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FX 63-143 AIRFOIL (fx63143-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 63-143 AIRFOIL (fx63143-il)
Reynolds number: 200,000
Max Cl/Cd: 65.81 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63143-il-200000-n5.txt
Download as CSV file: xf-fx63143-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-143 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3845   0.09142   0.08801  -0.0417   1.0000   0.0111
 -10.000  -0.3887   0.08668   0.08331  -0.0439   1.0000   0.0109
  -9.750  -0.3959   0.08121   0.07791  -0.0467   1.0000   0.0107
  -9.500  -0.4091   0.07396   0.07072  -0.0515   1.0000   0.0105
  -9.250  -0.4348   0.06547   0.06221  -0.0576   1.0000   0.0102
  -9.000  -0.4832   0.05564   0.05215  -0.0595   0.9822   0.0096
  -8.750  -0.4769   0.05015   0.04637  -0.0641   0.9290   0.0095
  -8.500  -0.4560   0.04381   0.03951  -0.0703   0.8948   0.0093
  -8.250  -0.4389   0.03831   0.03343  -0.0733   0.8600   0.0091
  -7.750  -0.4181   0.03010   0.02398  -0.0713   0.8068   0.0086
  -7.500  -0.4051   0.02692   0.02019  -0.0693   0.7871   0.0084
  -7.250  -0.3879   0.02439   0.01713  -0.0677   0.7701   0.0083
  -7.000  -0.3679   0.02257   0.01494  -0.0664   0.7548   0.0082
  -6.750  -0.3468   0.02120   0.01329  -0.0653   0.7412   0.0082
  -6.500  -0.3255   0.02019   0.01206  -0.0642   0.7289   0.0082
  -6.250  -0.3041   0.01935   0.01107  -0.0632   0.7173   0.0083
  -6.000  -0.2822   0.01868   0.01023  -0.0623   0.7072   0.0083
  -5.750  -0.2602   0.01808   0.00950  -0.0613   0.6972   0.0084
  -5.500  -0.2375   0.01761   0.00893  -0.0605   0.6880   0.0086
  -5.250  -0.2148   0.01716   0.00836  -0.0597   0.6790   0.0087
  -5.000  -0.1914   0.01680   0.00792  -0.0590   0.6708   0.0089
  -4.750  -0.1680   0.01647   0.00749  -0.0583   0.6626   0.0091
  -4.500  -0.1441   0.01618   0.00711  -0.0577   0.6549   0.0095
  -4.250  -0.1204   0.01583   0.00665  -0.0570   0.6472   0.0110
  -4.000  -0.0958   0.01559   0.00623  -0.0563   0.6406   0.0127
  -3.750  -0.0704   0.01544   0.00598  -0.0559   0.6332   0.0143
  -3.500  -0.0449   0.01534   0.00575  -0.0555   0.6269   0.0159
  -3.250  -0.0205   0.01506   0.00536  -0.0550   0.6210   0.0187
  -3.000   0.0040   0.01478   0.00501  -0.0545   0.6153   0.0205
  -2.750   0.0292   0.01461   0.00475  -0.0541   0.6100   0.0215
  -2.500   0.0550   0.01449   0.00456  -0.0538   0.6047   0.0220
  -2.250   0.0808   0.01438   0.00440  -0.0535   0.5986   0.0224
  -2.000   0.1065   0.01430   0.00423  -0.0532   0.5925   0.0229
  -1.750   0.1322   0.01419   0.00411  -0.0529   0.5846   0.0238
  -1.500   0.1574   0.01405   0.00398  -0.0525   0.5762   0.0314
  -1.250   0.1834   0.01400   0.00388  -0.0522   0.5677   0.0326
  -1.000   0.2094   0.01398   0.00376  -0.0519   0.5601   0.0336
  -0.750   0.2355   0.01396   0.00368  -0.0516   0.5526   0.0352
  -0.500   0.2616   0.01396   0.00361  -0.0514   0.5454   0.0375
  -0.250   0.2869   0.01383   0.00351  -0.0510   0.5378   0.0634
   0.000   0.3121   0.01370   0.00343  -0.0507   0.5290   0.0812
   0.250   0.3382   0.01373   0.00340  -0.0504   0.5202   0.1019
   0.500   0.3641   0.01370   0.00337  -0.0502   0.5112   0.1089
   0.750   0.3900   0.01362   0.00334  -0.0500   0.5034   0.1446
   1.000   0.4159   0.01359   0.00332  -0.0498   0.4948   0.1597
   1.250   0.4407   0.01332   0.00331  -0.0496   0.4874   0.2580
   1.500   0.4632   0.01256   0.00330  -0.0493   0.4799   0.4807
   1.750   0.4772   0.01189   0.00358  -0.0463   0.4729   0.7250
   2.000   0.4883   0.01208   0.00409  -0.0417   0.4657   0.8192
   2.250   0.5103   0.01226   0.00426  -0.0403   0.4580   0.8457
   2.500   0.5339   0.01242   0.00442  -0.0393   0.4514   0.8627
