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PW1211 (pw1211-pw)

PW1211 - Peter Wick. Airfoil for plank model gliders


Airfoil pw1211-pw
Details Dat file Parser  
(pw1211-pw) PW1211
Peter Wick. Airfoil for plank model gliders
Max thickness 7% at 24% chord.
Max camber 1.7% at 28.2% chord
Source RC Groups
Source dat file
The dat file is in Selig format
PW1211
1.00000   0.00024
0.99644   0.00008
0.99011  -0.00010
0.98279  -0.00021
0.97494  -0.00024
0.96687  -0.00017
0.95870   0.00002
0.95043   0.00030
0.94209   0.00066
0.93371   0.00109
0.92529   0.00158
0.91682   0.00211
0.90832   0.00268
0.89982   0.00329
0.89129   0.00392
0.88275   0.00459
0.87419   0.00527
0.86564   0.00597
0.85710   0.00670
0.84856   0.00744
0.84000   0.00821
0.83142   0.00900
0.82284   0.00979
0.81425   0.01060
0.80567   0.01142
0.79709   0.01225
0.78848   0.01309
0.77987   0.01393
0.77125   0.01478
0.76265   0.01563
0.75406   0.01648
0.74547   0.01734
0.73686   0.01822
0.72825   0.01909
0.71963   0.01996
0.71101   0.02083
0.70240   0.02170
0.69379   0.02258
0.68517   0.02345
0.67657   0.02432
0.66796   0.02519
0.65936   0.02605
0.65075   0.02690
0.64216   0.02775
0.63357   0.02859
0.62499   0.02941
0.61640   0.03023
0.60780   0.03104
0.59921   0.03184
0.59061   0.03263
0.58202   0.03342
0.57341   0.03419
0.56481   0.03496
0.55622   0.03572
0.54764   0.03647
0.53907   0.03720
0.53048   0.03792
0.52189   0.03863
0.51329   0.03933
0.50469   0.04002
0.49610   0.04069
0.48752   0.04136
0.47893   0.04201
0.47035   0.04264
0.46178   0.04326
0.45321   0.04386
0.44466   0.04444
0.43609   0.04500
0.42752   0.04554
0.41895   0.04606
0.41038   0.04656
0.40181   0.04705
0.39324   0.04751
0.38467   0.04795
0.37610   0.04838
0.36755   0.04878
0.35900   0.04915
0.35046   0.04950
0.34190   0.04982
0.33335   0.05011
0.32480   0.05038
0.31627   0.05062
0.30773   0.05083
0.29918   0.05101
0.29064   0.05117
0.28211   0.05130
0.27361   0.05139
0.26512   0.05144
0.25661   0.05145
0.24810   0.05142
0.23961   0.05136
0.23114   0.05126
0.22267   0.05110
0.21419   0.05091
0.20572   0.05067
0.19730   0.05039
0.18892   0.05005
0.18052   0.04964
0.17213   0.04917
0.16377   0.04865
0.15547   0.04806
0.14717   0.04739
0.13887   0.04665
0.13064   0.04583
0.12247   0.04492
0.11430   0.04392
0.10617   0.04282
0.09813   0.04163
0.09017   0.04032
0.08227   0.03889
0.07449   0.03735
0.06684   0.03566
0.05930   0.03381
0.05196   0.03182
0.04483   0.02966
0.03798   0.02735
0.03156   0.02491
0.02563   0.02235
0.02038   0.01981
0.01594   0.01738
0.01233   0.01513
0.00947   0.01306
0.00720   0.01118
0.00540   0.00951
0.00397   0.00799
0.00287   0.00658
0.00203   0.00526
0.00136   0.00404
0.00082   0.00292
0.00040   0.00189
0.00011   0.00092
0.00000   0.00000
0.00009  -0.00092
0.00039  -0.00184
0.00089  -0.00277
0.00158  -0.00368
0.00247  -0.00456
0.00360  -0.00535
0.00500  -0.00607
0.00671  -0.00674
0.00879  -0.00744
0.01136  -0.00819
0.01461  -0.00900
0.01879  -0.00988
0.02405  -0.01088
0.03032  -0.01189
0.03746  -0.01285
0.04507  -0.01373
0.05300  -0.01448
0.06117  -0.01517
0.06935  -0.01578
0.07764  -0.01627
0.08605  -0.01672
0.09443  -0.01713
0.10284  -0.01745
0.11133  -0.01773
0.11984  -0.01799
0.12831  -0.01820
0.13681  -0.01836
0.14538  -0.01850
0.15396  -0.01862
0.16250  -0.01871
0.17105  -0.01877
0.17965  -0.01881
0.18825  -0.01884
0.19684  -0.01885
0.20542  -0.01884
0.21403  -0.01880
0.22267  -0.01876
0.23130  -0.01872
0.23991  -0.01867
0.24852  -0.01860
0.25716  -0.01852
0.26580  -0.01843
0.27445  -0.01835
0.28307  -0.01825
0.29170  -0.01815
0.30034  -0.01803
0.30899  -0.01791
0.31764  -0.01780
0.32629  -0.01768
0.33493  -0.01755
0.34358  -0.01742
0.35223  -0.01729
0.36089  -0.01715
0.36954  -0.01701
0.37819  -0.01687
0.38684  -0.01672
0.39549  -0.01657
0.40415  -0.01642
0.41281  -0.01627
0.42146  -0.01613
0.43011  -0.01597
0.43876  -0.01581
0.44741  -0.01566
0.45606  -0.01550
0.46471  -0.01535
0.47336  -0.01519
0.48200  -0.01503
0.49065  -0.01487
0.49930  -0.01470
0.50795  -0.01454
0.51660  -0.01437
0.52525  -0.01421
0.53389  -0.01404
0.54254  -0.01387
0.55119  -0.01369
0.55984  -0.01352
0.56849  -0.01335
0.57714  -0.01318
0.58579  -0.01300
0.59444  -0.01282
0.60309  -0.01264
0.61174  -0.01247
0.62040  -0.01229
0.62904  -0.01211
0.63769  -0.01193
0.64634  -0.01174
0.65499  -0.01155
0.66366  -0.01136
0.67231  -0.01116
0.68097  -0.01097
0.68962  -0.01077
0.69828  -0.01057
0.70694  -0.01037
0.71559  -0.01017
0.72425  -0.00996
0.73290  -0.00974
0.74156  -0.00953
0.75022  -0.00932
0.75887  -0.00910
0.76751  -0.00888
0.77616  -0.00865
0.78481  -0.00842
0.79346  -0.00818
0.80211  -0.00794
0.81076  -0.00770
0.81941  -0.00745
0.82806  -0.00720
0.83671  -0.00694
0.84535  -0.00669
0.85399  -0.00642
0.86264  -0.00615
0.87128  -0.00587
0.87993  -0.00560
0.88857  -0.00531
0.89720  -0.00503
0.90582  -0.00473
0.91444  -0.00442
0.92305  -0.00410
0.93165  -0.00377
0.94025  -0.00342
0.94882  -0.00307
0.95732  -0.00269
0.96576  -0.00227
0.97411  -0.00182
0.98225  -0.00132
0.98987  -0.00084
0.99641  -0.00045
1.00000  -0.00024
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Selig format dat file

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Polars for PW1211 (pw1211-pw)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   pw1211-pw50,000927.5 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   pw1211-pw100,000941.1 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   pw1211-pw200,000955.4 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   pw1211-pw500,000974.2 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   pw1211-pw1,000,000987.3 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   pw1211-pw2,000,000999.5 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   pw1211-pw5,000,0009114.2 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
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