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FX 66-17AII-182 AIRFOIL (fx6617a2-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 66-17AII-182 AIRFOIL (fx6617a2-il)
Reynolds number: 100,000
Max Cl/Cd: 5.9 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx6617a2-il-100000.txt
Download as CSV file: xf-fx6617a2-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 66-17AII-182 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.2674   0.13424   0.12984  -0.0497   1.0000   0.1079
 -12.500  -0.2913   0.13183   0.12759  -0.0544   1.0000   0.1125
 -12.250  -0.2894   0.12737   0.12326  -0.0553   1.0000   0.1143
 -12.000  -0.2682   0.12493   0.12096  -0.0531   1.0000   0.1174
 -11.750  -0.2586   0.11928   0.11531  -0.0634   0.9516   0.1269
 -11.500  -0.2147   0.11304   0.10893  -0.0690   0.9268   0.1334
 -11.250  -0.2345   0.10747   0.10333  -0.0827   0.9090   0.1429
 -11.000  -0.1649   0.10200   0.09756  -0.0840   0.8854   0.1502
 -10.750  -0.1749   0.09684   0.09232  -0.0913   0.8678   0.1597
 -10.500  -0.1434   0.09365   0.08892  -0.0919   0.8501   0.1642
 -10.250  -0.1633   0.08947   0.08476  -0.0964   0.8372   0.1744
 -10.000  -0.1351   0.08682   0.08198  -0.0956   0.8247   0.1789
  -9.750  -0.1428   0.08313   0.07828  -0.0980   0.8158   0.1903
  -9.500  -0.3380   0.05592   0.05061  -0.1166   0.8128   0.0814
  -9.250  -0.3859   0.05244   0.04622  -0.1126   0.8044   0.0714
  -9.000  -0.3757   0.04859   0.04222  -0.1120   0.7967   0.0701
  -8.750  -0.3687   0.04513   0.03851  -0.1110   0.7899   0.0687
  -8.500  -0.3614   0.04217   0.03520  -0.1096   0.7837   0.0674
  -8.250  -0.3523   0.03950   0.03216  -0.1080   0.7771   0.0666
  -8.000  -0.3386   0.03723   0.02944  -0.1066   0.7718   0.0672
  -7.750  -0.3242   0.03564   0.02746  -0.1051   0.7654   0.0693
  -7.500  -0.3068   0.03441   0.02577  -0.1036   0.7597   0.0710
  -7.250  -0.2825   0.03178   0.02305  -0.1034   0.7555   0.0740
  -7.000  -0.2611   0.03071   0.02195  -0.1028   0.7502   0.0779
  -6.750  -0.2367   0.02953   0.02060  -0.1022   0.7453   0.0809
  -6.500  -0.2115   0.02858   0.01943  -0.1015   0.7412   0.0849
  -6.250  -0.1874   0.02740   0.01841  -0.1010   0.7371   0.0902
  -6.000  -0.1663   0.02674   0.01777  -0.0998   0.7320   0.0953
  -5.750  -0.1467   0.02598   0.01706  -0.0984   0.7277   0.1017
  -5.500  -0.1283   0.02535   0.01646  -0.0969   0.7243   0.1143
  -5.250  -0.1168   0.02465   0.01600  -0.0948   0.7206   0.1385
  -5.000  -0.1236   0.02256   0.01514  -0.0911   0.7166   0.2993
  -4.750  -0.1139   0.02338   0.01690  -0.0865   0.7128   0.5358
  -4.500  -0.0888   0.02464   0.01798  -0.0845   0.7094   0.5734
  -4.250  -0.0655   0.02608   0.01933  -0.0819   0.7060   0.6022
  -4.000  -0.0500   0.02771   0.02099  -0.0784   0.7015   0.6300
  -3.750  -0.0292   0.02946   0.02279  -0.0741   0.6980   0.6531
  -3.500  -0.0087   0.03032   0.02355  -0.0712   0.6949   0.6744
  -3.250   0.0140   0.03074   0.02382  -0.0692   0.6923   0.6922
  -3.000   0.0289   0.03147   0.02455  -0.0662   0.6884   0.7031
  -2.750   0.0392   0.03195   0.02501  -0.0638   0.6841   0.7136
  -2.500   0.0538   0.03213   0.02506  -0.0627   0.6808   0.7244
  -2.250   0.0762   0.03224   0.02508  -0.0615   0.6782   0.7314
  -2.000   0.1011   0.03211   0.02476  -0.0613   0.6759   0.7412
