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PW75 (pw75-pw)

PW75 - Peter Wick. Modified PW51 with some more reflex


Airfoil pw75-pw
Details Dat file Parser  
(pw75-pw) PW75
Peter Wick. Modified PW51 with some more reflex
Max thickness 8.9% at 27.5% chord.
Max camber 1.5% at 23.4% chord
Source RC Groups
Source dat file
The dat file is in Selig format
PW75 
1.00000 0.00047
0.99655 0.00046
0.98638 0.00068
0.96991 0.00140
0.94761 0.00273
0.91998 0.00470
0.88752 0.00734
0.85073 0.01064
0.81018 0.01456
0.76640 0.01905
0.71996 0.02404
0.67144 0.02927
0.62141 0.03458
0.57048 0.03979
0.51920 0.04475
0.46812 0.04925
0.41776 0.05310
0.36860 0.05614
0.32105 0.05823
0.27556 0.05925
0.23256 0.05911
0.19244 0.05774
0.15550 0.05510
0.12200 0.05120
0.09220 0.04613
0.06630 0.04002
0.04448 0.03302
0.02687 0.02538
0.01357 0.01744
0.00472 0.00958
0.00042 0.00171
0.00003 0.00017
0.00000 0.00000
0.00006 -0.00021
0.00025 -0.00085
0.00056 -0.00179
0.00100 -0.00293
0.00156 -0.00402
0.00224 -0.00486
0.00305 -0.00549
0.00398 -0.00617
0.00504 -0.00692
0.00622 -0.00765
0.00752 -0.00835
0.00895 -0.00904
0.01049 -0.00974
0.01216 -0.01045
0.01395 -0.01112
0.01587 -0.01179
0.01790 -0.01245
0.02005 -0.0131
0.02233 -0.01374
0.02472 -0.01437
0.02723 -0.01499
0.02985 -0.01559
0.03260 -0.01619
0.03546 -0.01677
0.03844 -0.01734
0.04153 -0.0179
0.04474 -0.01844
0.04806 -0.01897
0.05149 -0.01948
0.05504 -0.01998
0.05869 -0.02046
0.06246 -0.02094
0.06633 -0.02139
0.07031 -0.02183
0.07440 -0.02227
0.07860 -0.02268
0.08290 -0.02309
0.08731 -0.02348
0.09181 -0.02386
0.09642 -0.02422
0.10113 -0.02457
0.10594 -0.0249
0.11085 -0.02523
0.11585 -0.02554
0.12095 -0.02584
0.12615 -0.02613
0.13144 -0.02639
0.13682 -0.02664
0.14229 -0.0269
0.14785 -0.02714
0.15349 -0.02737
0.15922 -0.02758
0.16504 -0.02779
0.17095 -0.02797
0.18299 -0.02834
0.19536 -0.02865
0.20803 -0.02892
0.22099 -0.02916
0.23422 -0.02937
0.24772 -0.02952
0.26148 -0.02964
0.27547 -0.02973
0.28969 -0.02978
0.30411 -0.02981
0.31873 -0.02979
0.33353 -0.02975
0.34850 -0.02968
0.36361 -0.02958
0.37887 -0.02945
0.39424 -0.02928
0.40972 -0.02909
0.42529 -0.02886
0.44094 -0.02861
0.45664 -0.02832
0.47239 -0.02802
0.48816 -0.02768
0.50395 -0.02731
0.51973 -0.02691
0.53549 -0.02650
0.55122 -0.02605
0.56689 -0.02558
0.58250 -0.02507
0.59803 -0.02456
0.61346 -0.02402
0.62877 -0.02347
0.64396 -0.02289
0.65901 -0.02230
0.67389 -0.02169
0.68860 -0.02105
0.70313 -0.02041
0.71745 -0.01976
0.73156 -0.01909
0.74543 -0.01842
0.75906 -0.01774
0.77243 -0.01703
0.78553 -0.01631
0.79835 -0.01555
0.81086 -0.01479
0.82307 -0.01403
0.83496 -0.01324
0.84651 -0.01247
0.85771 -0.01169
0.86856 -0.01091
0.87905 -0.01014
0.88915 -0.00939
0.89887 -0.00866
0.90819 -0.00793
0.91710 -0.00723
0.92560 -0.00656
0.93367 -0.00591
0.94131 -0.00530
0.94851 -0.00471
0.95526 -0.00415
0.96156 -0.00364
0.96740 -0.00316
0.97277 -0.00272
0.97768 -0.00232
0.98210 -0.00193
0.98605 -0.00161
0.98951 -0.00131
0.99248 -0.00107
0.99496 -0.00087
0.99695 -0.00071
0.99844 -0.00059
0.99944 -0.00051
0.99975 -0.00049
0.99994 -0.00048
1.00000 -0.00047
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Polars for PW75 (pw75-pw)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   pw75-pw50,000924.7 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   pw75-pw100,000940.3 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   pw75-pw200,000957 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   pw75-pw500,000973.4 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   pw75-pw1,000,000983.6 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   pw75-pw2,000,000991.4 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   pw75-pw5,000,0009107.2 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
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