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AG35 (ag35-il)

AG35 - Drela AG35 airfoil


Airfoil ag35-il
Details Dat file Parser  
(ag35-il) AG35
Drela AG35 airfoil
Max thickness 8.7% 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
AG35
     0.999998    0.002490
     0.994759    0.003346
     0.985091    0.004927
     0.973580    0.006810
     0.961032    0.008862
     0.948054    0.010984
     0.934900    0.013135
     0.921611    0.015308
     0.908313    0.017483
     0.895069    0.019649
     0.882085    0.021772
     0.869641    0.023807
     0.857457    0.025799
     0.845280    0.027791
     0.832888    0.029817
     0.820358    0.031820
     0.807162    0.033810
     0.793920    0.035807
     0.780706    0.037799
     0.767485    0.039793
     0.754283    0.041784
     0.741095    0.043773
     0.727945    0.045756
     0.714849    0.047731
     0.701910    0.049683
     0.689256    0.051591
     0.677196    0.053410
     0.665868    0.055118
     0.653950    0.056821
     0.641439    0.058395
     0.629634    0.059724
     0.616637    0.061083
     0.603508    0.062456
     0.590173    0.063850
     0.576733    0.065256
     0.563295    0.066661
     0.549886    0.068063
     0.536505    0.069462
     0.523180    0.070855
     0.509878    0.072246
     0.496652    0.073629
     0.483548    0.074999
     0.470786    0.076333
     0.458362    0.077628
     0.445896    0.078818
     0.433429    0.079944
     0.420874    0.081007
     0.408286    0.081997
     0.395609    0.082920
     0.382821    0.083766
     0.369887    0.084535
     0.356838    0.085222
     0.343751    0.085813
     0.330663    0.086309
     0.317616    0.086705
     0.304632    0.086997
     0.291702    0.087187
     0.278827    0.087271
     0.265976    0.087249
     0.253136    0.087116
     0.240294    0.086871
     0.227478    0.086509
     0.214700    0.086025
     0.201997    0.085414
     0.189397    0.084673
     0.176924    0.083810
     0.164600    0.082809
     0.152423    0.081657
     0.140376    0.080341
     0.128493    0.078850
     0.116797    0.077175
     0.105297    0.075296
     0.093994    0.073194
     0.082821    0.070835
     0.071861    0.068212
     0.061304    0.065349
     0.051308    0.062264
     0.042046    0.059001
     0.033755    0.055657
     0.026622    0.052361
     0.020720    0.049247
     0.015971    0.046398
     0.012197    0.043833
     0.009198    0.041532
     0.006803    0.039456
     0.004900    0.037586
     0.003379    0.035865
     0.002164    0.034249
     0.001229    0.032717
     0.000559    0.031249
     0.000149    0.029826
     0.000002    0.028464
     0.000102    0.027126
     0.000484    0.025764
     0.001210    0.024382
     0.002270    0.023013
     0.003661    0.021703
     0.005428    0.020443
     0.007602    0.019219
     0.010243    0.018007
     0.013475    0.016774
     0.017495    0.015493
     0.022573    0.014138
     0.029012    0.012694
     0.037035    0.011190
     0.046580    0.009697
     0.057315    0.008300
     0.068834    0.007045
     0.080828    0.005944
     0.093116    0.004984
     0.105597    0.004152
     0.118206    0.003432
     0.130910    0.002812
     0.143690    0.002279
     0.156527    0.001823
     0.169413    0.001438
     0.182341    0.001114
     0.195310    0.000845
     0.208312    0.000624
     0.221345    0.000445
     0.234403    0.000300
     0.247480    0.000191
     0.260580    0.000110
     0.273702    0.000054
     0.286843    0.000019
     0.300001    0.000000
     0.313176   -0.000004
     0.326377   -0.000003
     0.339590   -0.000003
     0.352803   -0.000003
     0.366016   -0.000002
     0.379236   -0.000003
     0.392461   -0.000003
     0.405687   -0.000003
     0.418909   -0.000002
     0.432127   -0.000002
     0.445346   -0.000003
     0.458571   -0.000002
     0.471797   -0.000002
     0.485016   -0.000003
     0.498234   -0.000003
     0.511456   -0.000002
     0.524682   -0.000002
     0.537907   -0.000002
     0.551127   -0.000003
     0.564340   -0.000002
     0.577555   -0.000003
     0.590775   -0.000002
     0.603995   -0.000001
     0.617213   -0.000002
     0.630437   -0.000002
     0.643663   -0.000002
     0.656887   -0.000002
     0.670108   -0.000001
     0.683326   -0.000002
     0.696547   -0.000002
     0.709772   -0.000002
     0.722997   -0.000001
     0.736216   -0.000002
     0.749434   -0.000001
     0.762657   -0.000001
     0.775884   -0.000001
     0.789107   -0.000001
     0.802326   -0.000002
     0.815538   -0.000001
     0.828754   -0.000002
     0.841973   -0.000001
     0.855190    0.000000
     0.868400   -0.000001
     0.881610    0.000000
     0.894825   -0.000001
     0.908046   -0.000001
     0.921267   -0.000001
     0.934476   -0.000001
     0.947640   -0.000001
     0.960660   -0.000001
     0.973282    0.000000
     0.984898    0.000000
     0.994724   -0.000001
     1.000001    0.000000
Dat file parser warnings
  • Line 181 - X value too large but included: 1.000001 0.000000
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Lednicer format dat file
Selig format dat file

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Polars for AG35 (ag35-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ag35-il50,000932.3 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag35-il50,000536.9 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag35-il100,000950.5 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ag35-il100,000551.6 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ag35-il200,000968.5 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag35-il200,000565.3 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag35-il500,000990.8 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag35-il500,000582.2 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag35-il1,000,0009105.2 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   ag35-il1,000,000595.3 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
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