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FX 66-17AII-182 AIRFOIL (fx6617a2-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 66-17AII-182 AIRFOIL (fx6617a2-il)
Reynolds number: 50,000
Max Cl/Cd: 8.27 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx6617a2-il-50000-n5.txt
Download as CSV file: xf-fx6617a2-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.2922   0.11900   0.11268  -0.0583   1.0000   0.0542
 -12.000  -0.2955   0.11468   0.10849  -0.0599   1.0000   0.0539
 -11.750  -0.3010   0.11029   0.10425  -0.0615   1.0000   0.0540
 -11.500  -0.3024   0.10446   0.09855  -0.0652   0.9864   0.0536
 -11.250  -0.3016   0.09651   0.09061  -0.0723   0.9409   0.0532
 -11.000  -0.3116   0.08622   0.08026  -0.0819   0.9189   0.0521
 -10.750  -0.3379   0.07538   0.06921  -0.0928   0.9000   0.0507
 -10.500  -0.3886   0.06555   0.05879  -0.1029   0.8774   0.0482
 -10.250  -0.3903   0.06147   0.05443  -0.1060   0.8576   0.0488
 -10.000  -0.3986   0.05822   0.05085  -0.1067   0.8403   0.0490
  -9.750  -0.4007   0.05548   0.04784  -0.1065   0.8261   0.0496
  -9.500  -0.4000   0.05284   0.04488  -0.1059   0.8140   0.0501
  -9.250  -0.3943   0.05056   0.04231  -0.1053   0.8036   0.0514
  -9.000  -0.3889   0.04845   0.03992  -0.1042   0.7932   0.0531
  -8.750  -0.3806   0.04629   0.03736  -0.1033   0.7848   0.0551
  -8.500  -0.3699   0.04419   0.03484  -0.1021   0.7761   0.0568
  -8.250  -0.3528   0.04208   0.03221  -0.1013   0.7692   0.0583
  -8.000  -0.3321   0.04033   0.03037  -0.1008   0.7615   0.0610
  -7.750  -0.3088   0.03895   0.02882  -0.1004   0.7557   0.0648
  -7.500  -0.2829   0.03765   0.02729  -0.0998   0.7488   0.0681
  -7.250  -0.2506   0.03646   0.02583  -0.0994   0.7431   0.0715
  -7.000  -0.2264   0.03551   0.02487  -0.0987   0.7379   0.0766
  -6.750  -0.2071   0.03483   0.02406  -0.0974   0.7316   0.0830
  -6.500  -0.1905   0.03400   0.02322  -0.0959   0.7265   0.0888
  -6.250  -0.1755   0.03321   0.02232  -0.0942   0.7221   0.0968
  -5.750  -0.1571   0.03149   0.02077  -0.0906   0.7117   0.1264
  -5.500  -0.1502   0.03014   0.01973  -0.0888   0.7078   0.1663
  -5.250  -0.1501   0.02882   0.01908  -0.0864   0.7026   0.2579
  -5.000  -0.1423   0.02925   0.02085  -0.0812   0.6979   0.4437
  -4.750  -0.1253   0.03032   0.02174  -0.0785   0.6940   0.5322
  -4.500  -0.1059   0.03172   0.02289  -0.0753   0.6908   0.5806
  -4.250  -0.0895   0.03312   0.02422  -0.0716   0.6856   0.6080
  -4.000  -0.0720   0.03379   0.02470  -0.0690   0.6814   0.6309
  -3.750  -0.0496   0.03419   0.02488  -0.0671   0.6780   0.6477
  -3.500  -0.0277   0.03428   0.02470  -0.0658   0.6749   0.6620
  -3.250  -0.0145   0.03467   0.02502  -0.0636   0.6700   0.6713
  -3.000   0.0021   0.03481   0.02499  -0.0622   0.6660   0.6814
  -2.750   0.0209   0.03478   0.02475  -0.0612   0.6627   0.6928
  -2.500   0.0462   0.03480   0.02457  -0.0604   0.6601   0.7011
  -2.250   0.0539   0.03518   0.02489  -0.0582   0.6551   0.7107
  -2.000   0.0680   0.03547   0.02508  -0.0565   0.6508   0.7188
  -1.750   0.0872   0.03552   0.02496  -0.0558   0.6476   0.7263
  -1.500   0.1111   0.03551   0.02479  -0.0554   0.6450   0.7323
  -1.250   0.1210   0.03593   0.02511  -0.0541   0.6407   0.7395
  -1.000   0.1293   0.03653   0.02569  -0.0520   0.6356   0.7445
  -0.750   0.1488   0.03677   0.02579  -0.0515   0.6322   0.7506
