AG47c -03f (ag47c03-il)
AG47c -03f - Drela AG47c -03f airfoil
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(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
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for AG47c -03f (ag47c03-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag47c03-il | 50,000 | 9 | 30.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag47c03-il | 50,000 | 5 | 30.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag47c03-il | 100,000 | 9 | 42.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag47c03-il | 100,000 | 5 | 39.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag47c03-il | 200,000 | 9 | 53 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag47c03-il | 200,000 | 5 | 49.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag47c03-il | 500,000 | 9 | 65.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag47c03-il | 500,000 | 5 | 66.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag47c03-il | 1,000,000 | 9 | 80.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag47c03-il | 1,000,000 | 5 | 80.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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