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J5012 12% (j5012-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: J5012 12% (j5012-il)
Reynolds number: 200,000
Max Cl/Cd: 51.35 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-j5012-il-200000.txt
Download as CSV file: xf-j5012-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: J5012   12%                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.7689   0.08981   0.08568  -0.0392   1.0000   0.0404
 -13.500  -0.7967   0.08110   0.07689  -0.0442   1.0000   0.0400
 -13.250  -0.8225   0.07374   0.06942  -0.0482   1.0000   0.0394
 -13.000  -0.8523   0.06707   0.06259  -0.0516   1.0000   0.0391
 -12.750  -0.8776   0.06180   0.05715  -0.0531   1.0000   0.0387
 -12.500  -0.9027   0.05730   0.05244  -0.0530   1.0000   0.0386
 -12.250  -0.9249   0.05348   0.04841  -0.0516   1.0000   0.0384
 -12.000  -0.9441   0.05032   0.04503  -0.0490   1.0000   0.0383
 -11.750  -0.9608   0.04783   0.04231  -0.0454   1.0000   0.0387
 -11.500  -0.9764   0.04536   0.03960  -0.0408   1.0000   0.0388
 -11.250  -0.9882   0.04320   0.03718  -0.0361   1.0000   0.0392
 -11.000  -0.9936   0.04084   0.03453  -0.0322   1.0000   0.0394
 -10.750  -0.9944   0.03867   0.03207  -0.0286   1.0000   0.0397
 -10.500  -0.9922   0.03679   0.02989  -0.0251   1.0000   0.0401
 -10.250  -0.9863   0.03513   0.02794  -0.0219   1.0000   0.0405
 -10.000  -0.9749   0.03187   0.02446  -0.0202   1.0000   0.0415
  -9.750  -0.9600   0.03031   0.02289  -0.0185   1.0000   0.0429
  -9.500  -0.9462   0.02919   0.02169  -0.0165   1.0000   0.0444
  -9.250  -0.9318   0.02809   0.02047  -0.0144   1.0000   0.0460
  -9.000  -0.9167   0.02693   0.01914  -0.0123   1.0000   0.0477
  -8.750  -0.9009   0.02588   0.01791  -0.0101   1.0000   0.0490
  -8.500  -0.8832   0.02405   0.01603  -0.0086   1.0000   0.0511
  -8.250  -0.8684   0.02310   0.01511  -0.0065   1.0000   0.0537
  -8.000  -0.8537   0.02239   0.01434  -0.0042   1.0000   0.0571
  -7.750  -0.8391   0.02148   0.01334  -0.0019   1.0000   0.0606
  -7.500  -0.8268   0.02050   0.01244   0.0007   1.0000   0.0647
  -7.250  -0.8126   0.01987   0.01173   0.0032   1.0000   0.0697
  -7.000  -0.8016   0.01894   0.01085   0.0061   1.0000   0.0753
  -6.750  -0.7873   0.01845   0.01030   0.0085   1.0000   0.0826
  -6.500  -0.7760   0.01768   0.00962   0.0114   1.0000   0.0910
  -6.250  -0.7632   0.01706   0.00903   0.0140   1.0000   0.1014
  -6.000  -0.7499   0.01648   0.00850   0.0166   1.0000   0.1147
  -5.750  -0.7368   0.01590   0.00802   0.0191   1.0000   0.1322
  -5.500  -0.7235   0.01532   0.00756   0.0215   1.0000   0.1561
  -5.250  -0.7105   0.01473   0.00716   0.0240   1.0000   0.1882
  -5.000  -0.6972   0.01418   0.00681   0.0264   1.0000   0.2292
  -4.750  -0.6839   0.01367   0.00654   0.0288   1.0000   0.2764
  -4.500  -0.6704   0.01322   0.00632   0.0311   1.0000   0.3260
  -4.250  -0.6566   0.01283   0.00616   0.0334   1.0000   0.3771
  -4.000  -0.6424   0.01251   0.00604   0.0357   1.0000   0.4269
  -3.750  -0.6078   0.01231   0.00608   0.0339   0.9948   0.4888
  -3.500  -0.5738   0.01212   0.00612   0.0324   0.9888   0.5443
  -3.250  -0.5369   0.01205   0.00623   0.0305   0.9834   0.5975
  -3.000  -0.5048   0.01192   0.00625   0.0296   0.9763   0.6434
  -2.750  -0.4669   0.01188   0.00637   0.0277   0.9710   0.6863
  -2.500  -0.4347   0.01182   0.00639   0.0270   0.9636   0.7223
  -2.250  -0.3964   0.01181   0.00647   0.0251   0.9580   0.7550
  -2.000  -0.3605   0.01181   0.00653   0.0238   0.9518   0.7847
  -1.750  -0.3231   0.01182   0.00660   0.0223   0.9452   0.8102
  -1.500  -0.2787   0.01185   0.00665   0.0194   0.9412   0.8337
  -1.250  -0.2434   0.01190   0.00674   0.0184   0.9334   0.8527
  -1.000  -0.1977   0.01196   0.00679   0.0153   0.9287   0.8690
  -0.750  -0.1461   0.01200   0.00682   0.0110   0.9259   0.8822
