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WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il)
Reynolds number: 100,000
Max Cl/Cd: 6.06 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx6617ai-il-100000.txt
Download as CSV file: xf-fx6617ai-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT N
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3049   0.10195   0.09727  -0.0650   0.7839   0.1785
 -10.000  -0.3478   0.05644   0.05163  -0.0938   0.7741   0.0881
  -9.750  -0.3555   0.05142   0.04649  -0.0947   0.7692   0.0855
  -9.500  -0.4405   0.05870   0.05340  -0.0950   0.7756   0.0849
  -9.250  -0.4696   0.05271   0.04651  -0.0958   0.7706   0.0750
  -9.000  -0.4618   0.04908   0.04259  -0.0958   0.7647   0.0740
  -8.750  -0.4523   0.04591   0.03908  -0.0956   0.7582   0.0734
  -8.500  -0.4398   0.04293   0.03569  -0.0952   0.7530   0.0726
  -8.250  -0.4240   0.04008   0.03244  -0.0949   0.7478   0.0713
  -8.000  -0.4052   0.03759   0.02956  -0.0945   0.7424   0.0704
  -7.750  -0.3840   0.03548   0.02707  -0.0939   0.7378   0.0703
  -7.500  -0.3608   0.03373   0.02502  -0.0935   0.7332   0.0709
  -7.250  -0.3362   0.03223   0.02332  -0.0932   0.7277   0.0721
  -7.000  -0.3112   0.03110   0.02193  -0.0927   0.7231   0.0748
  -6.750  -0.2859   0.02973   0.02044  -0.0922   0.7194   0.0780
  -6.500  -0.2615   0.02869   0.01954  -0.0920   0.7147   0.0818
  -6.250  -0.2374   0.02788   0.01873  -0.0914   0.7106   0.0863
  -6.000  -0.2153   0.02699   0.01787  -0.0905   0.7071   0.0927
  -5.750  -0.1935   0.02635   0.01720  -0.0896   0.7040   0.1039
  -5.500  -0.1765   0.02550   0.01659  -0.0889   0.6996   0.1209
  -5.250  -0.1662   0.02346   0.01541  -0.0881   0.6957   0.2171
  -5.000  -0.1558   0.02302   0.01637  -0.0851   0.6923   0.5064
  -4.750  -0.1307   0.02433   0.01753  -0.0832   0.6893   0.5521
  -4.500  -0.1070   0.02572   0.01885  -0.0813   0.6862   0.5795
  -4.250  -0.0852   0.02737   0.02055  -0.0786   0.6824   0.6012
  -4.000  -0.0640   0.02912   0.02232  -0.0750   0.6789   0.6238
  -3.750  -0.0422   0.03013   0.02320  -0.0725   0.6758   0.6455
  -3.500  -0.0190   0.03083   0.02377  -0.0702   0.6732   0.6611
  -3.250   0.0004   0.03171   0.02465  -0.0676   0.6700   0.6705
  -3.000   0.0188   0.03219   0.02510  -0.0667   0.6666   0.6814
  -2.750   0.0398   0.03241   0.02519  -0.0671   0.6635   0.6931
  -2.500   0.0609   0.03271   0.02544  -0.0655   0.6608   0.6995
  -2.250   0.0860   0.03263   0.02518  -0.0659   0.6583   0.7098
  -2.000   0.1106   0.03273   0.02516  -0.0647   0.6563   0.7170
  -1.750   0.1199   0.03381   0.02631  -0.0644   0.6518   0.7265
  -1.500   0.1331   0.03467   0.02719  -0.0633   0.6487   0.7342
  -1.250   0.1519   0.03520   0.02764  -0.0635   0.6460   0.7425
  -1.000   0.1738   0.03545   0.02782  -0.0630   0.6436   0.7491
  -0.750   0.2030   0.03538   0.02760  -0.0640   0.6416   0.7566
  -0.500   0.2056   0.03710   0.02940  -0.0628   0.6378   0.7620
  -0.250   0.1947   0.04017   0.03257  -0.0626   0.6343   0.7689
   0.000   0.1935   0.04224   0.03466  -0.0619   0.6312   0.7744
   0.250   0.1978   0.04397   0.03640  -0.0614   0.6292   0.7804
   0.500   0.1749   0.04775   0.04022  -0.0608   0.6313   0.7870
   0.750   0.1743   0.04991   0.04240  -0.0600   0.6327   0.7924
   1.000   0.1856   0.05193   0.04440  -0.0609   0.6368   0.7986
   1.250   0.2115   0.05329   0.04571  -0.0624   0.6414   0.8048
   1.500   0.2382   0.05434   0.04672  -0.0630   0.6404   0.8113
   1.750   0.1364   0.06175   0.05443  -0.0609   0.6949   0.8159
   2.000   0.1667   0.06285   0.05547  -0.0619   0.6906   0.8220
   2.250   0.2052   0.06466   0.05722  -0.0642   0.6885   0.8292
   2.500   0.1949   0.06482   0.05739  -0.0613   0.6771   0.8353
   2.750   0.2266   0.06620   0.05873  -0.0625   0.6740   0.8426
   3.000   0.2612   0.06827   0.06076  -0.0646   0.6719   0.8499
   3.250   0.2532   0.06817   0.06069  -0.0616   0.6597   0.8567
   3.500   0.2885   0.06995   0.06242  -0.0635   0.6574   0.8652
   3.750   0.2785   0.07053   0.06304  -0.0608   0.6470   0.8726
   4.000   0.3089   0.07190   0.06440  -0.0620   0.6430   0.8818
   4.250   0.3457   0.07387   0.06636  -0.0637   0.6410   0.8923
   4.500   0.3294   0.07420   0.06675  -0.0606   0.6298   0.9023
   4.750   0.3592   0.07568   0.06826  -0.0615   0.6266   0.9163
   5.000   0.3981   0.07792   0.07056  -0.0635   0.6249   0.9362
   5.250   0.3828   0.07806   0.07078  -0.0615   0.6124   1.0002
   5.500   0.4227   0.08042   0.07311  -0.0649   0.6099   1.0002
   5.750   0.4149   0.08181   0.07451  -0.0643   0.6003   1.0002
   6.000   0.4479   0.08373   0.07640  -0.0667   0.5958   1.0002
   6.250   0.4894   0.08635   0.07901  -0.0699   0.5937   1.0002
   6.500   0.4729   0.08755   0.08022  -0.0685   0.5832   1.0002
   6.750   0.5047   0.08964   0.08229  -0.0706   0.5796   1.0002
   7.000   0.5454   0.09244   0.08509  -0.0733   0.5777   1.0002
   7.250   0.5248   0.09348   0.08614  -0.0714   0.5665   1.0002
   7.500   0.5554   0.09570   0.08836  -0.0731   0.5634   1.0002
   7.750   0.5935   0.09866   0.09133  -0.0754   0.5618   1.0002
   8.000   0.5690   0.09962   0.09230  -0.0733   0.5505   1.0002
   8.250   0.5999   0.10191   0.09462  -0.0747   0.5475   1.0002
   8.500   0.6371   0.10506   0.09779  -0.0767   0.5459   1.0002
   8.750   0.6082   0.10597   0.09872  -0.0744   0.5348   1.0002
   9.000   0.6393   0.10832   0.10110  -0.0756   0.5317   1.0002
   9.250   0.6772   0.11168   0.10451  -0.0775   0.5302   1.0002
   9.500   0.6457   0.11245   0.10531  -0.0753   0.5190   1.0002
   9.750   0.6777   0.11495   0.10786  -0.0764   0.5160   1.0002
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