AG03 (flat aft bottom) (ag03-il)
AG03 (flat aft bottom) - Drela AG03 (flat aft bottom) airfoil
| Details | Dat file | Parser | |
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(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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Polars for AG03 (flat aft bottom) (ag03-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag03-il | 50,000 | 9 | 32.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag03-il | 50,000 | 5 | 34.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag03-il | 100,000 | 9 | 46.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag03-il | 100,000 | 5 | 46.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag03-il | 200,000 | 9 | 60.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag03-il | 200,000 | 5 | 58.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag03-il | 500,000 | 9 | 78.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag03-il | 500,000 | 5 | 74.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag03-il | 1,000,000 | 9 | 92.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag03-il | 1,000,000 | 5 | 88 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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