AG455ct -02f rot. (ag455ct02r-il)
AG455ct -02f rot. - Drela AG455ct -02f airfoil
| Details | Dat file | Parser | |
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(ag455ct02r-il) AG455ct -02f rot. Drela AG455ct -02f airfoil Max thickness 6.5% 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 |
AG455ct -02f rot.
1.000000 0.000422
0.994170 0.000954
0.982316 0.002035
0.968892 0.003221
0.955202 0.004424
0.941444 0.005624
0.927663 0.006791
0.913863 0.007945
0.900051 0.009079
0.886239 0.010196
0.872425 0.011290
0.858612 0.012360
0.844813 0.013416
0.831008 0.014448
0.817215 0.015463
0.803422 0.016459
0.789639 0.017432
0.775854 0.018393
0.762077 0.019332
0.748302 0.020252
0.734533 0.021156
0.720760 0.022041
0.710075 0.022717
0.704818 0.023044
0.702188 0.023207
0.699579 0.023458
0.694361 0.023961
0.680231 0.025310
0.666108 0.026635
0.659173 0.027278
0.648776 0.028235
0.637922 0.029221
0.623855 0.030481
0.607516 0.031915
0.595808 0.032923
0.581851 0.034103
0.567919 0.035257
0.556858 0.036153
0.547916 0.036865
0.539911 0.037494
0.526047 0.038556
0.512218 0.039585
0.498385 0.040583
0.484548 0.041545
0.470723 0.042469
0.456908 0.043354
0.443086 0.044199
0.429265 0.045000
0.415452 0.045755
0.401634 0.046462
0.387821 0.047118
0.374011 0.047721
0.360206 0.048269
0.346397 0.048755
0.332597 0.049178
0.318804 0.049535
0.305013 0.049822
0.291233 0.050032
0.277461 0.050163
0.263691 0.050206
0.249936 0.050156
0.236200 0.050007
0.222471 0.049752
0.208767 0.049380
0.195088 0.048882
0.181432 0.048247
0.167822 0.047462
0.154250 0.046514
0.140736 0.045384
0.127294 0.044055
0.113930 0.042500
0.100688 0.040698
0.087581 0.038611
0.074669 0.036199
0.061994 0.033406
0.049680 0.030176
0.037910 0.026460
0.027072 0.022269
0.017878 0.017838
0.011050 0.013680
0.006524 0.010179
0.003631 0.007321
0.001787 0.004934
0.000668 0.002882
0.000113 0.001120
0.000013 -0.000359
0.000337 -0.001726
0.001239 -0.003095
0.002858 -0.004390
0.005244 -0.005665
0.008721 -0.007025
0.013948 -0.008549
0.021760 -0.010208
0.032064 -0.011783
0.043924 -0.013076
0.056554 -0.014057
0.069555 -0.014776
0.082773 -0.015286
0.096139 -0.015633
0.109606 -0.015854
0.123148 -0.015975
0.136750 -0.016013
0.150401 -0.015977
0.164083 -0.015879
0.177803 -0.015730
0.191544 -0.015537
0.205308 -0.015310
0.219101 -0.015056
0.232927 -0.014781
0.246776 -0.014488
0.260659 -0.014186
0.274574 -0.013872
0.288521 -0.013551
0.302495 -0.013226
0.316489 -0.012897
0.330500 -0.012566
0.344528 -0.012235
0.358569 -0.011904
0.372617 -0.011572
0.386681 -0.011241
0.400763 -0.010909
0.414858 -0.010579
0.428946 -0.010250
0.443025 -0.009923
0.457091 -0.009599
0.471152 -0.009274
0.485206 -0.008954
0.499244 -0.008636
0.513274 -0.008321
0.527300 -0.008006
0.541320 -0.007694
0.548893 -0.007526
0.558509 -0.007311
0.568829 -0.007080
0.582291 -0.006781
0.595470 -0.006488
0.609368 -0.006177
0.622968 -0.005875
0.636569 -0.005574
0.646155 -0.005363
0.655175 -0.005166
0.663777 -0.004978
0.677452 -0.004682
0.691121 -0.004388
0.696993 -0.004263
0.699968 -0.004200
0.702041 -0.004159
0.706272 -0.004069
0.718805 -0.003804
0.732681 -0.003515
0.746544 -0.003230
0.760397 -0.002950
0.774251 -0.002672
0.788103 -0.002399
0.801961 -0.002128
0.815822 -0.001864
0.829684 -0.001609
0.843548 -0.001374
0.857420 -0.001155
0.871290 -0.000956
0.885162 -0.000778
0.899044 -0.000622
0.912921 -0.000494
0.926805 -0.000391
0.940689 -0.000321
0.954576 -0.000285
0.968440 -0.000285
0.982058 -0.000332
0.994081 -0.000389
1.000000 -0.000422
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Polars for AG455ct -02f rot. (ag455ct02r-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag455ct02r-il | 50,000 | 9 | 30.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag455ct02r-il | 50,000 | 5 | 34 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag455ct02r-il | 100,000 | 9 | 44.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag455ct02r-il | 100,000 | 5 | 46 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag455ct02r-il | 200,000 | 9 | 59.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag455ct02r-il | 200,000 | 5 | 58.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag455ct02r-il | 500,000 | 9 | 78.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag455ct02r-il | 500,000 | 5 | 75.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag455ct02r-il | 1,000,000 | 9 | 92.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag455ct02r-il | 1,000,000 | 5 | 88.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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