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AG37 (ag37-il)

AG37 - Drela AG37 airfoil


Airfoil ag37-il
Details Dat file Parser  
(ag37-il) AG37
Drela AG37 airfoil
Max thickness 7.7% at 26.5% chord.
Max camber 2.1% at 35.5% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AG37
     1.000000    0.003508
     0.993634    0.004540
     0.983839    0.006128
     0.972384    0.007984
     0.960126    0.009970
     0.947509    0.012015
     0.934838    0.014069
     0.922272    0.016105
     0.909672    0.018147
     0.897163    0.020174
     0.884502    0.022136
     0.872236    0.023744
     0.859132    0.025363
     0.845998    0.026986
     0.832762    0.028622
     0.819330    0.030281
     0.805796    0.031954
     0.792287    0.033623
     0.778764    0.035294
     0.765277    0.036961
     0.751736    0.038634
     0.738244    0.040301
     0.724795    0.041963
     0.711419    0.043616
     0.698229    0.045246
     0.685362    0.046836
     0.672702    0.048400
     0.659989    0.049874
     0.648296    0.051133
     0.636014    0.052350
     0.622979    0.053568
     0.610109    0.054732
     0.597124    0.055906
     0.583924    0.057099
     0.570608    0.058304
     0.557288    0.059508
     0.543987    0.060711
     0.530692    0.061913
     0.517439    0.063111
     0.504203    0.064308
     0.491039    0.065499
     0.478020    0.066675
     0.465306    0.067826
     0.453088    0.068931
     0.440823    0.069934
     0.428638    0.070879
     0.416395    0.071774
     0.404233    0.072598
     0.392113    0.073355
     0.379952    0.074055
     0.367557    0.074706
     0.354881    0.075304
     0.342042    0.075842
     0.329120    0.076312
     0.316188    0.076710
     0.303310    0.077030
     0.290456    0.077269
     0.277633    0.077424
     0.264786    0.077488
     0.251944    0.077457
     0.239030    0.077318
     0.226008    0.077063
     0.212844    0.076678
     0.199532    0.076147
     0.186403    0.075471
     0.173367    0.074641
     0.160427    0.073645
     0.147589    0.072472
     0.134778    0.071102
     0.122032    0.069519
     0.109366    0.067704
     0.096850    0.065646
     0.085381    0.063498
     0.074326    0.061155
     0.063754    0.058627
     0.053804    0.055941
     0.044531    0.053109
     0.036013    0.050157
     0.028389    0.047142
     0.021830    0.044161
     0.016458    0.041336
     0.012225    0.038754
     0.008994    0.036451
     0.006578    0.034442
     0.004804    0.032719
     0.003498    0.031245
     0.002484    0.029908
     0.001659    0.028617
     0.000975    0.027306
     0.000462    0.026004
     0.000097    0.024530
     0.000005    0.023090
     0.000139    0.021997
     0.000479    0.020847
     0.001101    0.019658
     0.002090    0.018460
     0.003442    0.017314
     0.005164    0.016221
     0.007326    0.015167
     0.009992    0.014136
     0.013260    0.013114
     0.017315    0.012059
     0.022425    0.010949
     0.028894    0.009771
     0.036949    0.008569
     0.046522    0.007388
     0.057281    0.006303
     0.068822    0.005337
     0.080832    0.004491
     0.093131    0.003758
     0.105621    0.003130
     0.118238    0.002594
     0.130947    0.002135
     0.143732    0.001745
     0.156572    0.001410
     0.169460    0.001125
     0.182388    0.000884
     0.195358    0.000679
     0.208361    0.000508
     0.221395    0.000367
     0.234451    0.000255
     0.247531    0.000166
     0.260630    0.000098
     0.273751    0.000052
     0.286893    0.000021
     0.300050    0.000002
     0.313224   -0.000009
     0.326425   -0.000016
     0.339638   -0.000016
     0.352851   -0.000015
     0.366065   -0.000015
     0.379284   -0.000015
     0.392508   -0.000016
     0.405734   -0.000015
     0.418957   -0.000013
     0.432174   -0.000016
     0.445391   -0.000014
     0.458618   -0.000013
     0.471843   -0.000014
     0.485062   -0.000013
     0.498279   -0.000013
     0.511500   -0.000014
     0.524726   -0.000012
     0.537952   -0.000014
     0.551171   -0.000014
     0.564383   -0.000012
     0.577598   -0.000013
     0.590818   -0.000013
     0.604037   -0.000011
     0.617254   -0.000011
     0.630479   -0.000011
     0.643705   -0.000010
     0.656928   -0.000010
     0.670149   -0.000008
     0.683367   -0.000010
     0.696587   -0.000008
     0.709814   -0.000009
     0.723037   -0.000008
     0.736256   -0.000010
     0.749473   -0.000008
     0.762697   -0.000008
     0.775924   -0.000006
     0.789146   -0.000006
     0.802363   -0.000005
     0.815577   -0.000005
     0.828791   -0.000005
     0.842011   -0.000004
     0.855227   -0.000006
     0.868438   -0.000006
     0.881646   -0.000005
     0.894863   -0.000005
     0.908082   -0.000004
     0.921304   -0.000003
     0.934512   -0.000002
     0.947676   -0.000001
     0.960697   -0.000002
     0.973318   -0.000002
     0.984934   -0.000001
     0.994759   -0.000001
     1.000000    0.000000
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Lednicer format dat file
Selig format dat file

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Polars for AG37 (ag37-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ag37-il50,000932.9 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag37-il50,000536.4 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag37-il100,000949.3 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ag37-il100,000549.8 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ag37-il200,000965.3 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag37-il200,000562.5 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   ag37-il500,000985.2 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ag37-il500,000578.6 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag37-il1,000,000998.9 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag37-il1,000,000589.7 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
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