AG45ct -02f (ag45ct02r-il)
AG45ct -02f - Drela AG45ct -02f airfoil
| Details | Dat file | Parser | |
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(ag45ct02r-il) AG45ct -02f Drela AG45ct -02f airfoil Max thickness 6.9% at 23.3% chord. Max camber 1.8% at 33.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AG45ct -02f
1.000000 0.000311
0.994227 0.000847
0.982595 0.001929
0.969434 0.003139
0.956049 0.004355
0.942645 0.005557
0.929204 0.006747
0.915742 0.007922
0.902251 0.009085
0.888763 0.010232
0.875271 0.011366
0.861775 0.012483
0.848292 0.013586
0.834812 0.014671
0.821351 0.015742
0.807898 0.016797
0.794449 0.017838
0.781009 0.018863
0.767570 0.019874
0.754139 0.020871
0.740701 0.021854
0.727245 0.022823
0.716793 0.023568
0.710626 0.024002
0.707082 0.024251
0.702553 0.024571
0.697239 0.025118
0.686613 0.026207
0.672246 0.027662
0.665190 0.028368
0.654607 0.029418
0.643558 0.030500
0.629239 0.031878
0.612612 0.033445
0.600711 0.034541
0.586534 0.035819
0.572386 0.037063
0.561159 0.038028
0.552085 0.038789
0.543968 0.039459
0.529917 0.040590
0.515878 0.041683
0.501782 0.042740
0.487635 0.043762
0.473459 0.044743
0.459248 0.045684
0.444998 0.046580
0.430752 0.047427
0.416527 0.048221
0.402335 0.048957
0.388199 0.049631
0.374125 0.050243
0.360112 0.050788
0.346152 0.051266
0.332237 0.051674
0.318350 0.052011
0.304472 0.052274
0.290601 0.052459
0.276746 0.052560
0.262911 0.052567
0.249109 0.052477
0.235341 0.052278
0.221593 0.051963
0.207871 0.051520
0.194176 0.050937
0.180507 0.050204
0.166888 0.049307
0.153309 0.048233
0.139793 0.046967
0.126354 0.045491
0.113001 0.043780
0.099775 0.041815
0.086695 0.039554
0.073820 0.036962
0.061195 0.033986
0.048949 0.030569
0.037266 0.026672
0.026537 0.022321
0.017464 0.017772
0.010753 0.013553
0.006324 0.010038
0.003508 0.007194
0.001719 0.004837
0.000641 0.002824
0.000108 0.001102
0.000012 -0.000341
0.000323 -0.001724
0.001200 -0.003122
0.002797 -0.004458
0.005165 -0.005785
0.008624 -0.007213
0.013835 -0.008829
0.021627 -0.010619
0.031916 -0.012345
0.043766 -0.013786
0.056391 -0.014905
0.069386 -0.015756
0.082602 -0.016393
0.095968 -0.016868
0.109435 -0.017200
0.122981 -0.017412
0.136584 -0.017525
0.150238 -0.017559
0.163923 -0.017527
0.177645 -0.017443
0.191390 -0.017314
0.205156 -0.017148
0.218951 -0.016951
0.232789 -0.016727
0.246662 -0.016479
0.260584 -0.016211
0.274554 -0.015926
0.288570 -0.015627
0.302626 -0.015315
0.316706 -0.014990
0.330800 -0.014657
0.344916 -0.014315
0.359042 -0.013965
0.373168 -0.013610
0.387310 -0.013247
0.401465 -0.012878
0.415627 -0.012504
0.429771 -0.012126
0.443898 -0.011743
0.458005 -0.011357
0.472101 -0.010967
0.486182 -0.010574
0.500232 -0.010178
0.514274 -0.009778
0.528296 -0.009379
0.542309 -0.008976
0.549868 -0.008761
0.559467 -0.008487
0.569774 -0.008195
0.583198 -0.007814
0.596337 -0.007448
0.610185 -0.007068
0.623741 -0.006703
0.637286 -0.006344
0.646835 -0.006099
0.655828 -0.005869
0.664399 -0.005656
0.678037 -0.005317
0.691677 -0.004993
0.697217 -0.004864
0.699989 -0.004799
0.702621 -0.004742
0.706923 -0.004644
0.719461 -0.004368
0.733337 -0.004070
0.747215 -0.003781
0.761077 -0.003501
0.774940 -0.003231
0.788815 -0.002969
0.802688 -0.002719
0.816585 -0.002478
0.830472 -0.002249
0.844343 -0.002030
0.858214 -0.001824
0.872063 -0.001626
0.885892 -0.001441
0.899731 -0.001266
0.913535 -0.001102
0.927344 -0.000948
0.941134 -0.000804
0.954910 -0.000674
0.968662 -0.000551
0.982162 -0.000441
0.994091 -0.000353
1.000000 -0.000311
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Polars for AG45ct -02f (ag45ct02r-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag45ct02r-il | 50,000 | 9 | 30.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45ct02r-il | 50,000 | 5 | 34.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45ct02r-il | 100,000 | 9 | 45.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45ct02r-il | 100,000 | 5 | 46.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45ct02r-il | 200,000 | 9 | 60.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45ct02r-il | 200,000 | 5 | 59.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45ct02r-il | 500,000 | 9 | 80.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45ct02r-il | 500,000 | 5 | 76.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45ct02r-il | 1,000,000 | 9 | 94.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45ct02r-il | 1,000,000 | 5 | 89.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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