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K3311 (original) (k3311-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: K3311 (original) (k3311-il)
Reynolds number: 200,000
Max Cl/Cd: 76.24 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-k3311-il-200000-n5.txt
Download as CSV file: xf-k3311-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: K3311  (original)                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3803   0.08763   0.08410  -0.0412   1.0000   0.0237
  -9.000  -0.3874   0.08309   0.07963  -0.0427   1.0000   0.0231
  -8.750  -0.3996   0.07807   0.07469  -0.0444   1.0000   0.0225
  -8.250  -0.4687   0.05711   0.05370  -0.0579   0.9963   0.0206
  -8.000  -0.4627   0.04828   0.04447  -0.0666   0.9856   0.0209
  -7.750  -0.4437   0.04512   0.04120  -0.0698   0.9777   0.0216
  -7.500  -0.4175   0.04374   0.03975  -0.0723   0.9709   0.0226
  -7.250  -0.3941   0.03948   0.03513  -0.0760   0.9632   0.0239
  -7.000  -0.3742   0.03465   0.02979  -0.0781   0.9526   0.0246
  -6.750  -0.3510   0.03073   0.02535  -0.0795   0.9431   0.0252
  -6.500  -0.3225   0.02797   0.02204  -0.0808   0.9352   0.0266
  -6.250  -0.2956   0.02646   0.02006  -0.0812   0.9251   0.0275
  -6.000  -0.2683   0.02365   0.01684  -0.0821   0.9175   0.0280
  -5.750  -0.2413   0.02173   0.01465  -0.0824   0.9081   0.0286
  -5.500  -0.2127   0.02038   0.01314  -0.0830   0.8995   0.0296
  -5.250  -0.1830   0.01938   0.01198  -0.0836   0.8907   0.0309
  -5.000  -0.1551   0.01837   0.01080  -0.0836   0.8803   0.0317
  -4.750  -0.1266   0.01740   0.00966  -0.0837   0.8705   0.0322
  -4.500  -0.0985   0.01656   0.00868  -0.0837   0.8604   0.0327
  -4.250  -0.0722   0.01586   0.00787  -0.0833   0.8492   0.0332
  -4.000  -0.0459   0.01523   0.00715  -0.0830   0.8381   0.0338
  -3.750  -0.0196   0.01473   0.00655  -0.0826   0.8268   0.0348
  -3.500   0.0066   0.01430   0.00603  -0.0822   0.8152   0.0359
  -3.250   0.0320   0.01387   0.00552  -0.0816   0.8033   0.0363
  -3.000   0.0575   0.01344   0.00501  -0.0811   0.7924   0.0368
  -2.750   0.0833   0.01304   0.00450  -0.0807   0.7822   0.0376
  -2.500   0.1094   0.01275   0.00410  -0.0803   0.7719   0.0388
  -2.250   0.1356   0.01253   0.00379  -0.0799   0.7613   0.0403
  -2.000   0.1620   0.01236   0.00351  -0.0795   0.7515   0.0423
  -1.750   0.1886   0.01222   0.00329  -0.0791   0.7418   0.0452
  -1.500   0.2147   0.01204   0.00312  -0.0787   0.7315   0.0550
  -1.250   0.2370   0.01118   0.00294  -0.0781   0.7219   0.2459
  -1.000   0.2580   0.01044   0.00293  -0.0771   0.7124   0.4610
  -0.750   0.2822   0.01024   0.00294  -0.0763   0.7026   0.5424
  -0.500   0.3062   0.01007   0.00293  -0.0753   0.6936   0.6152
  -0.250   0.3307   0.00996   0.00291  -0.0744   0.6840   0.6638
   0.000   0.3544   0.00983   0.00293  -0.0733   0.6735   0.7250
   0.250   0.3801   0.00962   0.00295  -0.0722   0.6633   0.8257
   0.500   0.4520   0.00948   0.00290  -0.0812   0.6525   0.9789
   0.750   0.4877   0.00958   0.00292  -0.0830   0.6426   1.0000
   1.000   0.5121   0.00968   0.00294  -0.0823   0.6338   1.0000
   1.250   0.5366   0.00980   0.00297  -0.0817   0.6249   1.0000
   1.500   0.5612   0.00990   0.00303  -0.0810   0.6150   1.0000
   1.750   0.5859   0.01001   0.00308  -0.0804   0.6057   1.0000
   2.000   0.6107   0.01012   0.00314  -0.0798   0.5964   1.0000
   2.250   0.6356   0.01023   0.00322  -0.0792   0.5866   1.0000
   2.500   0.6605   0.01036   0.00330  -0.0786   0.5771   1.0000
   2.750   0.6851   0.01050   0.00337  -0.0779   0.5664   1.0000
   3.000   0.7096   0.01065   0.00348  -0.0772   0.5546   1.0000
   3.250   0.7344   0.01081   0.00360  -0.0766   0.5440   1.0000
   3.500   0.7591   0.01099   0.00374  -0.0760   0.5347   1.0000
   3.750   0.7840   0.01116   0.00391  -0.0754   0.5249   1.0000
   4.000   0.8089   0.01134   0.00409  -0.0749   0.5155   1.0000
   4.250   0.8336   0.01154   0.00427  -0.0743   0.5065   1.0000
