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FX 66-S-196 AIRFOIL (fx66s196-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 66-S-196 AIRFOIL (fx66s196-il)
Reynolds number: 200,000
Max Cl/Cd: 37.19 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx66s196-il-200000.txt
Download as CSV file: xf-fx66s196-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 66-S-196 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.1543   0.10177   0.09779  -0.0947   0.7728   0.0748
 -12.750  -0.1291   0.09933   0.09527  -0.0921   0.7666   0.0767
 -12.500  -0.3803   0.06579   0.06128  -0.1232   0.8073   0.0421
 -12.250  -0.3747   0.06277   0.05812  -0.1233   0.7995   0.0408
 -12.000  -0.3920   0.05834   0.05358  -0.1240   0.7912   0.0402
 -11.750  -0.4106   0.05456   0.04959  -0.1241   0.7847   0.0396
 -11.500  -0.4289   0.05119   0.04606  -0.1237   0.7770   0.0392
 -11.250  -0.4464   0.04780   0.04242  -0.1225   0.7708   0.0383
 -11.000  -0.4642   0.04469   0.03906  -0.1206   0.7643   0.0376
 -10.750  -0.4818   0.04183   0.03587  -0.1176   0.7583   0.0368
 -10.500  -0.4926   0.03906   0.03268  -0.1144   0.7537   0.0361
 -10.250  -0.4918   0.03663   0.02994  -0.1124   0.7478   0.0359
 -10.000  -0.4819   0.03465   0.02769  -0.1110   0.7426   0.0362
  -9.750  -0.4674   0.03301   0.02580  -0.1099   0.7384   0.0368
  -9.500  -0.4516   0.03173   0.02438  -0.1090   0.7330   0.0380
  -9.250  -0.4341   0.03044   0.02287  -0.1081   0.7285   0.0392
  -9.000  -0.4134   0.02901   0.02117  -0.1074   0.7248   0.0402
  -8.750  -0.3912   0.02785   0.01979  -0.1068   0.7211   0.0410
  -8.500  -0.3660   0.02646   0.01831  -0.1065   0.7168   0.0419
  -8.250  -0.3397   0.02502   0.01692  -0.1065   0.7131   0.0440
  -8.000  -0.3191   0.02432   0.01618  -0.1058   0.7098   0.0466
  -7.750  -0.2983   0.02374   0.01546  -0.1050   0.7070   0.0496
  -7.500  -0.2804   0.02283   0.01458  -0.1038   0.7032   0.0525
  -7.250  -0.2659   0.02201   0.01383  -0.1024   0.6995   0.0566
  -7.000  -0.2487   0.02141   0.01315  -0.1012   0.6961   0.0619
  -6.750  -0.2351   0.02058   0.01234  -0.0998   0.6934   0.0696
  -6.500  -0.2196   0.01989   0.01165  -0.0986   0.6908   0.0813
  -6.250  -0.2049   0.01915   0.01102  -0.0974   0.6874   0.1004
  -6.000  -0.1922   0.01807   0.01027  -0.0962   0.6842   0.1472
  -5.750  -0.1835   0.01645   0.00939  -0.0949   0.6813   0.2895
  -5.500  -0.1686   0.01603   0.00992  -0.0931   0.6788   0.4882
  -5.250  -0.1408   0.01653   0.01018  -0.0929   0.6766   0.5306
  -5.000  -0.1142   0.01716   0.01079  -0.0923   0.6741   0.5502
  -4.750  -0.0880   0.01774   0.01133  -0.0918   0.6712   0.5654
  -4.500  -0.0613   0.01829   0.01182  -0.0912   0.6683   0.5795
  -4.250  -0.0344   0.01880   0.01225  -0.0906   0.6658   0.5930
  -4.000  -0.0065   0.01930   0.01272  -0.0901   0.6637   0.6026
  -3.750   0.0211   0.01962   0.01294  -0.0897   0.6619   0.6111
  -3.500   0.0483   0.02004   0.01330  -0.0894   0.6602   0.6197
  -3.250   0.0722   0.02055   0.01386  -0.0883   0.6577   0.6284
  -3.000   0.0967   0.02094   0.01420  -0.0879   0.6553   0.6398
  -2.750   0.1218   0.02138   0.01469  -0.0867   0.6531   0.6450
  -2.500   0.1478   0.02153   0.01478  -0.0866   0.6511   0.6513
  -2.250   0.1739   0.02159   0.01475  -0.0866   0.6493   0.6578
  -2.000   0.2004   0.02180   0.01493  -0.0862   0.6477   0.6621
  -1.750   0.2281   0.02182   0.01485  -0.0866   0.6463   0.6665
  -1.500   0.2555   0.02181   0.01471  -0.0875   0.6447   0.6717
  -1.250   0.2761   0.02204   0.01502  -0.0866   0.6419   0.6741
  -1.000   0.2992   0.02224   0.01524  -0.0862   0.6393   0.6766
  -0.750   0.3240   0.02237   0.01534  -0.0863   0.6372   0.6790
  -0.500   0.3503   0.02243   0.01536  -0.0867   0.6354   0.6810
