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AG47c -03f (ag47c03-il)

AG47c -03f - Drela AG47c -03f airfoil


Airfoil ag47c03-il
Details Dat file Parser  
(ag47c03-il) AG47c -03f
Drela AG47c -03f airfoil
Max thickness 5.1% at 22.4% chord.
Max camber 1.3% at 33.4% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AG47c -03f
     1.000094    0.015773
     0.994171    0.016000
     0.982184    0.016518
     0.968648    0.017109
     0.954819    0.017717
     0.940950    0.018322
     0.927080    0.018923
     0.913211    0.019515
     0.899342    0.020093
     0.885476    0.020647
     0.871609    0.021183
     0.857748    0.021703
     0.843889    0.022209
     0.830033    0.022699
     0.816179    0.023174
     0.802323    0.023628
     0.788472    0.024068
     0.774621    0.024488
     0.760772    0.024890
     0.746924    0.025276
     0.733076    0.025638
     0.719227    0.025982
     0.706935    0.026267
     0.700789    0.026404
     0.697999    0.026611
     0.692419    0.027022
     0.678608    0.028023
     0.664800    0.029000
     0.650997    0.029950
     0.637188    0.030874
     0.623383    0.031772
     0.611695    0.032513
     0.604258    0.032972
     0.601189    0.033159
     0.594519    0.033562
     0.582039    0.034296
     0.568282    0.035076
     0.557345    0.035675
     0.548490    0.036144
     0.540555    0.036554
     0.526799    0.037239
     0.513046    0.037890
     0.499270    0.038508
     0.485479    0.039092
     0.471698    0.039638
     0.457928    0.040146
     0.444153    0.040615
     0.430382    0.041044
     0.416616    0.041434
     0.402847    0.041779
     0.389082    0.042083
     0.375324    0.042340
     0.361570    0.042554
     0.347817    0.042717
     0.334073    0.042830
     0.320337    0.042891
     0.306606    0.042897
     0.292886    0.042847
     0.279177    0.042736
     0.265471    0.042562
     0.251781    0.042320
     0.238110    0.042009
     0.224447    0.041623
     0.210807    0.041156
     0.197193    0.040606
     0.183600    0.039964
     0.170049    0.039226
     0.156531    0.038384
     0.143065    0.037427
     0.129660    0.036345
     0.116322    0.035122
     0.103087    0.033739
     0.089964    0.032171
     0.077006    0.030388
     0.064245    0.028342
     0.051788    0.025974
     0.039808    0.023209
     0.028684    0.019998
     0.019160    0.016466
     0.011996    0.012986
     0.007174    0.009915
     0.004060    0.007299
     0.002077    0.005020
     0.000902    0.002997
     0.000329    0.001242
     0.000254   -0.000234
     0.000643   -0.001581
     0.001647   -0.002880
     0.003351   -0.004063
     0.005806   -0.005200
     0.009352   -0.006369
     0.014652   -0.007619
     0.022534   -0.008891
     0.032895   -0.010006
     0.044792   -0.010819
     0.057441   -0.011339
     0.070447   -0.011635
     0.083664   -0.011760
     0.097025   -0.011754
     0.110482   -0.011651
     0.124013   -0.011475
     0.137600   -0.011243
     0.151236   -0.010965
     0.164909   -0.010649
     0.178627   -0.010302
     0.192370   -0.009930
     0.206139   -0.009535
     0.219932   -0.009124
     0.233740   -0.008697
     0.247562   -0.008259
     0.261402   -0.007808
     0.275257   -0.007350
     0.289127   -0.006885
     0.303016   -0.006414
     0.316919   -0.005937
     0.330834   -0.005458
     0.344767   -0.004975
     0.358712   -0.004490
     0.372670   -0.004001
     0.386646   -0.003512
     0.400648   -0.003020
     0.414665   -0.002528
     0.428680   -0.002035
     0.442691   -0.001544
     0.456697   -0.001053
     0.470703   -0.000563
     0.484701   -0.000073
     0.498695    0.000416
     0.512689    0.000903
     0.526684    0.001390
     0.540674    0.001875
     0.548232    0.002138
     0.557834    0.002467
     0.568141    0.002823
     0.581594    0.003283
     0.594559    0.003727
     0.601042    0.003949
     0.603610    0.004036
     0.608744    0.004212
     0.622437    0.004676
     0.636127    0.005136
     0.649804    0.005593
     0.663479    0.006045
     0.677146    0.006495
     0.690806    0.006941
     0.699379    0.007216
     0.704795    0.007390
     0.718702    0.007837
     0.732602    0.008275
     0.746491    0.008708
     0.760376    0.009134
     0.774257    0.009555
     0.788140    0.009969
     0.802026    0.010374
     0.815920    0.010772
     0.829806    0.011162
     0.843691    0.011545
     0.857586    0.011918
     0.871471    0.012281
     0.885355    0.012639
     0.899241    0.012989
     0.913118    0.013325
     0.927001    0.013650
     0.940874    0.013967
     0.954746    0.014278
     0.968595    0.014574
     0.982198    0.014813
     0.994211    0.014996
     1.000149    0.015081
Dat file parser warnings
  • Line 2 - X value too large but included: 1.000094 0.015773
  • Line 170 - X value too large but included: 1.000149 0.015081
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Polars for AG47c -03f (ag47c03-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ag47c03-il50,000930.3 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag47c03-il50,000530.7 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag47c03-il100,000942.3 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ag47c03-il100,000539.3 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag47c03-il200,000953 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag47c03-il200,000549.3 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag47c03-il500,000965.2 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag47c03-il500,000566.6 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ag47c03-il1,000,000980.3 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ag47c03-il1,000,000580.7 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
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