PW1211 (pw1211-pw)
PW1211 - Peter Wick. Airfoil for plank model gliders
| Details | Dat file | Parser | |
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(pw1211-pw) PW1211 Peter Wick. Airfoil for plank model gliders Max thickness 7% at 24% chord. Max camber 1.7% at 28.2% chord Source RC Groups Source dat file The dat file is in Selig format |
PW1211 1.00000 0.00024 0.99644 0.00008 0.99011 -0.00010 0.98279 -0.00021 0.97494 -0.00024 0.96687 -0.00017 0.95870 0.00002 0.95043 0.00030 0.94209 0.00066 0.93371 0.00109 0.92529 0.00158 0.91682 0.00211 0.90832 0.00268 0.89982 0.00329 0.89129 0.00392 0.88275 0.00459 0.87419 0.00527 0.86564 0.00597 0.85710 0.00670 0.84856 0.00744 0.84000 0.00821 0.83142 0.00900 0.82284 0.00979 0.81425 0.01060 0.80567 0.01142 0.79709 0.01225 0.78848 0.01309 0.77987 0.01393 0.77125 0.01478 0.76265 0.01563 0.75406 0.01648 0.74547 0.01734 0.73686 0.01822 0.72825 0.01909 0.71963 0.01996 0.71101 0.02083 0.70240 0.02170 0.69379 0.02258 0.68517 0.02345 0.67657 0.02432 0.66796 0.02519 0.65936 0.02605 0.65075 0.02690 0.64216 0.02775 0.63357 0.02859 0.62499 0.02941 0.61640 0.03023 0.60780 0.03104 0.59921 0.03184 0.59061 0.03263 0.58202 0.03342 0.57341 0.03419 0.56481 0.03496 0.55622 0.03572 0.54764 0.03647 0.53907 0.03720 0.53048 0.03792 0.52189 0.03863 0.51329 0.03933 0.50469 0.04002 0.49610 0.04069 0.48752 0.04136 0.47893 0.04201 0.47035 0.04264 0.46178 0.04326 0.45321 0.04386 0.44466 0.04444 0.43609 0.04500 0.42752 0.04554 0.41895 0.04606 0.41038 0.04656 0.40181 0.04705 0.39324 0.04751 0.38467 0.04795 0.37610 0.04838 0.36755 0.04878 0.35900 0.04915 0.35046 0.04950 0.34190 0.04982 0.33335 0.05011 0.32480 0.05038 0.31627 0.05062 0.30773 0.05083 0.29918 0.05101 0.29064 0.05117 0.28211 0.05130 0.27361 0.05139 0.26512 0.05144 0.25661 0.05145 0.24810 0.05142 0.23961 0.05136 0.23114 0.05126 0.22267 0.05110 0.21419 0.05091 0.20572 0.05067 0.19730 0.05039 0.18892 0.05005 0.18052 0.04964 0.17213 0.04917 0.16377 0.04865 0.15547 0.04806 0.14717 0.04739 0.13887 0.04665 0.13064 0.04583 0.12247 0.04492 0.11430 0.04392 0.10617 0.04282 0.09813 0.04163 0.09017 0.04032 0.08227 0.03889 0.07449 0.03735 0.06684 0.03566 0.05930 0.03381 0.05196 0.03182 0.04483 0.02966 0.03798 0.02735 0.03156 0.02491 0.02563 0.02235 0.02038 0.01981 0.01594 0.01738 0.01233 0.01513 0.00947 0.01306 0.00720 0.01118 0.00540 0.00951 0.00397 0.00799 0.00287 0.00658 0.00203 0.00526 0.00136 0.00404 0.00082 0.00292 0.00040 0.00189 0.00011 0.00092 0.00000 0.00000 0.00009 -0.00092 0.00039 -0.00184 0.00089 -0.00277 0.00158 -0.00368 0.00247 -0.00456 0.00360 -0.00535 0.00500 -0.00607 0.00671 -0.00674 0.00879 -0.00744 0.01136 -0.00819 0.01461 -0.00900 0.01879 -0.00988 0.02405 -0.01088 0.03032 -0.01189 0.03746 -0.01285 0.04507 -0.01373 0.05300 -0.01448 0.06117 -0.01517 0.06935 -0.01578 0.07764 -0.01627 0.08605 -0.01672 0.09443 -0.01713 0.10284 -0.01745 0.11133 -0.01773 0.11984 -0.01799 0.12831 -0.01820 0.13681 -0.01836 0.14538 -0.01850 0.15396 -0.01862 0.16250 -0.01871 0.17105 -0.01877 0.17965 -0.01881 0.18825 -0.01884 0.19684 -0.01885 0.20542 -0.01884 0.21403 -0.01880 0.22267 -0.01876 0.23130 -0.01872 0.23991 -0.01867 0.24852 -0.01860 0.25716 -0.01852 0.26580 -0.01843 0.27445 -0.01835 0.28307 -0.01825 0.29170 -0.01815 0.30034 -0.01803 0.30899 -0.01791 0.31764 -0.01780 0.32629 -0.01768 0.33493 -0.01755 0.34358 -0.01742 0.35223 -0.01729 0.36089 -0.01715 0.36954 -0.01701 0.37819 -0.01687 0.38684 -0.01672 0.39549 -0.01657 0.40415 -0.01642 0.41281 -0.01627 0.42146 -0.01613 0.43011 -0.01597 0.43876 -0.01581 0.44741 -0.01566 0.45606 -0.01550 0.46471 -0.01535 0.47336 -0.01519 0.48200 -0.01503 0.49065 -0.01487 0.49930 -0.01470 0.50795 -0.01454 0.51660 -0.01437 0.52525 -0.01421 0.53389 -0.01404 0.54254 -0.01387 0.55119 -0.01369 0.55984 -0.01352 0.56849 -0.01335 0.57714 -0.01318 0.58579 -0.01300 0.59444 -0.01282 0.60309 -0.01264 0.61174 -0.01247 0.62040 -0.01229 0.62904 -0.01211 0.63769 -0.01193 0.64634 -0.01174 0.65499 -0.01155 0.66366 -0.01136 0.67231 -0.01116 0.68097 -0.01097 0.68962 -0.01077 0.69828 -0.01057 0.70694 -0.01037 0.71559 -0.01017 0.72425 -0.00996 0.73290 -0.00974 0.74156 -0.00953 0.75022 -0.00932 0.75887 -0.00910 0.76751 -0.00888 0.77616 -0.00865 0.78481 -0.00842 0.79346 -0.00818 0.80211 -0.00794 0.81076 -0.00770 0.81941 -0.00745 0.82806 -0.00720 0.83671 -0.00694 0.84535 -0.00669 0.85399 -0.00642 0.86264 -0.00615 0.87128 -0.00587 0.87993 -0.00560 0.88857 -0.00531 0.89720 -0.00503 0.90582 -0.00473 0.91444 -0.00442 0.92305 -0.00410 0.93165 -0.00377 0.94025 -0.00342 0.94882 -0.00307 0.95732 -0.00269 0.96576 -0.00227 0.97411 -0.00182 0.98225 -0.00132 0.98987 -0.00084 0.99641 -0.00045 1.00000 -0.00024 |
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Polars for PW1211 (pw1211-pw)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| pw1211-pw | 50,000 | 9 | 27.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw1211-pw | 100,000 | 9 | 41.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw1211-pw | 200,000 | 9 | 55.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw1211-pw | 500,000 | 9 | 74.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw1211-pw | 1,000,000 | 9 | 87.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw1211-pw | 2,000,000 | 9 | 99.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw1211-pw | 5,000,000 | 9 | 114.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
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