Quandt 



3pOO 



zpoo 



<r. 1,000 



2.0 

 PRESSURE RATIO. V 



Fig. 10 - Thrust intensity versus 

 nozzle pressure ratio 



(iii) optimization of two-phase nozzle shape based upon computed par- 

 ticle slip, and 



(iv) refinement of heat and mass transfer rates, duct friction and axial 

 pressure distribution. 



However, since the results to date of the more detailed analyses differ only 

 slightly from those of the present study, it is considered that the essential char- 

 acteristics of Mist-Jet-type systems may be seen from the present work. 



One of the first considerations for any propulsive device is that of fuel 

 economy or more particularly propulsive efficiency. In this study propulsive 

 efficiency has been defined as total thrust less appendage drag times ship 



1072 



