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AG36 (ag36-il)

AG36 - Drela AG36 airfoil


Airfoil ag36-il
Details Dat file Parser  
(ag36-il) AG36
Drela AG36 airfoil
Max thickness 8.2% at 27.9% chord.
Max camber 2.3% at 37% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AG36
     1.000003    0.002671
     0.993991    0.003641
     0.983912    0.005266
     0.972030    0.007181
     0.959208    0.009247
     0.946050    0.011369
     0.932962    0.013479
     0.920159    0.015543
     0.907668    0.017556
     0.895474    0.019522
     0.883699    0.021360
     0.870771    0.023227
     0.857975    0.025012
     0.845188    0.026795
     0.832275    0.028596
     0.819232    0.030415
     0.806149    0.032241
     0.793050    0.034067
     0.779976    0.035891
     0.766906    0.037713
     0.753833    0.039537
     0.740771    0.041359
     0.727741    0.043176
     0.714758    0.044986
     0.701919    0.046776
     0.689366    0.048527
     0.677377    0.050200
     0.664649    0.051879
     0.652447    0.053315
     0.640918    0.054568
     0.628145    0.055906
     0.615243    0.057187
     0.602241    0.058477
     0.589040    0.059787
     0.575726    0.061108
     0.562405    0.062429
     0.549108    0.063749
     0.535834    0.065066
     0.522613    0.066377
     0.509419    0.067687
     0.496304    0.068989
     0.483304    0.070278
     0.470656    0.071534
     0.458359    0.072753
     0.445894    0.073861
     0.433427    0.074908
     0.420872    0.075896
     0.408284    0.076816
     0.395608    0.077673
     0.382819    0.078458
     0.369887    0.079171
     0.356838    0.079807
     0.343750    0.080355
     0.330663    0.080811
     0.317617    0.081175
     0.304632    0.081461
     0.291705    0.081662
     0.278830    0.081769
     0.265979    0.081778
     0.253138    0.081683
     0.240295    0.081478
     0.227476    0.081157
     0.214697    0.080715
     0.201993    0.080143
     0.189391    0.079442
     0.176920    0.078603
     0.164596    0.077626
     0.152422    0.076506
     0.140378    0.075232
     0.128500    0.073800
     0.116809    0.072199
     0.105313    0.070415
     0.094012    0.068433
     0.082843    0.066214
     0.071888    0.063743
     0.061341    0.061036
     0.051360    0.058108
     0.042120    0.055009
     0.033853    0.051846
     0.026739    0.048740
     0.020859    0.045811
     0.016127    0.043144
     0.012360    0.040758
     0.009362    0.038628
     0.006964    0.036710
     0.005060    0.034982
     0.003534    0.033393
     0.002309    0.031907
     0.001353    0.030504
     0.000648    0.029159
     0.000194    0.027848
     0.000000    0.026309
     0.000132    0.024817
     0.000499    0.023544
     0.001172    0.022228
     0.002191    0.020915
     0.003558    0.019663
     0.005312    0.018465
     0.007482    0.017306
     0.010121    0.016172
     0.013360    0.015034
     0.017387    0.013858
     0.022470    0.012613
     0.028917    0.011289
     0.036947    0.009926
     0.046502    0.008580
     0.057245    0.007335
     0.068770    0.006220
     0.080769    0.005246
     0.093063    0.004396
     0.105547    0.003663
     0.118159    0.003025
     0.130865    0.002475
     0.143646    0.002005
     0.156485    0.001599
     0.169372    0.001259
     0.182302    0.000971
     0.195271    0.000730
     0.208276    0.000533
     0.221309    0.000373
     0.234368    0.000243
     0.247445    0.000144
     0.260548    0.000069
     0.273668    0.000023
     0.286811    0.000010
     0.299969    0.000001
     0.313145   -0.000001
     0.326347   -0.000001
     0.339561   -0.000001
     0.352775   -0.000003
     0.365989   -0.000002
     0.379209   -0.000002
     0.392435   -0.000003
     0.405661   -0.000003
     0.418885   -0.000001
     0.432102   -0.000003
     0.445323   -0.000002
     0.458549   -0.000002
     0.471776   -0.000003
     0.484996   -0.000002
     0.498215   -0.000003
     0.511436   -0.000003
     0.524664   -0.000002
     0.537889   -0.000003
     0.551110   -0.000003
     0.564324   -0.000002
     0.577539   -0.000003
     0.590761   -0.000003
     0.603980   -0.000002
     0.617200   -0.000002
     0.630423   -0.000003
     0.643651   -0.000002
     0.656876   -0.000002
     0.670097   -0.000001
     0.683316   -0.000002
     0.696538   -0.000001
     0.709765   -0.000002
     0.722989   -0.000001
     0.736210   -0.000003
     0.749428   -0.000002
     0.762651   -0.000001
     0.775880   -0.000001
     0.789103   -0.000001
     0.802324   -0.000001
     0.815536   -0.000001
     0.828754   -0.000001
     0.841972   -0.000001
     0.855190   -0.000001
     0.868401   -0.000001
     0.881611   -0.000001
     0.894828   -0.000001
     0.908049    0.000000
     0.921271   -0.000001
     0.934482    0.000000
     0.947646    0.000000
     0.960667    0.000000
     0.973288    0.000000
     0.984906    0.000000
     0.994731    0.000000
     1.000000    0.000001
Dat file parser warnings
  • Line 2 - X value too large but included: 1.000003 0.002671
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Lednicer format dat file
Selig format dat file

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Polars for AG36 (ag36-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ag36-il50,000932.7 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag36-il50,000536.9 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag36-il100,000950.2 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag36-il100,000551 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ag36-il200,000967.5 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   ag36-il200,000564.3 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag36-il500,000988.9 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag36-il500,000581 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag36-il1,000,0009103 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag36-il1,000,000593 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
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