  -0.500  -0.1072   0.01207   0.00689   0.0093   0.9179   0.8952
  -0.250  -0.0505   0.01214   0.00696   0.0040   0.9142   0.9016
   0.000   0.0000   0.01209   0.00689   0.0000   0.9102   0.9101
   0.250   0.0506   0.01215   0.00697  -0.0041   0.9016   0.9143
   0.500   0.1071   0.01207   0.00689  -0.0093   0.8952   0.9179
   0.750   0.1461   0.01200   0.00683  -0.0110   0.8823   0.9259
   1.000   0.1977   0.01196   0.00679  -0.0153   0.8690   0.9287
   1.250   0.2433   0.01190   0.00673  -0.0184   0.8527   0.9334
   1.500   0.2787   0.01184   0.00665  -0.0194   0.8334   0.9412
   1.750   0.3231   0.01182   0.00660  -0.0223   0.8103   0.9452
   2.000   0.3606   0.01181   0.00653  -0.0238   0.7849   0.9517
   2.250   0.3963   0.01181   0.00647  -0.0251   0.7552   0.9580
   2.500   0.4347   0.01182   0.00639  -0.0270   0.7223   0.9637
   2.750   0.4668   0.01188   0.00637  -0.0277   0.6859   0.9710
   3.000   0.5049   0.01192   0.00625  -0.0296   0.6434   0.9764
   3.250   0.5370   0.01205   0.00623  -0.0305   0.5976   0.9834
   3.500   0.5738   0.01212   0.00612  -0.0324   0.5441   0.9888
   3.750   0.6077   0.01230   0.00608  -0.0339   0.4889   0.9948
   4.000   0.6424   0.01251   0.00604  -0.0357   0.4268   1.0000
   4.250   0.6566   0.01283   0.00616  -0.0334   0.3769   1.0000
   4.500   0.6704   0.01321   0.00632  -0.0311   0.3266   1.0000
   4.750   0.6839   0.01367   0.00654  -0.0288   0.2764   1.0000
   5.000   0.6972   0.01418   0.00681  -0.0264   0.2292   1.0000
   5.250   0.7105   0.01473   0.00716  -0.0240   0.1879   1.0000
   5.500   0.7234   0.01533   0.00756  -0.0215   0.1558   1.0000
   5.750   0.7368   0.01590   0.00801  -0.0191   0.1322   1.0000
   6.000   0.7500   0.01647   0.00849  -0.0166   0.1148   1.0000
   6.250   0.7632   0.01705   0.00903  -0.0140   0.1015   1.0000
   6.500   0.7759   0.01768   0.00962  -0.0114   0.0909   1.0000
   6.750   0.7874   0.01843   0.01029  -0.0086   0.0825   1.0000
   7.000   0.8016   0.01894   0.01084  -0.0061   0.0751   1.0000
   7.250   0.8126   0.01987   0.01173  -0.0032   0.0696   1.0000
   7.500   0.8267   0.02051   0.01244  -0.0007   0.0646   1.0000
   7.750   0.8390   0.02150   0.01336   0.0019   0.0605   1.0000
   8.000   0.8535   0.02234   0.01429   0.0043   0.0567   1.0000
   8.250   0.8682   0.02307   0.01508   0.0066   0.0535   1.0000
   8.500   0.8833   0.02405   0.01603   0.0086   0.0512   1.0000
   8.750   0.9008   0.02587   0.01790   0.0101   0.0490   1.0000
   9.000   0.9166   0.02691   0.01913   0.0123   0.0476   1.0000
   9.250   0.9319   0.02813   0.02051   0.0144   0.0460   1.0000
   9.500   0.9464   0.02932   0.02182   0.0165   0.0444   1.0000
   9.750   0.9600   0.03034   0.02290   0.0185   0.0428   1.0000
  10.000   0.9750   0.03191   0.02450   0.0202   0.0415   1.0000
  10.250   0.9863   0.03514   0.02795   0.0219   0.0405   1.0000
  10.500   0.9920   0.03674   0.02984   0.0251   0.0401   1.0000
  10.750   0.9945   0.03874   0.03214   0.0285   0.0398   1.0000
  11.000   0.9934   0.04095   0.03464   0.0322   0.0395   1.0000
  11.250   0.9883   0.04324   0.03722   0.0361   0.0392   1.0000
  11.500   0.9772   0.04556   0.03979   0.0406   0.0390   1.0000
  11.750   0.9623   0.04772   0.04219   0.0452   0.0387   1.0000
  12.000   0.9452   0.05053   0.04522   0.0488   0.0387   1.0000
  12.250   0.9249   0.05366   0.04859   0.0515   0.0386   1.0000
  12.500   0.9025   0.05738   0.05253   0.0530   0.0386   1.0000
  12.750   0.8785   0.06177   0.05711   0.0530   0.0387   1.0000
  13.000   0.8530   0.06699   0.06251   0.0514   0.0389   1.0000
  13.250   0.8257   0.07345   0.06912   0.0484   0.0394   1.0000
  13.500   0.7957   0.08143   0.07723   0.0438   0.0400   1.0000
  13.750   0.7761   0.08902   0.08485   0.0405   0.0406   1.0000
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