  -0.250   0.3773   0.02246   0.01533  -0.0873   0.6337   0.6829
   0.000   0.4052   0.02249   0.01527  -0.0880   0.6323   0.6848
   0.250   0.4339   0.02254   0.01523  -0.0889   0.6310   0.6869
   0.500   0.4623   0.02263   0.01527  -0.0896   0.6298   0.6884
   0.750   0.4792   0.02321   0.01593  -0.0886   0.6272   0.6895
   1.000   0.4943   0.02388   0.01668  -0.0875   0.6240   0.6907
   1.250   0.5152   0.02427   0.01710  -0.0872   0.6213   0.6919
   1.500   0.5389   0.02456   0.01740  -0.0871   0.6193   0.6933
   1.750   0.5646   0.02479   0.01761  -0.0874   0.6178   0.6947
   2.000   0.5925   0.02494   0.01774  -0.0879   0.6166   0.6964
   2.250   0.6216   0.02504   0.01781  -0.0885   0.6153   0.6984
   2.500   0.6515   0.02517   0.01789  -0.0894   0.6142   0.7001
   2.750   0.6167   0.02836   0.02133  -0.0822   0.6055   0.7014
   3.000   0.6352   0.02898   0.02195  -0.0817   0.6032   0.7026
   3.250   0.6603   0.02929   0.02226  -0.0818   0.6018   0.7043
   3.500   0.6886   0.02941   0.02241  -0.0822   0.6007   0.7061
   3.750   0.7201   0.02943   0.02243  -0.0831   0.5999   0.7076
   4.000   0.7541   0.02936   0.02237  -0.0843   0.5991   0.7094
   4.250   0.5144   0.04506   0.03825  -0.0588   0.5701   0.7105
   4.500   0.5500   0.04473   0.03793  -0.0596   0.5691   0.7123
   4.750   0.5664   0.04571   0.03892  -0.0590   0.5657   0.7139
   5.000   0.6146   0.04456   0.03778  -0.0608   0.5666   0.7159
   5.250   0.6584   0.04371   0.03695  -0.0623   0.5672   0.7179
   5.500   0.5992   0.04963   0.04289  -0.0568   0.5532   0.7197
   5.750   0.6357   0.04921   0.04251  -0.0575   0.5525   0.7216
   6.000   0.6703   0.04900   0.04236  -0.0582   0.5519   0.7239
   7.500   0.6922   0.05978   0.05345  -0.0520   0.5114   0.7417
   7.750   0.7227   0.05975   0.05350  -0.0525   0.5094   0.7465
   8.000   0.7560   0.05947   0.05329  -0.0531   0.5081   0.7519
   8.250   0.7448   0.06260   0.05651  -0.0517   0.4972   0.7561
   8.500   0.7741   0.06250   0.05651  -0.0521   0.4947   0.7630
   8.750   0.8101   0.06179   0.05591  -0.0526   0.4932   0.7709
   9.000   0.8479   0.06091   0.05515  -0.0533   0.4921   0.7807
   9.250   0.8870   0.05992   0.05433  -0.0541   0.4913   0.7928
   9.500   0.9296   0.05871   0.05330  -0.0552   0.4908   0.8093
  10.500   1.2854   0.03456   0.02999  -0.0690   0.5053   1.0000
  10.750   1.0640   0.05808   0.05343  -0.0590   0.4633   1.0000
  11.000   1.1172   0.05460   0.05003  -0.0596   0.4629   1.0000
  11.250   1.1821   0.04942   0.04497  -0.0604   0.4632   1.0000
  11.500   1.2718   0.04165   0.03732  -0.0621   0.4634   1.0000
  11.750   1.2679   0.04391   0.03964  -0.0609   0.4503   1.0000
  12.000   1.2787   0.04481   0.04060  -0.0603   0.4372   1.0000
  12.250   1.3035   0.04427   0.04010  -0.0601   0.4192   1.0000
  12.500   1.3078   0.04600   0.04184  -0.0592   0.3966   1.0000
  13.000   1.3402   0.04595   0.04103  -0.0568   0.3024   1.0000
  13.250   1.3224   0.04990   0.04473  -0.0551   0.2664   1.0000
  13.500   1.3035   0.05421   0.04881  -0.0537   0.2334   1.0000
  13.750   1.2836   0.05883   0.05319  -0.0526   0.1997   1.0000
  14.000   1.2651   0.06348   0.05761  -0.0516   0.1656   1.0000
  14.250   1.2470   0.06825   0.06213  -0.0509   0.1323   1.0000
  14.500   1.2300   0.07298   0.06661  -0.0504   0.1008   1.0000
  14.750   1.2137   0.07777   0.07114  -0.0499   0.0742   1.0000
  15.000   1.2024   0.08213   0.07537  -0.0496   0.0587   1.0000
  15.250   1.1946   0.08615   0.07932  -0.0495   0.0484   1.0000
  15.500   1.1899   0.08989   0.08305  -0.0494   0.0428   1.0000
  15.750   1.1856   0.09359   0.08679  -0.0494   0.0383   1.0000
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