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FX 63-143 AIRFOIL (fx63143-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 63-143 AIRFOIL (fx63143-il)
Reynolds number: 200,000
Max Cl/Cd: 72.8 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63143-il-200000.txt
Download as CSV file: xf-fx63143-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3643   0.10051   0.09716  -0.0398   1.0000   0.0410
 -10.000  -0.3811   0.09330   0.09003  -0.0463   1.0000   0.0418
  -9.750  -0.4023   0.08465   0.08144  -0.0549   1.0000   0.0419
  -9.500  -0.3768   0.08680   0.08363  -0.0464   1.0000   0.0429
  -9.250  -0.3778   0.08328   0.08016  -0.0474   1.0000   0.0437
  -9.000  -0.3862   0.07836   0.07531  -0.0505   1.0000   0.0442
  -8.750  -0.4059   0.07261   0.06960  -0.0546   1.0000   0.0443
  -8.500  -0.4300   0.06896   0.06598  -0.0542   1.0000   0.0442
  -8.250  -0.4586   0.06695   0.06404  -0.0504   0.9998   0.0441
  -8.000  -0.4642   0.05843   0.05495  -0.0590   0.9616   0.0472
  -7.750  -0.4298   0.05508   0.05170  -0.0626   0.9456   0.0489
  -7.500  -0.4047   0.04996   0.04623  -0.0683   0.9252   0.0539
  -7.250  -0.3738   0.04557   0.04142  -0.0735   0.9034   0.0599
  -6.500  -0.3123   0.02925   0.02281  -0.0720   0.8355   0.0298
  -6.250  -0.2912   0.02590   0.01892  -0.0704   0.8185   0.0257
  -6.000  -0.2677   0.02318   0.01561  -0.0688   0.8034   0.0230
  -5.750  -0.2422   0.02147   0.01361  -0.0680   0.7897   0.0220
  -5.500  -0.2156   0.01989   0.01165  -0.0671   0.7776   0.0213
  -5.250  -0.1914   0.01890   0.01052  -0.0662   0.7648   0.0212
  -5.000  -0.1690   0.01791   0.00949  -0.0652   0.7533   0.0215
  -4.750  -0.1473   0.01712   0.00860  -0.0640   0.7437   0.0221
  -4.500  -0.1272   0.01639   0.00782  -0.0627   0.7332   0.0231
  -4.250  -0.1057   0.01582   0.00717  -0.0616   0.7246   0.0248
  -4.000  -0.0820   0.01556   0.00691  -0.0608   0.7153   0.0276
  -3.750  -0.0573   0.01535   0.00658  -0.0602   0.7075   0.0317
  -3.500  -0.0328   0.01517   0.00626  -0.0595   0.6992   0.0362
  -3.250  -0.0085   0.01488   0.00585  -0.0590   0.6928   0.0436
  -3.000   0.0151   0.01460   0.00565  -0.0584   0.6852   0.0505
  -2.750   0.0412   0.01453   0.00548  -0.0581   0.6787   0.0641
  -2.500   0.0666   0.01443   0.00532  -0.0577   0.6722   0.0717
  -2.250   0.0912   0.01423   0.00517  -0.0572   0.6649   0.0972
  -2.000   0.1176   0.01418   0.00502  -0.0570   0.6583   0.1115
  -1.750   0.1412   0.01393   0.00490  -0.0564   0.6496   0.1567
  -1.500   0.1630   0.01330   0.00472  -0.0557   0.6428   0.2964
  -1.250   0.1864   0.01300   0.00466  -0.0551   0.6349   0.3727
  -1.000   0.2114   0.01279   0.00456  -0.0547   0.6279   0.4291
  -0.750   0.2358   0.01257   0.00452  -0.0543   0.6209   0.4957
  -0.500   0.2595   0.01228   0.00451  -0.0535   0.6135   0.5738
  -0.250   0.2742   0.01201   0.00491  -0.0498   0.6076   0.7509
   0.000   0.2915   0.01233   0.00545  -0.0464   0.5994   0.8230
   0.250   0.3149   0.01256   0.00557  -0.0450   0.5922   0.8470
   0.500   0.3382   0.01268   0.00567  -0.0440   0.5845   0.8609
   0.750   0.3626   0.01283   0.00574  -0.0429   0.5776   0.8694
   1.000   0.3860   0.01297   0.00583  -0.0418   0.5707   0.8804
   1.250   0.4085   0.01310   0.00591  -0.0405   0.5635   0.8919
   1.500   0.4333   0.01327   0.00597  -0.0395   0.5580   0.9000
   1.750   0.4541   0.01342   0.00614  -0.0377   0.5508   0.9125
   2.000   0.4821   0.01366   0.00635  -0.0368   0.5444   0.9309
   2.250   0.5102   0.01380   0.00643  -0.0366   0.5383   0.9426
   2.500   0.5589   0.01388   0.00650  -0.0407   0.5312   0.9501
   2.750   0.6585   0.01401   0.00653  -0.0550   0.5230   0.9719
   3.000   0.7052   0.01395   0.00650  -0.0592   0.5161   0.9788
   3.250   0.7759   0.01377   0.00626  -0.0684   0.5090   0.9933
   3.500   0.8250   0.01359   0.00614  -0.0733   0.5023   1.0000
   3.750   0.8453   0.01364   0.00622  -0.0721   0.4970   1.0000
   4.000   0.8661   0.01371   0.00626  -0.0711   0.4922   1.0000
