Propeller Design Assignment Fall 2006 A lifting line code (PVL) is setup and run for a particular propeller design. The input file and resulting design output file are attached. The input file gives the operating point specifics as well as the inflow distribution and design chordlength distribution on the propeller. The full scale propeller runs on a ship with the following characteristic: Diameter: 5 m Ship Speed: 13 m/s RPM: 156 Required Propeller thrust: 991.5 kN Depth at Prop Centerline: 8m Vapor pressure: 2500 Pa Water Density: 997 kg/m3 Axial inflow velocity variation +/-1 m/s The output file shows the non-dimensional circulation distribution G, induced velocities Flow angles and drag coefficient. 1)Find the optimal efficiency for this propeller from Kramer’s Diagram Using the data for a NACA a=0.8 meanline and NACA 65A010 Thickness section determine the blade section design at the r/R=0.697 radius. The max. thickness of this section is chosen at to/C = 0.04 2) Find the lift coefficient for this section as well as the camber ration fo/c and proper angle of attack 3). Determine the blade angle and pitch P/D for this section. 4).Will this section cavitate at this radius under the design operating conditions for this ship? Use Brockett diagram to estimate 5). Use the matlab m-file vlm.m provided to analyze the 2D section at ideal angle of attack. Plot the pressure distribution Cp vs. chordwise position. At what position on the blade would cavitation first occur under these conditions?PVL input file 32 : NUMBER OF VORTEX PANELS OVER THE RADIUS 10 : MAXIMUM ITERATIONS IN WAKE ALIGNMENT 1 : HUB IMAGE FLAG: 1=YES, 0=NO 0.5 : HUB VORTEX RADIUS/HUB RADIUS 11 : NUMBER OF INPUT RADII 5 : NUMBER OF BLADES 1.0 : ADVANCE COEFFICIENT, J, BASED ON SHIP SPEED 0.600 : DESIRED THRUST COEFFICIENT, CT 0.000 : HUB UNLOADING FACTOR: 0.0=OPTIMUM (NO UNLOADING) 0.000 : TIP UNLOADING FACTOR 1.0=REDUCED LOADING 1.000 : CRP SWIRL CANCELLATION FACTOR: 1.0=NO CANCELLATION r/R c/D Cd Va/Vs Vt/Vs 0.20000 0.17400 0.00800 1.00000 0.00000 0.25000 0.19700 0.00800 1.00000 0.00000 0.30000 0.22900 0.00800 1.00000 0.00000 0.40000 0.27500 0.00800 1.00000 0.00000 0.50000 0.31200 0.00800 1.00000 0.00000 0.60000 0.33700 0.00800 1.00000 0.00000 0.70000 0.34700 0.00800 1.00000 0.00000 0.80000 0.33400 0.00800 1.00000 0.00000 0.90000 0.28000 0.00800 1.00000 0.00000 0.95000 0.24000 0.00800 1.00000 0.00000 1.00000 0.00200 0.00800 1.00000 0.00000PVL output design for assignment Ct= 0.6000 Cp= 0.8392 Kt= 0.2356 Kq= 0.0524 Va/Vs= 1.0000 Efficiency= 0.7150 r/R G VA VT UA UT BETA BETAI Chord/D CD 0.20048 0.012889 1.00000 0.00000 0.05119 -0.10192 57.796 63.334 0.17419 0.00800 0.20433 0.012905 1.00000 0.00000 0.05276 -0.10307 57.303 62.895 0.17576 0.00800 0.21199 0.012995 1.00000 0.00000 0.05590 -0.10527 56.337 62.031 0.17890 0.00800 0.22338 0.013231 1.00000 0.00000 0.06060 -0.10830 54.940 60.770 0.18377 0.00800 0.23840 0.013668 1.00000 0.00000 0.06681 -0.11187 53.168 59.154 0.19082 0.00800 0.25691 0.014331 1.00000 0.00000 0.07443 -0.11565 51.093 57.237 0.20106 0.00800 0.27872 0.015217 1.00000 0.00000 0.08328 -0.11929 48.794 55.078 0.21512 0.00800 0.30362 0.016295 1.00000 0.00000 0.09313 -0.12245 46.353 52.745 0.23122 0.00800 0.33138 0.017522 1.00000 0.00000 0.10367 -0.12490 43.848 50.304 0.24637 0.00800 0.36172 0.018842 1.00000 0.00000 0.11458 -0.12645 41.347 47.820 0.26003 0.00800 0.39436 0.020199 1.00000 0.00000 0.12552 -0.12706 38.909 45.350 0.27285 0.00800 0.42898 0.021538 1.00000 0.00000 0.13619 -0.12674 36.576 42.941 0.28614 0.00800 0.46524 0.022811 1.00000 0.00000 0.14637 -0.12559 34.379 40.631 0.29986 0.00800 0.50281 0.023974 1.00000 0.00000 0.15588 -0.12376 32.336 38.448 0.31291 0.00800 0.54131 0.024990 1.00000 0.00000 0.16461 -0.12139 30.457 36.408 0.32415 0.00800 0.58037 0.025826 1.00000 0.00000 0.17251 -0.11866 28.743 34.522 0.33326 0.00800 0.61963 0.026454 1.00000 0.00000 0.17959 -0.11570 27.190 32.792 0.34021 0.00800 0.65869 0.026847 1.00000 0.00000 0.18587 -0.11264 25.792 31.218 0.34487 0.00800 0.69719 0.026981 1.00000 0.00000 0.19139 -0.10959 24.540 29.795 0.34696 0.00800 0.73476 0.026830 1.00000 0.00000 0.19621 -0.10661 23.423 28.516 0.34610 0.00800 0.77102 0.026376 1.00000 0.00000 0.20041 -0.10376 22.433 27.373 0.34147 0.00800 0.80564 0.025599 1.00000 0.00000 0.20404 -0.10110 21.559 26.359 0.33205 0.00800 0.83828 0.024490 1.00000 0.00000 0.20715 -0.09865 20.793 25.465 0.31757 0.00800 0.86862 0.023042 1.00000 0.00000 0.20982 -0.09643 20.126 24.683 0.30007 0.00800 0.89638 0.021261 1.00000 0.00000 0.21207 -0.09445 19.550 24.006 0.28231 0.00800 0.92128 0.019161 1.00000 0.00000 0.21396 -0.09271 19.060 23.428 0.26639 0.00800 0.94309 0.016764 1.00000 0.00000 0.21552 -0.09123 18.650 22.943 0.24822 0.0080 0.96160 0.014101 1.00000 0.00000 0.21677 -0.08999 18.316 22.546 0.22128 0.00800 0.97662 0.011213 1.00000 0.00000 0.21775 -0.08901 18.052 22.233 0.18391 0.00800 0.98801 0.008143 1.00000 0.00000 0.21847 -0.08827 17.857 22.001 0.13812 0.00800 0.99567 0.004940 1.00000 0.00000 0.21894 -0.08778 17.729 21.848 0.08618 0.00800 0.99952 0.001656 1.00000 0.00000 0.21917 -0.08754 17.665 21.772 0.03048