   2.750   0.5561   0.01261   0.00461  -0.0380   0.4442   0.8804
   3.000   0.5725   0.01288   0.00489  -0.0352   0.4380   0.9036
   3.250   0.5900   0.01307   0.00510  -0.0326   0.4313   0.9196
   3.500   0.6115   0.01319   0.00519  -0.0314   0.4249   0.9273
   3.750   0.6341   0.01328   0.00528  -0.0301   0.4189   0.9347
   4.000   0.6551   0.01339   0.00538  -0.0287   0.4123   0.9443
   4.250   0.6793   0.01350   0.00549  -0.0278   0.4061   0.9557
   4.500   0.7189   0.01362   0.00564  -0.0303   0.3988   0.9641
   4.750   0.7473   0.01374   0.00576  -0.0306   0.3906   0.9707
   5.000   0.7913   0.01388   0.00594  -0.0343   0.3792   0.9746
   5.250   0.8266   0.01403   0.00611  -0.0362   0.3696   0.9782
   5.500   0.8518   0.01418   0.00626  -0.0361   0.3605   0.9811
   5.750   0.8774   0.01434   0.00644  -0.0361   0.3530   0.9834
   6.000   0.9065   0.01452   0.00664  -0.0369   0.3457   0.9850
   6.250   0.9348   0.01472   0.00687  -0.0375   0.3382   0.9870
   6.500   0.9633   0.01490   0.00713  -0.0382   0.3296   0.9892
   6.750   0.9897   0.01512   0.00740  -0.0384   0.3185   0.9918
   7.000   1.0141   0.01541   0.00771  -0.0383   0.3046   0.9942
   7.250   1.0360   0.01587   0.00810  -0.0380   0.2861   0.9971
   7.500   1.0545   0.01634   0.00854  -0.0370   0.2610   1.0000
   7.750   1.0532   0.01687   0.00898  -0.0320   0.2382   1.0000
   8.000   1.0537   0.01729   0.00937  -0.0274   0.2271   1.0000
   8.250   1.0528   0.01768   0.00976  -0.0226   0.2176   1.0000
   8.750   1.0597   0.01884   0.01087  -0.0154   0.1801   1.0000
   9.000   1.0700   0.01952   0.01157  -0.0134   0.1686   1.0000
   9.500   1.0810   0.02173   0.01366  -0.0092   0.1295   1.0000
   9.750   1.0917   0.02272   0.01472  -0.0080   0.1146   1.0000
  10.000   1.0935   0.02435   0.01629  -0.0064   0.0944   1.0000
  10.250   1.0979   0.02598   0.01792  -0.0054   0.0893   1.0000
  10.500   1.1067   0.02740   0.01944  -0.0048   0.0840   1.0000
  10.750   1.1165   0.02883   0.02098  -0.0044   0.0765   1.0000
  11.000   1.1266   0.03029   0.02255  -0.0042   0.0658   1.0000
  11.250   1.1282   0.03252   0.02477  -0.0038   0.0610   1.0000
  11.500   1.1299   0.03484   0.02711  -0.0036   0.0582   1.0000
  11.750   1.1299   0.03739   0.02971  -0.0034   0.0556   1.0000
  12.000   1.1336   0.03965   0.03210  -0.0034   0.0532   1.0000
  12.250   1.1373   0.04195   0.03456  -0.0035   0.0501   1.0000
  12.500   1.1352   0.04488   0.03759  -0.0036   0.0471   1.0000
  12.750   1.1477   0.04638   0.03929  -0.0038   0.0406   1.0000
  13.000   1.1516   0.04878   0.04177  -0.0040   0.0352   1.0000
  13.250   1.1535   0.05144   0.04447  -0.0044   0.0326   1.0000
  13.500   1.1539   0.05434   0.04741  -0.0048   0.0304   1.0000
  13.750   1.1547   0.05729   0.05047  -0.0053   0.0290   1.0000
  14.000   1.1549   0.06039   0.05368  -0.0059   0.0278   1.0000
  14.250   1.1550   0.06358   0.05698  -0.0067   0.0268   1.0000
  14.500   1.1545   0.06691   0.06041  -0.0075   0.0258   1.0000
  14.750   1.1535   0.07037   0.06396  -0.0084   0.0248   1.0000
  15.000   1.1513   0.07406   0.06772  -0.0095   0.0237   1.0000
  15.250   1.1489   0.07786   0.07160  -0.0106   0.0225   1.0000
  15.500   1.1509   0.08110   0.07497  -0.0117   0.0218   1.0000
  15.750   1.1534   0.08434   0.07834  -0.0128   0.0208   1.0000
  16.000   1.1551   0.08775   0.08187  -0.0140   0.0198   1.0000
  16.250   1.1563   0.09127   0.08550  -0.0153   0.0190   1.0000
  16.500   1.1567   0.09493   0.08928  -0.0168   0.0183   1.0000
  16.750   1.1565   0.09876   0.09320  -0.0183   0.0176   1.0000
  17.000   1.1549   0.10283   0.09735  -0.0200   0.0170   1.0000
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