RESULTS AND DISCUSSIONS 

 The procedure to calculate the pressure distribution presented in the .pre- 

 ceding section has been applied to the following configurations: 



1. Two-dimensional airfoil sections; flat plate, NACA 0012 and NACA 4412 

 sections 



2. IHI Propeller MP 282 



3. DTNSRDC Propeller 4718 



4. NSMB Model Propeller 



5. DTNSRDC Propeller 4118 



6. DTNSRDC Propeller 4498 



The geometric characteristics of these propellers are summarized in Table 1. The 

 predictions by PSP are compared with either experimental measurements or other 

 theoretical predictions. 



TWO-DIMENSIONAL AIRFOIL SECTIONS 



In order to test the validity of the discrete vortex/source lattice method for 

 pressure computation, a computer program, F0IL2D, was developed for computing the 

 pressure distribution on two-dimensional airfoil sections. F0IL2D has all the 

 ingredients of the discrete vortex/source lattice method except for three-dimen- 

 sional effects. 



Figure 7 shows the comparison of the predicted pressure distribution on a flat 

 plate with an angle of attack a = 4 degrees by F0IL2D with the analytical solution in 



Reference 20. In Figure 8, the pressure distribution is compared for the analytical 



20 

 solution and the F0IL2D predictions on the NACA 0012 section at zero angle of 



attack. In Figure 9, measured pressure distribution on NACA 4412 section at 



a = 6.4 degrees is compared with predictions by different methods including F0IL2D. 



Agreements between the predictions by F0IL2D and experiments as well as those 



between the former and other prediction methods are excellent for two-dimensional 



shapes . 



IHI MODEL PROPELLER MP 282 



The open-water performance and the pressure distribution were computed on the 

 Ishikawajima-Harima Heavy Industries (IHI) large model propeller MP 282 operating 

 in uniform flow. The diameter of the propeller is 0.95 m. This propeller has 

 radially varying meanline and thickness distribution. The predictions are 