   4.500   0.8583   0.01173   0.00448  -0.0737   0.4961   1.0000
   4.750   0.8825   0.01194   0.00471  -0.0730   0.4847   1.0000
   5.000   0.9065   0.01216   0.00493  -0.0723   0.4729   1.0000
   5.250   0.9300   0.01239   0.00515  -0.0715   0.4588   1.0000
   5.500   0.9531   0.01262   0.00541  -0.0706   0.4425   1.0000
   5.750   0.9759   0.01287   0.00567  -0.0697   0.4245   1.0000
   6.000   0.9988   0.01313   0.00594  -0.0689   0.4078   1.0000
   6.250   1.0216   0.01340   0.00624  -0.0680   0.3927   1.0000
   6.500   1.0437   0.01371   0.00658  -0.0670   0.3763   1.0000
   6.750   1.0643   0.01409   0.00693  -0.0658   0.3570   1.0000
   7.000   1.0830   0.01456   0.00733  -0.0643   0.3303   1.0000
   7.250   1.0986   0.01521   0.00781  -0.0623   0.2928   1.0000
   7.500   1.1119   0.01600   0.00836  -0.0602   0.2459   1.0000
   7.750   1.1242   0.01689   0.00904  -0.0579   0.2029   1.0000
   8.000   1.1365   0.01780   0.00976  -0.0557   0.1634   1.0000
   8.250   1.1455   0.01890   0.01061  -0.0531   0.1217   1.0000
   8.500   1.1537   0.02001   0.01154  -0.0503   0.0908   1.0000
   8.750   1.1581   0.02120   0.01253  -0.0470   0.0552   1.0000
   9.000   1.1607   0.02250   0.01367  -0.0435   0.0351   1.0000
   9.250   1.1672   0.02361   0.01480  -0.0406   0.0280   1.0000
   9.500   1.1736   0.02478   0.01602  -0.0379   0.0241   1.0000
   9.750   1.1819   0.02585   0.01721  -0.0357   0.0216   1.0000
  10.000   1.1874   0.02717   0.01859  -0.0333   0.0196   1.0000
  10.250   1.1914   0.02864   0.02017  -0.0310   0.0185   1.0000
  10.500   1.1974   0.03005   0.02172  -0.0291   0.0177   1.0000
  10.750   1.2015   0.03167   0.02347  -0.0273   0.0168   1.0000
  11.000   1.2054   0.03339   0.02530  -0.0257   0.0163   1.0000
  11.250   1.2083   0.03528   0.02729  -0.0243   0.0154   1.0000
  11.500   1.2103   0.03735   0.02949  -0.0231   0.0149   1.0000
  11.750   1.2103   0.03969   0.03191  -0.0220   0.0142   1.0000
  12.000   1.2056   0.04261   0.03491  -0.0210   0.0136   1.0000
  12.250   1.2088   0.04486   0.03730  -0.0203   0.0132   1.0000
  12.500   1.2099   0.04739   0.03994  -0.0197   0.0130   1.0000
  12.750   1.2114   0.04996   0.04264  -0.0192   0.0126   1.0000
  13.000   1.2127   0.05258   0.04539  -0.0188   0.0124   1.0000
  13.250   1.2139   0.05529   0.04822  -0.0184   0.0121   1.0000
  13.500   1.2151   0.05807   0.05111  -0.0182   0.0118   1.0000
  13.750   1.2163   0.06091   0.05408  -0.0180   0.0115   1.0000
  14.000   1.2176   0.06383   0.05712  -0.0180   0.0113   1.0000
  14.250   1.2183   0.06688   0.06032  -0.0182   0.0110   1.0000
  14.500   1.2178   0.07015   0.06369  -0.0187   0.0106   1.0000
  14.750   1.2169   0.07355   0.06719  -0.0192   0.0104   1.0000
  15.000   1.2160   0.07703   0.07079  -0.0199   0.0102   1.0000
  15.250   1.2127   0.08089   0.07473  -0.0205   0.0098   1.0000
  15.500   1.2107   0.08473   0.07873  -0.0212   0.0098   1.0000
  15.750   1.2051   0.08929   0.08347  -0.0228   0.0096   1.0000
  16.000   1.1994   0.09400   0.08837  -0.0245   0.0095   1.0000
  16.250   1.1912   0.09934   0.09393  -0.0268   0.0093   1.0000
  16.500   1.1835   0.10466   0.09943  -0.0291   0.0093   1.0000
  16.750   1.1729   0.11074   0.10572  -0.0320   0.0092   1.0000
  17.000   1.1628   0.11691   0.11208  -0.0351   0.0092   1.0000
  17.250   1.1513   0.12356   0.11892  -0.0388   0.0092   1.0000
  17.500   1.1385   0.13078   0.12633  -0.0429   0.0091   1.0000
  17.750   1.1253   0.13835   0.13408  -0.0474   0.0091   1.0000
  18.000   1.1113   0.14643   0.14234  -0.0523   0.0092   1.0000
  18.250   1.0961   0.15524   0.15131  -0.0579   0.0092   1.0000
  18.500   1.0793   0.16495   0.16118  -0.0640   0.0092   1.0000
  18.750   1.0623   0.17524   0.17159  -0.0704   0.0094   1.0000
  19.000   1.0403   0.18819   0.18465  -0.0781   0.0095   1.0000
  19.250   1.0182   0.20261   0.19911  -0.0859   0.0097   1.0000
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