  -0.500   0.1730   0.03685   0.02571  -0.0517   0.6297   0.7564
  -0.250   0.1956   0.03705   0.02580  -0.0513   0.6272   0.7613
   0.000   0.1844   0.03852   0.02732  -0.0477   0.6201   0.7673
   0.250   0.2024   0.03894   0.02764  -0.0473   0.6165   0.7725
   0.500   0.2270   0.03915   0.02775  -0.0472   0.6140   0.7772
   0.750   0.2555   0.03928   0.02776  -0.0478   0.6121   0.7824
   1.000   0.2293   0.04164   0.03019  -0.0433   0.6036   0.7881
   1.250   0.2483   0.04215   0.03064  -0.0428   0.6002   0.7930
   1.500   0.2749   0.04244   0.03084  -0.0432   0.5979   0.7984
   2.000   0.2676   0.04588   0.03430  -0.0391   0.5865   0.8096
   2.250   0.2908   0.04645   0.03480  -0.0393   0.5836   0.8155
   2.500   0.3195   0.04675   0.03505  -0.0399   0.5815   0.8211
   2.750   0.3063   0.04931   0.03765  -0.0378   0.5744   0.8278
   3.000   0.3211   0.05044   0.03876  -0.0377   0.5703   0.8345
   3.250   0.3454   0.05105   0.03937  -0.0381   0.5675   0.8412
   3.500   0.3744   0.05151   0.03980  -0.0388   0.5654   0.8490
   3.750   0.3644   0.05407   0.04245  -0.0375   0.5585   0.8579
   4.000   0.3817   0.05522   0.04363  -0.0378   0.5544   0.8675
   4.250   0.4088   0.05593   0.04438  -0.0388   0.5516   0.8786
   4.500   0.4416   0.05656   0.04507  -0.0404   0.5495   0.8924
   5.000   0.4618   0.06071   0.04943  -0.0430   0.5384   1.0000
   5.250   0.4876   0.06170   0.05039  -0.0441   0.5356   1.0000
   5.500   0.5175   0.06254   0.05120  -0.0454   0.5336   1.0000
   5.750   0.5036   0.06574   0.05440  -0.0447   0.5263   1.0000
   6.000   0.5222   0.06715   0.05579  -0.0453   0.5225   1.0000
   6.250   0.5480   0.06820   0.05684  -0.0462   0.5197   1.0000
   6.500   0.5547   0.07032   0.05896  -0.0462   0.5149   1.0000
   6.750   0.5606   0.07243   0.06108  -0.0462   0.5095   1.0000
   7.000   0.5818   0.07371   0.06236  -0.0467   0.5059   1.0000
   7.250   0.6097   0.07463   0.06331  -0.0474   0.5034   1.0000
   7.500   0.6013   0.07755   0.06626  -0.0468   0.4960   1.0000
   7.750   0.6189   0.07899   0.06773  -0.0471   0.4916   1.0000
   8.000   0.6449   0.08000   0.06877  -0.0476   0.4887   1.0000
   8.250   0.6409   0.08271   0.07153  -0.0472   0.4816   1.0000
   8.500   0.6566   0.08428   0.07317  -0.0474   0.4769   1.0000
   8.750   0.6819   0.08532   0.07427  -0.0477   0.4738   1.0000
   9.000   0.6780   0.08807   0.07707  -0.0474   0.4662   1.0000
   9.250   0.6955   0.08951   0.07859  -0.0476   0.4614   1.0000
   9.500   0.7225   0.09040   0.07957  -0.0479   0.4584   1.0000
   9.750   0.7147   0.09342   0.08267  -0.0476   0.4495   1.0000
  10.000   0.7374   0.09449   0.08383  -0.0477   0.4452   1.0000
  10.250   0.7401   0.09692   0.08634  -0.0477   0.4379   1.0000
  10.500   0.7555   0.09843   0.08798  -0.0477   0.4320   1.0000
  10.750   0.7833   0.09910   0.08877  -0.0478   0.4287   1.0000
  11.000   0.7757   0.10225   0.09201  -0.0478   0.4187   1.0000
  11.250   0.8019   0.10292   0.09281  -0.0478   0.4147   1.0000
  11.500   0.7974   0.10591   0.09590  -0.0479   0.4050   1.0000
  11.750   0.8230   0.10648   0.09664  -0.0478   0.4005   1.0000
  12.000   0.8198   0.10943   0.09969  -0.0479   0.3906   1.0000
  12.250   0.8460   0.10979   0.10021  -0.0477   0.3858   1.0000
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