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PW51 (pw51-pw)

PW51 - Peter Wick. Airfoil for plank model gliders


Airfoil pw51-pw
Details Dat file Parser  
(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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Polars for PW51 (pw51-pw)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   pw51-pw50,000926.2 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   pw51-pw100,000941.2 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   pw51-pw200,000956.6 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   pw51-pw500,000976.6 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   pw51-pw1,000,000990.8 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   pw51-pw2,000,0009104.2 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   pw51-pw5,000,0009119.9 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
Reynolds number calculator
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