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FX 66-S-196 AIRFOIL (fx66s196-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 66-S-196 AIRFOIL (fx66s196-il)
Reynolds number: 100,000
Max Cl/Cd: 20 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx66s196-il-100000-n5.txt
Download as CSV file: xf-fx66s196-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.2661   0.10210   0.09676  -0.0922   0.8289   0.0313
 -13.250  -0.3083   0.08695   0.08157  -0.1005   0.8256   0.0304
 -13.000  -0.3815   0.07129   0.06559  -0.1106   0.8216   0.0287
 -12.750  -0.4087   0.06522   0.05924  -0.1139   0.8129   0.0286
 -12.500  -0.4346   0.05989   0.05361  -0.1160   0.8040   0.0284
 -12.250  -0.4449   0.05662   0.05013  -0.1170   0.7952   0.0286
 -12.000  -0.4545   0.05351   0.04679  -0.1174   0.7868   0.0290
 -11.750  -0.4626   0.05063   0.04368  -0.1175   0.7788   0.0293
 -11.500  -0.4686   0.04793   0.04072  -0.1171   0.7715   0.0295
 -11.250  -0.4713   0.04549   0.03801  -0.1165   0.7645   0.0298
 -11.000  -0.4708   0.04326   0.03552  -0.1156   0.7579   0.0303
 -10.750  -0.4663   0.04124   0.03321  -0.1147   0.7525   0.0307
 -10.500  -0.4587   0.03931   0.03103  -0.1137   0.7462   0.0315
 -10.250  -0.4465   0.03756   0.02899  -0.1128   0.7411   0.0322
 -10.000  -0.4338   0.03608   0.02719  -0.1118   0.7364   0.0335
  -9.750  -0.4165   0.03477   0.02588  -0.1113   0.7310   0.0349
  -9.500  -0.4009   0.03375   0.02479  -0.1106   0.7263   0.0363
  -9.250  -0.3818   0.03268   0.02354  -0.1099   0.7226   0.0379
  -9.000  -0.3606   0.03162   0.02236  -0.1093   0.7178   0.0398
  -8.750  -0.3395   0.03070   0.02128  -0.1085   0.7135   0.0415
  -8.500  -0.3247   0.02977   0.02038  -0.1073   0.7096   0.0435
  -8.250  -0.3119   0.02905   0.01960  -0.1059   0.7061   0.0468
  -8.000  -0.2979   0.02842   0.01887  -0.1044   0.7014   0.0502
  -7.750  -0.2863   0.02760   0.01804  -0.1028   0.6974   0.0535
  -7.500  -0.2734   0.02689   0.01728  -0.1014   0.6940   0.0579
  -7.250  -0.2594   0.02621   0.01652  -0.1000   0.6912   0.0642
  -7.000  -0.2464   0.02563   0.01596  -0.0986   0.6873   0.0725
  -6.750  -0.2332   0.02499   0.01537  -0.0972   0.6837   0.0838
  -6.500  -0.2196   0.02431   0.01473  -0.0958   0.6807   0.1009
  -6.250  -0.2062   0.02352   0.01406  -0.0946   0.6781   0.1281
  -6.000  -0.1935   0.02260   0.01334  -0.0934   0.6757   0.1775
  -5.750  -0.1847   0.02153   0.01273  -0.0920   0.6720   0.2535
  -5.500  -0.1742   0.02064   0.01255  -0.0903   0.6686   0.3734
  -5.250  -0.1506   0.02161   0.01399  -0.0880   0.6657   0.4800
  -5.000  -0.1265   0.02162   0.01365  -0.0882   0.6631   0.5241
  -4.750  -0.1001   0.02201   0.01384  -0.0877   0.6611   0.5454
  -4.500  -0.0759   0.02260   0.01433  -0.0868   0.6583   0.5622
  -4.250  -0.0522   0.02306   0.01468  -0.0859   0.6551   0.5769
  -4.000  -0.0279   0.02348   0.01500  -0.0851   0.6523   0.5908
  -3.750  -0.0021   0.02404   0.01552  -0.0838   0.6498   0.6008
  -3.500   0.0235   0.02429   0.01564  -0.0832   0.6477   0.6112
  -3.250   0.0500   0.02445   0.01565  -0.0829   0.6459   0.6192
  -3.000   0.0739   0.02460   0.01571  -0.0824   0.6437   0.6262
  -2.750   0.0960   0.02483   0.01590  -0.0817   0.6408   0.6308
  -2.500   0.1195   0.02485   0.01581  -0.0816   0.6380   0.6357
  -2.250   0.1443   0.02480   0.01564  -0.0818   0.6355   0.6406
  -2.000   0.1700   0.02485   0.01560  -0.0815   0.6334   0.6435
  -1.750   0.1967   0.02482   0.01546  -0.0817   0.6316   0.6463
  -1.500   0.2242   0.02475   0.01527  -0.0822   0.6302   0.6492
  -1.250   0.2488   0.02481   0.01523  -0.0824   0.6282   0.6519
  -1.000   0.2689   0.02505   0.01543  -0.0822   0.6252   0.6552
