PW51 (pw51-pw)
PW51 - Peter Wick. Airfoil for plank model gliders
| Details | Dat file | Parser | |
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(pw51-pw) PW51 Peter Wick. Airfoil for plank model gliders Max thickness 8.9% at 27.5% chord. Max camber 1.4% at 27.5% chord Source RC Groups Source dat file The dat file is in Selig format |
PW51 1.00000 0.00047 0.99655 0.00054 0.98638 0.00097 0.96991 0.00199 0.94761 0.0037 0.91998 0.0061 0.88752 0.00915 0.85073 0.0128 0.81018 0.01695 0.76640 0.02148 0.71996 0.02629 0.67144 0.03128 0.62141 0.0363 0.57048 0.04119 0.51920 0.04579 0.46812 0.04992 0.41776 0.05342 0.36860 0.05612 0.32105 0.05789 0.27556 0.05865 0.23256 0.05831 0.19244 0.05682 0.15550 0.05411 0.12200 0.05023 0.09220 0.04523 0.06630 0.03926 0.04448 0.03245 0.02687 0.02502 0.01357 0.01731 0.00472 0.00967 0.00042 0.00263 0.00003 0.00096 0.00000 0.00000 0.00006 -0.00066 0.00025 -0.00154 0.00056 -0.00235 0.00100 -0.00312 0.00156 -0.00387 0.00224 -0.00461 0.00305 -0.00535 0.00398 -0.00609 0.00504 -0.00683 0.00622 -0.00758 0.00752 -0.00833 0.00895 -0.00908 0.01049 -0.00982 0.01216 -0.01054 0.01395 -0.01126 0.01587 -0.01197 0.01790 -0.01267 0.02005 -0.01336 0.02233 -0.01404 0.02472 -0.01470 0.02723 -0.01536 0.02985 -0.01600 0.03260 -0.01663 0.03546 -0.01725 0.03844 -0.01785 0.04153 -0.01844 0.04474 -0.01902 0.04806 -0.01958 0.05149 -0.02012 0.05504 -0.02065 0.05869 -0.02117 0.06246 -0.02167 0.06633 -0.02215 0.07031 -0.02262 0.07440 -0.02308 0.07860 -0.02352 0.08290 -0.02395 0.08731 -0.02436 0.09181 -0.02475 0.09642 -0.02514 0.10113 -0.02550 0.10594 -0.02585 0.11085 -0.02619 0.11585 -0.02651 0.12095 -0.02681 0.12615 -0.02711 0.13144 -0.02738 0.13682 -0.02765 0.14229 -0.02790 0.14785 -0.02814 0.15349 -0.02836 0.15922 -0.02857 0.16504 -0.02877 0.17095 -0.02896 0.17693 -0.02913 0.18299 -0.02929 0.18914 -0.02944 0.19536 -0.02958 0.20166 -0.02970 0.20803 -0.02981 0.21447 -0.02991 0.22099 -0.03000 0.22757 -0.03008 0.23422 -0.03015 0.24094 -0.03020 0.24772 -0.03025 0.25457 -0.03029 0.26148 -0.03031 0.26844 -0.03033 0.27547 -0.03033 0.28255 -0.03032 0.28969 -0.03031 0.29687 -0.03028 0.30411 -0.03024 0.31140 -0.03020 0.31873 -0.03015 0.32611 -0.03008 0.33353 -0.03001 0.34099 -0.02993 0.34850 -0.02985 0.35604 -0.02975 0.36361 -0.02964 0.37123 -0.02953 0.37887 -0.02940 0.38654 -0.02927 0.39424 -0.02913 0.40197 -0.02898 0.40972 -0.02882 0.41750 -0.02866 0.42529 -0.02849 0.43311 -0.02831 0.44094 -0.02813 0.44878 -0.02793 0.45664 -0.02773 0.46451 -0.02752 0.47239 -0.02731 0.48027 -0.02708 0.48816 -0.02685 0.49605 -0.02662 0.50395 -0.02637 0.51184 -0.02612 0.51973 -0.02587 0.52761 -0.02560 0.53549 -0.02534 0.54336 -0.02506 0.55122 -0.02478 0.55906 -0.02449 0.56689 -0.02420 0.57471 -0.02391 0.58250 -0.02361 0.59028 -0.02330 0.59803 -0.02299 0.60576 -0.02267 0.61346 -0.02235 0.62113 -0.02203 0.62877 -0.02170 0.63639 -0.02137 0.64396 -0.02104 0.65150 -0.02070 0.65901 -0.02035 0.66647 -0.02001 0.67389 -0.01966 0.68127 -0.01931 0.68860 -0.01895 0.69589 -0.01860 0.70313 -0.01824 0.71032 -0.01788 0.71745 -0.01752 0.72453 -0.01715 0.73156 -0.01679 0.73852 -0.01643 0.74543 -0.01606 0.75228 -0.01569 0.75906 -0.01533 0.76578 -0.01496 0.77243 -0.01459 0.77901 -0.01423 0.78553 -0.01386 0.79197 -0.01349 0.79835 -0.01313 0.80464 -0.01276 0.81086 -0.01240 0.81701 -0.01204 0.82307 -0.01168 0.82905 -0.01132 0.83496 -0.01097 0.84077 -0.01061 0.84651 -0.01026 0.85215 -0.00992 0.85771 -0.00957 0.86318 -0.00923 0.86856 -0.00890 0.87385 -0.00856 0.87905 -0.00824 0.88415 -0.00791 0.88915 -0.00760 0.89406 -0.00728 0.89887 -0.00697 0.90358 -0.00667 0.90819 -0.00638 0.91270 -0.00608 0.91710 -0.00580 0.92140 -0.00552 0.92560 -0.00525 0.92969 -0.00498 0.93367 -0.00472 0.93754 -0.00447 0.94131 -0.00422 0.94496 -0.00398 0.94851 -0.00375 0.95194 -0.00353 0.95526 -0.00331 0.95847 -0.00310 0.96156 -0.00290 0.96454 -0.00271 0.96740 -0.00252 0.97015 -0.00234 0.97277 -0.00217 0.97528 -0.00201 0.97768 -0.00186 0.97995 -0.00171 0.98210 -0.00157 0.98413 -0.00144 0.98605 -0.00132 0.98784 -0.00121 0.98951 -0.00110 0.99105 -0.00100 0.99248 -0.00091 0.99378 -0.00083 0.99496 -0.00076 0.99602 -0.00070 0.99695 -0.00064 0.99776 -0.00060 0.99844 -0.00056 0.99900 -0.00053 0.99944 -0.00050 0.99975 -0.00048 0.99994 -0.00047 1.00000 -0.00047 |
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Similar airfoils
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Polars for PW51 (pw51-pw)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| pw51-pw | 50,000 | 9 | 26.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw51-pw | 100,000 | 9 | 41.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw51-pw | 200,000 | 9 | 56.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw51-pw | 500,000 | 9 | 76.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw51-pw | 1,000,000 | 9 | 90.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw51-pw | 2,000,000 | 9 | 104.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw51-pw | 5,000,000 | 9 | 119.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
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