PW106 (pw106-pw)
PW106 - Peter Wick. Modified PW51 with higher camber and therefore a higher clmax
| Details | Dat file | Parser | |
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(pw106-pw) PW106 Peter Wick. Modified PW51 with higher camber and therefore a higher clmax Max thickness 8.9% at 27.5% chord. Max camber 2.1% at 27.5% chord Source RC Groups Source dat file The dat file is in Selig format |
PW106 1.00000 0.00047 0.99655 0.00051 0.98638 0.00088 0.96991 0.00188 0.94761 0.00365 0.91998 0.00619 0.88752 0.00947 0.85073 0.01345 0.81018 0.01802 0.76640 0.02306 0.71996 0.02844 0.67144 0.03408 0.62141 0.03980 0.57048 0.04539 0.51920 0.05068 0.46812 0.05546 0.41776 0.05951 0.36860 0.06265 0.32105 0.06471 0.27556 0.06559 0.23256 0.06520 0.19244 0.06347 0.15550 0.06033 0.12200 0.05584 0.09220 0.05008 0.06630 0.04325 0.04448 0.03550 0.02687 0.02711 0.01357 0.01848 0.00472 0.01004 0.00042 0.00175 0.00003 0.00018 0.00000 0.00000 0.00006 -0.00021 0.00025 -0.00082 0.00056 -0.00173 0.00100 -0.00281 0.00156 -0.00384 0.00224 -0.00461 0.00305 -0.00517 0.00398 -0.00577 0.00504 -0.00644 0.00622 -0.00709 0.00752 -0.00770 0.00895 -0.00829 0.01049 -0.00888 0.01216 -0.00948 0.01395 -0.01006 0.01587 -0.01062 0.01790 -0.01118 0.02005 -0.01171 0.02233 -0.01224 0.02472 -0.01274 0.02723 -0.01325 0.02985 -0.01373 0.03260 -0.01420 0.03546 -0.01466 0.03844 -0.01510 0.04153 -0.01554 0.04474 -0.01596 0.04806 -0.01636 0.05149 -0.01674 0.05504 -0.01712 0.05869 -0.01748 0.06246 -0.01783 0.06633 -0.01816 0.07031 -0.01848 0.07440 -0.01879 0.07860 -0.01909 0.08290 -0.01938 0.08731 -0.01966 0.09181 -0.01991 0.09642 -0.02016 0.10113 -0.02039 0.10594 -0.02062 0.11085 -0.02084 0.11585 -0.02104 0.12095 -0.02122 0.12615 -0.02142 0.13144 -0.02157 0.13682 -0.02174 0.14229 -0.02189 0.14785 -0.02204 0.15349 -0.02217 0.15922 -0.02230 0.16504 -0.02242 0.17095 -0.02253 0.18299 -0.02273 0.19536 -0.02291 0.20803 -0.02304 0.22099 -0.02316 0.23422 -0.02326 0.24772 -0.02332 0.26148 -0.02336 0.27547 -0.02339 0.28969 -0.02339 0.30411 -0.02336 0.31873 -0.02332 0.33353 -0.02325 0.34850 -0.02319 0.36361 -0.02307 0.37887 -0.02295 0.39424 -0.02281 0.40972 -0.02265 0.42529 -0.02248 0.44094 -0.02228 0.45664 -0.02207 0.47239 -0.02183 0.48816 -0.02156 0.50395 -0.02128 0.51973 -0.02099 0.53549 -0.02067 0.55122 -0.02031 0.56689 -0.01995 0.58250 -0.01957 0.59803 -0.01917 0.61346 -0.01874 0.62877 -0.01831 0.64396 -0.01786 0.65901 -0.01737 0.67389 -0.01689 0.68860 -0.01637 0.70313 -0.01586 0.71745 -0.01533 0.73156 -0.01478 0.74543 -0.01423 0.75906 -0.01367 0.77243 -0.01308 0.78553 -0.01251 0.79835 -0.01192 0.81086 -0.01133 0.82307 -0.01075 0.83496 -0.01016 0.84651 -0.00957 0.85771 -0.00899 0.86856 -0.00842 0.87905 -0.00785 0.88915 -0.00729 0.89887 -0.00674 0.90819 -0.00621 0.91710 -0.00569 0.92560 -0.00519 0.93367 -0.00471 0.94131 -0.00425 0.94851 -0.00380 0.95526 -0.00339 0.96156 -0.00300 0.96740 -0.00263 0.97277 -0.00228 0.97768 -0.00197 0.98210 -0.00167 0.98605 -0.00141 0.98951 -0.00118 0.99248 -0.00097 0.99496 -0.00081 0.99695 -0.00067 0.99844 -0.00058 0.99944 -0.00051 0.99975 -0.00049 0.99994 -0.00047 1.00000 -0.00047 |
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Similar airfoils
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Polars for PW106 (pw106-pw)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| pw106-pw | 50,000 | 9 | 25 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw106-pw | 100,000 | 9 | 46.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw106-pw | 200,000 | 9 | 61.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw106-pw | 500,000 | 9 | 74.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw106-pw | 1,000,000 | 9 | 84.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw106-pw | 2,000,000 | 9 | 94.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw106-pw | 5,000,000 | 9 | 116.9 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
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