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FX 60-100 AIRFOIL (fx60100-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 60-100 AIRFOIL (fx60100-il)
Reynolds number: 200,000
Max Cl/Cd: 84.89 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx60100-il-200000.txt
Download as CSV file: xf-fx60100-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 60-100 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3675   0.09834   0.09483  -0.0404   1.0000   0.0471
  -9.000  -0.3767   0.09469   0.09127  -0.0437   1.0000   0.0475
  -8.750  -0.3848   0.09121   0.08787  -0.0456   1.0000   0.0477
  -8.500  -0.3724   0.08782   0.08449  -0.0410   1.0000   0.0493
  -8.250  -0.3691   0.08584   0.08255  -0.0393   1.0000   0.0503
  -8.000  -0.3725   0.08372   0.08049  -0.0379   1.0000   0.0513
  -7.750  -0.3819   0.08186   0.07871  -0.0359   1.0000   0.0525
  -7.500  -0.3988   0.08032   0.07726  -0.0330   1.0000   0.0531
  -7.250  -0.4195   0.07904   0.07607  -0.0296   1.0000   0.0533
  -7.000  -0.4347   0.07670   0.07381  -0.0286   1.0000   0.0543
  -6.750  -0.4466   0.07337   0.07054  -0.0300   1.0000   0.0555
  -6.500  -0.4350   0.05642   0.05312  -0.0615   0.9952   0.0597
  -6.250  -0.4112   0.05425   0.05113  -0.0607   0.9922   0.0617
  -6.000  -0.3783   0.04947   0.04619  -0.0681   0.9872   0.0665
  -5.750  -0.3375   0.04237   0.03864  -0.0796   0.9834   0.0745
  -5.500  -0.3030   0.03802   0.03385  -0.0859   0.9779   0.0857
  -5.250  -0.2486   0.02548   0.01960  -0.0912   0.9770   0.0311
  -5.000  -0.2068   0.02283   0.01617  -0.0934   0.9743   0.0277
  -4.750  -0.1685   0.02047   0.01361  -0.0960   0.9720   0.0291
  -4.500  -0.1296   0.01909   0.01212  -0.0983   0.9689   0.0307
  -4.250  -0.0953   0.01775   0.01069  -0.0995   0.9635   0.0308
  -4.000  -0.0556   0.01663   0.00951  -0.1018   0.9598   0.0317
  -3.750  -0.0133   0.01571   0.00850  -0.1047   0.9572   0.0340
  -3.500   0.0221   0.01496   0.00762  -0.1063   0.9521   0.0387
  -3.250   0.0629   0.01293   0.00657  -0.1101   0.9487   0.2633
  -3.000   0.1025   0.01261   0.00666  -0.1126   0.9449   0.4086
  -2.750   0.1455   0.01267   0.00676  -0.1154   0.9421   0.4680
  -2.500   0.1768   0.01266   0.00671  -0.1158   0.9343   0.4893
  -2.250   0.2178   0.01255   0.00653  -0.1181   0.9302   0.5106
  -2.000   0.2565   0.01245   0.00642  -0.1199   0.9264   0.5300
  -1.750   0.2859   0.01244   0.00640  -0.1199   0.9183   0.5481
  -1.500   0.3240   0.01227   0.00621  -0.1214   0.9140   0.5658
  -1.250   0.3530   0.01217   0.00611  -0.1213   0.9049   0.5796
  -1.000   0.3882   0.01194   0.00587  -0.1221   0.8993   0.5936
  -0.750   0.4156   0.01186   0.00580  -0.1217   0.8898   0.6065
  -0.500   0.4475   0.01167   0.00561  -0.1219   0.8833   0.6200
  -0.250   0.4750   0.01153   0.00548  -0.1214   0.8729   0.6324
   0.000   0.5029   0.01139   0.00535  -0.1210   0.8626   0.6445
   0.250   0.5321   0.01122   0.00519  -0.1207   0.8538   0.6576
   0.500   0.5592   0.01110   0.00509  -0.1201   0.8427   0.6719
   0.750   0.5858   0.01098   0.00501  -0.1193   0.8304   0.6865
   1.000   0.6125   0.01084   0.00490  -0.1186   0.8170   0.7013
   1.250   0.6387   0.01069   0.00479  -0.1177   0.8024   0.7170
   1.500   0.6649   0.01055   0.00468  -0.1168   0.7870   0.7341
   1.750   0.6909   0.01042   0.00456  -0.1159   0.7703   0.7535
   2.000   0.7160   0.01029   0.00449  -0.1149   0.7518   0.7756
   2.250   0.7402   0.01018   0.00447  -0.1137   0.7333   0.8048
   2.500   0.7620   0.01000   0.00439  -0.1119   0.7151   0.8519
   2.750   0.7867   0.00981   0.00426  -0.1107   0.6955   1.0000
   3.000   0.8151   0.00995   0.00430  -0.1108   0.6719   1.0000
   3.250   0.8425   0.01013   0.00436  -0.1105   0.6478   1.0000
   3.500   0.8693   0.01035   0.00446  -0.1102   0.6240   1.0000
   3.750   0.8957   0.01059   0.00461  -0.1098   0.5999   1.0000
