Cambered plate C=16% T=5% R=0.86 (cp-160-050-gn)
Cambered plate C=16% T=5% R=0.86 - HAWT pipe blade with coordinates based on top surface. Camber=16% Wall thickness=5% Radius=0.861
| Details | Dat file | Parser | |
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(cp-160-050-gn) Cambered plate C=16% T=5% R=0.86 HAWT pipe blade with coordinates based on top surface. Camber=16% Wall thickness=5% Radius=0.861 Max thickness 5.2% at 3.4% chord. Max camber 14.3% at 49.2% chord Source Generated Source dat file The dat file is in Selig format |
Cambered plate C=16% T=5% R=0.86 1.000000 0.000000 0.980275 0.013654 0.960176 0.026754 0.939721 0.039288 0.918925 0.051248 0.897803 0.062624 0.876373 0.073408 0.854651 0.083590 0.832654 0.093164 0.810399 0.102121 0.787902 0.110454 0.765183 0.118158 0.742258 0.125226 0.719144 0.131653 0.695861 0.137434 0.672425 0.142563 0.648856 0.147038 0.625172 0.150855 0.601390 0.154011 0.577530 0.156503 0.553609 0.158330 0.529647 0.159490 0.505662 0.159981 0.481672 0.159805 0.457697 0.158960 0.433754 0.157448 0.409863 0.155270 0.386042 0.152427 0.362309 0.148922 0.338683 0.144757 0.315183 0.139936 0.291825 0.134462 0.268629 0.128340 0.245613 0.121574 0.222794 0.114169 0.200190 0.106132 0.177819 0.097468 0.155698 0.088185 0.133844 0.078289 0.112274 0.067788 0.091005 0.056691 0.070053 0.045005 0.049435 0.032741 0.029166 0.019907 0.009263 0.006513 0.007422 0.005083 0.005746 0.003462 0.004255 0.001670 0.002967 -0.000274 0.001897 -0.002345 0.001056 -0.004519 0.000456 -0.006772 0.000103 -0.009077 0.000001 -0.011406 0.000152 -0.013732 0.000553 -0.016029 0.001200 -0.018269 0.002085 -0.020425 0.003199 -0.022473 0.004527 -0.024389 0.006055 -0.026150 0.007764 -0.027736 0.009635 -0.029127 0.011645 -0.030308 0.013771 -0.031265 0.015988 -0.031986 0.018270 -0.032464 0.020590 -0.032692 0.022921 -0.032667 0.025236 -0.032391 0.027508 -0.031866 0.029709 -0.031099 0.031815 -0.030098 0.033800 -0.028875 0.053066 -0.015918 0.072692 -0.003512 0.092661 0.008332 0.112959 0.019604 0.133569 0.030296 0.154474 0.040398 0.175657 0.049904 0.197101 0.058805 0.218789 0.067093 0.240704 0.074763 0.262827 0.081808 0.285141 0.088222 0.307629 0.094001 0.330271 0.099139 0.353050 0.103633 0.375947 0.107478 0.398944 0.110673 0.422023 0.113213 0.445164 0.115098 0.468349 0.116325 0.491560 0.116894 0.514778 0.116804 0.537984 0.116055 0.561159 0.114648 0.584285 0.112585 0.607344 0.109865 0.630315 0.106493 0.653182 0.102470 0.675925 0.097800 0.698527 0.092487 0.720969 0.086534 0.743233 0.079947 0.771763 0.071064 0.800292 0.062181 0.828822 0.053298 0.857352 0.044415 0.885881 0.035532 0.914411 0.026649 0.942941 0.017766 0.971470 0.008883 1.000000 0.000000 |
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Polars for Cambered plate C=16% T=5% R=0.86 (cp-160-050-gn)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| cp-160-050-gn | 50,000 | 9 | 16.5 at α=15.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-160-050-gn | 50,000 | 5 | 15.1 at α=16.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-160-050-gn | 50,000 | 1 | 13.1 at α=9.25° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-160-050-gn | 100,000 | 9 | 21 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-160-050-gn | 100,000 | 5 | 20.1 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-160-050-gn | 100,000 | 1 | 21 at α=6.75° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-160-050-gn | 200,000 | 9 | 39.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-160-050-gn | 200,000 | 5 | 37.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-160-050-gn | 200,000 | 1 | 34.2 at α=4.25° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-160-050-gn | 500,000 | 9 | 58.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-160-050-gn | 500,000 | 5 | 49.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-160-050-gn | 500,000 | 1 | 33.3 at α=2.25° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-160-050-gn | 1,000,000 | 9 | 56 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-160-050-gn | 1,000,000 | 5 | 48.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-160-050-gn | 1,000,000 | 1 | 33.7 at α=7° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
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