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AG455ct -02f rot. (ag455ct02r-il)

AG455ct -02f rot. - Drela AG455ct -02f airfoil


Airfoil ag455ct02r-il
Details Dat file Parser  
(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)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ag455ct02r-il50,000930.5 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag455ct02r-il50,000534 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ag455ct02r-il100,000944.7 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ag455ct02r-il100,000546 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag455ct02r-il200,000959.5 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag455ct02r-il200,000558.3 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag455ct02r-il500,000978.7 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag455ct02r-il500,000575.2 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag455ct02r-il1,000,000992.9 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag455ct02r-il1,000,000588.6 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
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