   4.000   0.9217   0.01086   0.00481  -0.1094   0.5763   1.0000
   4.250   0.9474   0.01116   0.00502  -0.1088   0.5528   1.0000
   4.500   0.9728   0.01147   0.00527  -0.1083   0.5278   1.0000
   4.750   0.9977   0.01181   0.00553  -0.1077   0.5008   1.0000
   5.000   1.0223   0.01217   0.00584  -0.1071   0.4736   1.0000
   5.250   1.0464   0.01256   0.00617  -0.1064   0.4441   1.0000
   5.500   1.0695   0.01303   0.00651  -0.1055   0.4102   1.0000
   5.750   1.0916   0.01357   0.00691  -0.1046   0.3689   1.0000
   6.000   1.1122   0.01425   0.00739  -0.1035   0.3221   1.0000
   6.250   1.1321   0.01504   0.00794  -0.1024   0.2730   1.0000
   6.500   1.1516   0.01591   0.00858  -0.1012   0.2269   1.0000
   6.750   1.1709   0.01685   0.00932  -0.1001   0.1880   1.0000
   7.000   1.1898   0.01783   0.01015  -0.0989   0.1588   1.0000
   7.250   1.2081   0.01887   0.01106  -0.0976   0.1362   1.0000
   7.500   1.2265   0.01990   0.01204  -0.0963   0.1184   1.0000
   7.750   1.2453   0.02086   0.01298  -0.0950   0.1045   1.0000
   8.000   1.2628   0.02192   0.01401  -0.0936   0.0940   1.0000
   8.250   1.2775   0.02336   0.01535  -0.0918   0.0857   1.0000
   8.500   1.2970   0.02424   0.01639  -0.0906   0.0794   1.0000
   8.750   1.3134   0.02556   0.01768  -0.0891   0.0746   1.0000
   9.000   1.3319   0.02668   0.01895  -0.0877   0.0705   1.0000
   9.250   1.3496   0.02748   0.01983  -0.0864   0.0661   1.0000
   9.500   1.3652   0.02887   0.02119  -0.0851   0.0619   1.0000
   9.750   1.3807   0.02959   0.02211  -0.0834   0.0582   1.0000
  10.000   1.3927   0.03039   0.02297  -0.0815   0.0542   1.0000
  10.250   1.4047   0.03212   0.02472  -0.0799   0.0503   1.0000
  10.500   1.4155   0.03272   0.02556  -0.0777   0.0474   1.0000
  10.750   1.4254   0.03354   0.02654  -0.0758   0.0439   1.0000
  11.000   1.4316   0.03490   0.02794  -0.0738   0.0404   1.0000
  11.250   1.4411   0.03584   0.02916  -0.0721   0.0359   1.0000
  11.500   1.4436   0.03744   0.03080  -0.0702   0.0295   1.0000
  11.750   1.4456   0.03945   0.03292  -0.0685   0.0230   1.0000
  12.000   1.4435   0.04228   0.03593  -0.0665   0.0199   1.0000
  12.250   1.4470   0.04439   0.03817  -0.0654   0.0175   1.0000
  12.500   1.4450   0.04718   0.04105  -0.0644   0.0160   1.0000
  12.750   1.4374   0.05094   0.04495  -0.0634   0.0151   1.0000
  13.000   1.4358   0.05421   0.04845  -0.0628   0.0144   1.0000
  13.250   1.4318   0.05789   0.05234  -0.0625   0.0139   1.0000
  13.500   1.4265   0.06191   0.05656  -0.0626   0.0134   1.0000
  13.750   1.4199   0.06626   0.06111  -0.0632   0.0130   1.0000
  14.000   1.4121   0.07095   0.06600  -0.0641   0.0127   1.0000
  14.250   1.4032   0.07601   0.07126  -0.0656   0.0124   1.0000
  14.500   1.3931   0.08155   0.07699  -0.0675   0.0122   1.0000
  14.750   1.3817   0.08754   0.08318  -0.0698   0.0121   1.0000
  15.000   1.3693   0.09403   0.08987  -0.0728   0.0120   1.0000
  15.250   1.3552   0.10115   0.09720  -0.0763   0.0119   1.0000
  15.500   1.3399   0.10882   0.10508  -0.0804   0.0119   1.0000
  15.750   1.3218   0.11755   0.11404  -0.0854   0.0120   1.0000
  16.000   1.3009   0.12742   0.12416  -0.0915   0.0122   1.0000
  16.250   1.2773   0.13854   0.13551  -0.0986   0.0124   1.0000
  16.500   1.2467   0.15258   0.14980  -0.1080   0.0129   1.0000
  16.750   1.2064   0.17104   0.16845  -0.1202   0.0139   1.0000
  17.000   1.1556   0.19620   0.19364  -0.1353   0.0158   1.0000
  17.250   1.1167   0.22505   0.22224  -0.1494   0.0202   1.0000
  17.500   1.1202   0.23133   0.22849  -0.1529   0.0202   1.0000
  17.750   1.1248   0.23716   0.23431  -0.1562   0.0204   1.0000
  18.000   1.1309   0.24175   0.23889  -0.1585   0.0210   1.0000
  18.250   0.8867   0.24217   0.23991  -0.1377   0.0392   1.0000
  18.500   0.8792   0.24729   0.24499  -0.1422   0.0372   1.0000
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