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PW106 (pw106-pw)

PW106 - Peter Wick. Modified PW51 with higher camber and therefore a higher clmax


Airfoil pw106-pw
Details Dat file Parser  
(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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Polars for PW106 (pw106-pw)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   pw106-pw50,000925 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   pw106-pw100,000946.3 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   pw106-pw200,000961.3 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   pw106-pw500,000974.4 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   pw106-pw1,000,000984.9 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   pw106-pw2,000,000994.7 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   pw106-pw5,000,0009116.9 at α=10.5°Mach=0 Ncrit=9Xfoil predictionDetails
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