPHSON 

 METHOD 



CALCULATE FINITE CAVITY EFFECT 



ON C L COMPUTE THRUST 



(OR POWER) 



ADJUST THF LEADING 



EDGE CAVITY THICKNESS 



TO HAVE THE MINIMUM 



CAVITY LENGTH 



CALCULATE POWER (THRUST) 



EFFICIENCY, PITCH DIAMETER RATIO 



BENDING MOMENT, ETC. 



f STOP J 



Figure 1 



Flow Chart of Computer Program of the Preliminary 

 Design of Supercavitating Propeller 



and the section drag-lift ratio, in addition to all of the cascade section data such as the foil cavity 

 shape, the pressure distribution, and the leading-edge thickness. The cascade section data are also to 

 be used for the lifting-surface theory of supercavitating propellers as a leading term of the three- 

 dimensional cavity solution. 



The computer execution time on CDC 6700 is about 80 seconds to produce all of the informa- 

 tion for preliminary propeller design. 



