Cambered plate C=12% T=5% R=1.1 (cp-120-050-gn)
Cambered plate C=12% T=5% R=1.1 - HAWT pipe blade with coordinates based on top surface. Camber=12% Wall thickness=5% Radius=1.102
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(cp-120-050-gn) Cambered plate C=12% T=5% R=1.1 HAWT pipe blade with coordinates based on top surface. Camber=12% Wall thickness=5% Radius=1.102 Max thickness 6.1% at 4% chord. Max camber 9.9% at 47.9% chord Source Generated Source dat file The dat file is in Selig format |
Cambered plate C=12% T=5% R=1.1 1.000000 0.000000 0.979219 0.010310 0.958226 0.020181 0.937030 0.029607 0.915640 0.038585 0.894065 0.047110 0.872316 0.055180 0.850402 0.062789 0.828332 0.069936 0.806117 0.076616 0.783766 0.082827 0.761289 0.088566 0.738697 0.093830 0.715998 0.098618 0.693204 0.102926 0.670324 0.106754 0.647369 0.110099 0.624348 0.112960 0.601272 0.115335 0.578152 0.117224 0.554996 0.118626 0.531816 0.119540 0.508622 0.119966 0.485425 0.119904 0.462233 0.119352 0.439059 0.118313 0.415911 0.116786 0.392801 0.114772 0.369739 0.112272 0.346734 0.109287 0.323797 0.105817 0.300938 0.101866 0.278167 0.097435 0.255495 0.092525 0.232931 0.087138 0.210486 0.081278 0.188169 0.074946 0.165990 0.068146 0.143959 0.060880 0.122087 0.053153 0.100381 0.044966 0.078853 0.036324 0.057512 0.027231 0.036367 0.017690 0.015427 0.007706 0.012824 0.006251 0.010393 0.004524 0.008164 0.002543 0.006161 0.000334 0.004410 -0.002080 0.002929 -0.004669 0.001737 -0.007402 0.000847 -0.010248 0.000271 -0.013174 0.000014 -0.016145 0.000080 -0.019127 0.000468 -0.022084 0.001173 -0.024981 0.002188 -0.027786 0.003499 -0.030464 0.005093 -0.032984 0.006950 -0.035318 0.009048 -0.037437 0.011363 -0.039317 0.013868 -0.040936 0.016533 -0.042274 0.019327 -0.043316 0.022217 -0.044050 0.025170 -0.044467 0.028151 -0.044563 0.031124 -0.044336 0.034056 -0.043788 0.036911 -0.042927 0.039656 -0.041762 0.060205 -0.031974 0.080962 -0.022634 0.101917 -0.013748 0.123061 -0.005320 0.144383 0.002647 0.165873 0.010148 0.187521 0.017179 0.209317 0.023739 0.231250 0.029822 0.253310 0.035428 0.275488 0.040552 0.297771 0.045193 0.320150 0.049348 0.342614 0.053015 0.365153 0.056193 0.387755 0.058880 0.410410 0.061075 0.433108 0.062777 0.455837 0.063984 0.478588 0.064698 0.501348 0.064916 0.524108 0.064639 0.546856 0.063867 0.569582 0.062601 0.592276 0.060841 0.614925 0.058588 0.637521 0.055842 0.660051 0.052606 0.697823 0.046761 0.735595 0.040916 0.773367 0.035071 0.811139 0.029226 0.848912 0.023381 0.886684 0.017535 0.924456 0.011690 0.962228 0.005845 1.000000 0.000000 |
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Polars for Cambered plate C=12% T=5% R=1.1 (cp-120-050-gn)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| cp-120-050-gn | 50,000 | 9 | 25.2 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-120-050-gn | 50,000 | 5 | 20.4 at α=12.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-120-050-gn | 50,000 | 1 | 19.1 at α=6° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-120-050-gn | 100,000 | 9 | 32.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-120-050-gn | 100,000 | 5 | 29.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-120-050-gn | 100,000 | 1 | 27 at α=3.75° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-120-050-gn | 200,000 | 9 | 42.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-120-050-gn | 200,000 | 5 | 39.1 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-120-050-gn | 200,000 | 1 | 34.6 at α=6.5° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-120-050-gn | 500,000 | 9 | 42.8 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-120-050-gn | 500,000 | 5 | 42.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-120-050-gn | 500,000 | 1 | 46 at α=5.75° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-120-050-gn | 1,000,000 | 9 | 43.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-120-050-gn | 1,000,000 | 5 | 53.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-120-050-gn | 1,000,000 | 1 | 56.4 at α=4.75° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
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