  -0.750   0.2902   0.02530   0.01568  -0.0817   0.6227   0.6571
  -0.500   0.3132   0.02550   0.01585  -0.0815   0.6205   0.6589
  -0.250   0.3378   0.02563   0.01593  -0.0815   0.6186   0.6606
   0.000   0.3643   0.02570   0.01593  -0.0818   0.6168   0.6625
   0.250   0.3920   0.02573   0.01588  -0.0822   0.6153   0.6648
   0.500   0.4208   0.02574   0.01581  -0.0829   0.6140   0.6675
   0.750   0.4324   0.02649   0.01661  -0.0815   0.6102   0.6703
   1.000   0.4472   0.02712   0.01729  -0.0803   0.6071   0.6723
   1.250   0.4662   0.02758   0.01777  -0.0796   0.6046   0.6742
   1.500   0.4884   0.02791   0.01810  -0.0793   0.6027   0.6762
   1.750   0.5129   0.02816   0.01834  -0.0793   0.6012   0.6783
   2.000   0.5397   0.02834   0.01849  -0.0796   0.5999   0.6809
   2.250   0.5686   0.02843   0.01855  -0.0802   0.5987   0.6832
   2.500   0.5410   0.03102   0.02131  -0.0742   0.5906   0.6852
   2.750   0.5572   0.03172   0.02201  -0.0734   0.5880   0.6872
   3.000   0.5805   0.03203   0.02233  -0.0732   0.5862   0.6887
   3.250   0.6079   0.03216   0.02247  -0.0735   0.5848   0.6903
   3.500   0.6366   0.03226   0.02259  -0.0740   0.5837   0.6922
   4.000   0.5330   0.04179   0.03232  -0.0602   0.5605   0.6966
   4.250   0.5470   0.04287   0.03342  -0.0596   0.5568   0.6990
   4.500   0.5703   0.04336   0.03392  -0.0597   0.5549   0.7016
   4.750   0.5958   0.04371   0.03428  -0.0599   0.5535   0.7041
   5.000   0.6223   0.04395   0.03457  -0.0600   0.5525   0.7065
   5.250   0.6501   0.04411   0.03478  -0.0603   0.5516   0.7091
   5.750   0.6448   0.04869   0.03946  -0.0571   0.5377   0.7153
   6.000   0.6765   0.04858   0.03938  -0.0577   0.5367   0.7191
   6.500   0.6766   0.05294   0.04391  -0.0553   0.5235   0.7257
   6.750   0.7056   0.05304   0.04408  -0.0556   0.5222   0.7304
   7.250   0.7109   0.05722   0.04843  -0.0539   0.5092   0.7393
   7.500   0.7376   0.05751   0.04882  -0.0542   0.5075   0.7449
   7.750   0.7678   0.05752   0.04892  -0.0546   0.5063   0.7514
   8.250   0.7822   0.06073   0.05236  -0.0533   0.4924   0.7647
   8.500   0.8131   0.06052   0.05228  -0.0537   0.4910   0.7736
   9.000   0.8275   0.06396   0.05600  -0.0527   0.4773   0.7947
   9.250   0.8565   0.06385   0.05609  -0.0529   0.4759   0.8121
   9.500   0.8464   0.06707   0.05947  -0.0519   0.4644   0.8319
   9.750   0.8798   0.06640   0.05909  -0.0525   0.4623   0.8830
  10.250   0.9000   0.06867   0.06154  -0.0514   0.4485   1.0000
  10.500   0.9310   0.06828   0.06125  -0.0517   0.4468   1.0000
  10.750   0.9248   0.07131   0.06435  -0.0512   0.4346   1.0000
  11.000   0.9566   0.07057   0.06371  -0.0513   0.4324   1.0000
  11.250   0.9523   0.07349   0.06671  -0.0508   0.4203   1.0000
  11.500   0.9829   0.07276   0.06611  -0.0508   0.4177   1.0000
  12.500   1.0307   0.07702   0.07079  -0.0495   0.3798   1.0000
  12.750   1.0636   0.07530   0.06921  -0.0491   0.3736   1.0000
  13.250   1.0861   0.07767   0.07178  -0.0485   0.3452   1.0000
  13.500   1.1119   0.07687   0.07100  -0.0481   0.3274   1.0000
  13.750   1.1287   0.07730   0.07140  -0.0476   0.3024   1.0000
  14.000   1.1499   0.07699   0.07091  -0.0470   0.2685   1.0000
  14.250   1.1580   0.07846   0.07213  -0.0464   0.2328   1.0000
  14.500   1.1560   0.08139   0.07479  -0.0460   0.1986   1.0000
  14.750   1.1496   0.08507   0.07824  -0.0459   0.1658   1.0000
  15.000   1.1421   0.08903   0.08199  -0.0460   0.1379   1.0000
  15.250   1.1345   0.09316   0.08590  -0.0463   0.1113   1.0000
  15.500   1.1294   0.09705   0.08967  -0.0467   0.0896   1.0000
  15.750   1.1247   0.10095   0.09343  -0.0472   0.0737   1.0000
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