   4.250   0.8860   0.01378   0.00640  -0.0698   0.4867   1.0000
   4.500   0.9061   0.01387   0.00654  -0.0686   0.4816   1.0000
   4.750   0.9264   0.01395   0.00663  -0.0675   0.4768   1.0000
   5.000   0.9464   0.01406   0.00677  -0.0662   0.4718   1.0000
   5.250   0.9655   0.01417   0.00698  -0.0648   0.4661   1.0000
   5.500   0.9849   0.01427   0.00712  -0.0634   0.4606   1.0000
   5.750   1.0044   0.01440   0.00728  -0.0621   0.4558   1.0000
   6.000   1.0226   0.01452   0.00753  -0.0605   0.4498   1.0000
   6.250   1.0408   0.01465   0.00772  -0.0589   0.4438   1.0000
   6.500   1.0587   0.01479   0.00791  -0.0572   0.4381   1.0000
   6.750   1.0750   0.01491   0.00814  -0.0553   0.4300   1.0000
   7.000   1.0912   0.01506   0.00828  -0.0532   0.4228   1.0000
   7.250   1.1055   0.01520   0.00853  -0.0509   0.4130   1.0000
   7.500   1.1192   0.01538   0.00873  -0.0484   0.4039   1.0000
   7.750   1.1328   0.01556   0.00903  -0.0460   0.3952   1.0000
   8.000   1.1455   0.01576   0.00930  -0.0434   0.3869   1.0000
   8.250   1.1560   0.01595   0.00958  -0.0403   0.3757   1.0000
   8.500   1.1645   0.01616   0.00983  -0.0369   0.3636   1.0000
   8.750   1.1704   0.01640   0.01009  -0.0331   0.3510   1.0000
   9.000   1.1740   0.01670   0.01038  -0.0289   0.3364   1.0000
   9.250   1.1811   0.01704   0.01078  -0.0256   0.3167   1.0000
   9.500   1.1860   0.01752   0.01121  -0.0221   0.2971   1.0000
   9.750   1.1885   0.01824   0.01184  -0.0185   0.2761   1.0000
  10.000   1.1926   0.01914   0.01267  -0.0156   0.2415   1.0000
  10.250   1.1930   0.02036   0.01379  -0.0127   0.2197   1.0000
  10.500   1.1935   0.02178   0.01514  -0.0103   0.1857   1.0000
  10.750   1.1908   0.02358   0.01687  -0.0082   0.1670   1.0000
  11.000   1.1888   0.02558   0.01881  -0.0066   0.1385   1.0000
  11.250   1.1815   0.02819   0.02133  -0.0053   0.1275   1.0000
  11.500   1.1862   0.03007   0.02334  -0.0047   0.1053   1.0000
  11.750   1.1772   0.03320   0.02635  -0.0040   0.0949   1.0000
  12.000   1.1666   0.03665   0.02977  -0.0036   0.0884   1.0000
  12.250   1.1612   0.03977   0.03300  -0.0033   0.0785   1.0000
  12.500   1.1602   0.04255   0.03578  -0.0033   0.0642   1.0000
  12.750   1.1486   0.04645   0.03965  -0.0033   0.0594   1.0000
  13.000   1.1343   0.05069   0.04388  -0.0035   0.0561   1.0000
  13.250   1.1257   0.05438   0.04761  -0.0035   0.0532   1.0000
  13.500   1.1240   0.05743   0.05075  -0.0035   0.0499   1.0000
  13.750   1.1244   0.06007   0.05333  -0.0032   0.0474   1.0000
  14.000   1.1318   0.06212   0.05547  -0.0029   0.0452   1.0000
  14.250   1.1398   0.06430   0.05779  -0.0031   0.0431   1.0000
  14.500   1.1468   0.06659   0.06016  -0.0034   0.0408   1.0000
  14.750   1.1531   0.06890   0.06242  -0.0038   0.0388   1.0000
  15.000   1.1594   0.07150   0.06523  -0.0045   0.0370   1.0000
  15.250   1.1648   0.07420   0.06807  -0.0053   0.0352   1.0000
  15.500   1.1704   0.07686   0.07082  -0.0061   0.0337   1.0000
  15.750   1.1751   0.07965   0.07366  -0.0069   0.0322   1.0000
  16.000   1.1862   0.08129   0.07534  -0.0064   0.0305   1.0000
  16.250   1.1911   0.08418   0.07843  -0.0071   0.0295   1.0000
  16.500   1.1937   0.08744   0.08187  -0.0080   0.0281   1.0000
  16.750   1.1934   0.09118   0.08577  -0.0095   0.0265   1.0000
  17.000   1.1934   0.09489   0.08958  -0.0110   0.0251   1.0000
  17.250   1.1931   0.09851   0.09327  -0.0120   0.0235   1.0000
  17.500   1.1872   0.10325   0.09825  -0.0134   0.0222   1.0000
  17.750   1.1812   0.10829   0.10351  -0.0159   0.0213   1.0000
  18.000   1.1753   0.11338   0.10881  -0.0182   0.0206   1.0000
  18.250   1.1682   0.11875   0.11439  -0.0208   0.0200   1.0000
  18.500   1.1598   0.12445   0.12028  -0.0238   0.0194   1.0000
  18.750   1.1504   0.13047   0.12649  -0.0272   0.0190   1.0000
  19.000   1.1385   0.13719   0.13341  -0.0311   0.0188   1.0000
  19.250   1.1244   0.14457   0.14099  -0.0357   0.0187   1.0000
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