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AG03 (flat aft bottom) (ag03-il)

AG03 (flat aft bottom) - Drela AG03 (flat aft bottom) airfoil


Airfoil ag03-il
Details Dat file Parser  
(ag03-il) AG03 (flat aft bottom)
Drela AG03 (flat aft bottom) airfoil
Max thickness 6.2% at 25.7% chord.
Max camber 2% at 33.1% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AG03 (flat aft bottom) 
     1.000000    0.000662
     0.994875    0.001210
     0.984975    0.002247
     0.973308    0.003426
     0.960939    0.004647
     0.948370    0.005887
     0.935754    0.007140
     0.923123    0.008397
     0.910487    0.009656
     0.897855    0.010913
     0.885230    0.012166
     0.872612    0.013411
     0.860000    0.014647
     0.847391    0.015874
     0.834786    0.017089
     0.822181    0.018292
     0.809577    0.019483
     0.796974    0.020660
     0.784368    0.021824
     0.771761    0.022975
     0.759154    0.024113
     0.746543    0.025238
     0.733929    0.026350
     0.721314    0.027451
     0.708699    0.028539
     0.696083    0.029615
     0.683469    0.030677
     0.670857    0.031725
     0.658247    0.032758
     0.645638    0.033774
     0.633032    0.034775
     0.620429    0.035756
     0.607827    0.036720
     0.595228    0.037664
     0.582632    0.038586
     0.570039    0.039488
     0.557449    0.040365
     0.544862    0.041218
     0.532277    0.042044
     0.519696    0.042844
     0.507117    0.043615
     0.494542    0.044357
     0.481970    0.045070
     0.469399    0.045748
     0.456832    0.046394
     0.444268    0.047005
     0.431705    0.047581
     0.419146    0.048121
     0.406590    0.048623
     0.394038    0.049085
     0.381491    0.049506
     0.368949    0.049886
     0.356413    0.050221
     0.343886    0.050509
     0.331366    0.050751
     0.318857    0.050940
     0.306358    0.051075
     0.293873    0.051154
     0.281401    0.051173
     0.268946    0.051128
     0.256511    0.051015
     0.244096    0.050830
     0.231706    0.050567
     0.219345    0.050221
     0.207014    0.049788
     0.194722    0.049257
     0.182473    0.048624
     0.170275    0.047879
     0.158135    0.047014
     0.146065    0.046016
     0.134077    0.044875
     0.122188    0.043576
     0.110415    0.042107
     0.098787    0.040447
     0.087333    0.038582
     0.076099    0.036490
     0.065141    0.034148
     0.054543    0.031546
     0.044438    0.028679
     0.035054    0.025580
     0.026726    0.022341
     0.019796    0.019132
     0.014399    0.016153
     0.010376    0.013518
     0.007410    0.011228
     0.005217    0.009239
     0.003584    0.007497
     0.002364    0.005957
     0.001461    0.004586
     0.000804    0.003348
     0.000336    0.002171
     0.000057    0.001038
     0.000003   -0.000144
     0.000295   -0.001237
     0.001304   -0.002345
     0.002832   -0.003392
     0.005146   -0.004550
     0.008148   -0.005700
     0.012068   -0.006869
     0.017309   -0.008078
     0.024142   -0.009278
     0.032772   -0.010396
     0.042956   -0.011344
     0.053780   -0.012046
     0.065071   -0.012544
     0.076714   -0.012880
     0.088600   -0.013076
     0.100661   -0.013162
     0.112851   -0.013163
     0.125133   -0.013101
     0.137483   -0.012991
     0.149888   -0.012852
     0.162339   -0.012699
     0.174831   -0.012533
     0.187362   -0.012358
     0.199929   -0.012175
     0.212527   -0.011993
     0.225155   -0.011809
     0.237803   -0.011625
     0.250473   -0.011441
     0.263159   -0.011256
     0.275856   -0.011072
     0.288560   -0.010887
     0.301265   -0.010703
     0.313969   -0.010518
     0.326666   -0.010333
     0.339358   -0.010149
     0.352044   -0.009965
     0.364727   -0.009780
     0.377405   -0.009596
     0.390079   -0.009412
     0.402750   -0.009228
     0.415417   -0.009043
     0.428079   -0.008860
     0.440739   -0.008676
     0.453397   -0.008492
     0.466057   -0.008308
     0.478721   -0.008123
     0.491390   -0.007940
     0.504060   -0.007755
     0.516731   -0.007571
     0.529400   -0.007387
     0.542065   -0.007204
     0.554732   -0.007019
     0.567398   -0.006835
     0.580063   -0.006651
     0.592727   -0.006467
     0.605391   -0.006283
     0.618056   -0.006099
     0.630721   -0.005915
     0.643385   -0.005730
     0.656047   -0.005547
     0.668712   -0.005363
     0.681376   -0.005179
     0.694041   -0.004994
     0.706707   -0.004810
     0.719375   -0.004627
     0.732044   -0.004442
     0.744714   -0.004258
     0.757385   -0.004074
     0.770058   -0.003890
     0.782733   -0.003706
     0.795412   -0.003522
     0.808092   -0.003337
     0.820775   -0.003154
     0.833464   -0.002968
     0.846158   -0.002784
     0.858858   -0.002599
     0.871564   -0.002415
     0.884274   -0.002230
     0.896980   -0.002045
     0.909681   -0.001860
     0.922381   -0.001677
     0.935082   -0.001492
     0.947777   -0.001308
     0.960437   -0.001123
     0.972932   -0.000942
     0.984788   -0.000769
     0.994831   -0.000624
     1.000000   -0.000548
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Lednicer format dat file
Selig format dat file

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Polars for AG03 (flat aft bottom) (ag03-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ag03-il50,000932.7 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ag03-il50,000534.6 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag03-il100,000946.7 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag03-il100,000546.4 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag03-il200,000960.6 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag03-il200,000558.2 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ag03-il500,000978.7 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ag03-il500,000574.7 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag03-il1,000,000992.3 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag03-il1,000,000588 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
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