  -1.750   0.0957   0.03327   0.02602  -0.0575   0.6706   0.7482
  -1.500   0.0987   0.03404   0.02676  -0.0553   0.6664   0.7568
  -1.250   0.1135   0.03446   0.02714  -0.0536   0.6636   0.7643
  -1.000   0.1374   0.03451   0.02705  -0.0536   0.6613   0.7724
  -0.750   0.1683   0.03436   0.02677  -0.0537   0.6596   0.7785
  -0.500   0.0718   0.03920   0.03192  -0.0422   0.6510   0.7840
  -0.250   0.0677   0.04048   0.03318  -0.0397   0.6483   0.7894
   0.000   0.1020   0.04038   0.03296  -0.0405   0.6459   0.7948
   0.250   0.1619   0.03954   0.03193  -0.0443   0.6442   0.8013
   0.500   0.0921   0.04374   0.03626  -0.0359   0.6414   0.8060
   0.750   0.0794   0.04571   0.03824  -0.0332   0.6400   0.8114
   1.000   0.0812   0.04730   0.03978  -0.0322   0.6400   0.8169
   1.250   0.0910   0.04865   0.04110  -0.0316   0.6413   0.8216
   1.500   0.1046   0.04999   0.04240  -0.0314   0.6423   0.8264
   1.750   0.1261   0.05130   0.04365  -0.0322   0.6440   0.8314
   2.000   0.0203   0.05663   0.04925  -0.0255   0.6979   0.8361
   2.250   0.0516   0.05778   0.05032  -0.0268   0.6937   0.8409
   2.500   0.0912   0.05977   0.05223  -0.0294   0.6915   0.8463
   2.750   0.0791   0.05953   0.05198  -0.0262   0.6808   0.8514
   3.000   0.1115   0.06093   0.05332  -0.0280   0.6775   0.8565
   3.250   0.1524   0.06313   0.05546  -0.0309   0.6755   0.8626
   3.500   0.1422   0.06286   0.05519  -0.0282   0.6639   0.8685
   3.750   0.1788   0.06457   0.05687  -0.0306   0.6609   0.8752
   4.000   0.1785   0.06540   0.05772  -0.0295   0.6533   0.8821
   4.250   0.2074   0.06665   0.05898  -0.0313   0.6475   0.8907
   4.500   0.2485   0.06862   0.06098  -0.0345   0.6448   0.9007
   4.750   0.2502   0.06955   0.06199  -0.0347   0.6356   0.9122
   5.000   0.2944   0.07150   0.06402  -0.0396   0.6308   0.9281
   5.250   0.3433   0.07403   0.06660  -0.0445   0.6284   1.0000
   5.500   0.3307   0.07458   0.06713  -0.0428   0.6178   1.0000
   5.750   0.3649   0.07652   0.06904  -0.0451   0.6141   1.0000
   6.000   0.4077   0.07931   0.07179  -0.0483   0.6123   1.0000
   6.250   0.3905   0.07961   0.07209  -0.0462   0.6007   1.0000
   6.500   0.4257   0.08182   0.07428  -0.0485   0.5978   1.0000
   6.750   0.4199   0.08321   0.07567  -0.0477   0.5891   1.0000
   7.000   0.4482   0.08496   0.07740  -0.0492   0.5837   1.0000
   7.250   0.4859   0.08754   0.07998  -0.0515   0.5813   1.0000
   7.500   0.4713   0.08860   0.08104  -0.0499   0.5709   1.0000
   7.750   0.5042   0.09065   0.08309  -0.0515   0.5668   1.0000
   8.000   0.5464   0.09376   0.08621  -0.0539   0.5649   1.0000
   8.250   0.5233   0.09426   0.08672  -0.0517   0.5528   1.0000
   8.500   0.5623   0.09682   0.08931  -0.0535   0.5499   1.0000
   8.750   0.5446   0.09824   0.09075  -0.0521   0.5396   1.0000
   9.000   0.5786   0.10034   0.09287  -0.0534   0.5352   1.0000
   9.250   0.5698   0.10242   0.09498  -0.0527   0.5269   1.0000
   9.500   0.5970   0.10423   0.09684  -0.0535   0.5207   1.0000
   9.750   0.6296   0.10720   0.09987  -0.0548   0.5176   1.0000
  10.000   0.6195   0.10830   0.10100  -0.0539   0.5059   1.0000
  10.250   0.6558   0.11112   0.10389  -0.0551   0.5024   1.0000
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