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S6063 7.05% (s6063-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S6063 7.05% (s6063-il)
Reynolds number: 1,000,000
Max Cl/Cd: 68.13 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s6063-il-1000000-n5.txt
Download as CSV file: xf-s6063-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S6063 7.05%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5655   0.08455   0.08297  -0.0042   1.0000   0.0032
  -8.500  -0.5703   0.07882   0.07727  -0.0072   1.0000   0.0036
  -8.250  -0.5770   0.07390   0.07238  -0.0103   1.0000   0.0036
  -8.000  -0.5836   0.06824   0.06675  -0.0162   1.0000   0.0035
  -7.750  -0.5838   0.06060   0.05906  -0.0240   1.0000   0.0035
  -7.500  -0.5800   0.05263   0.05096  -0.0296   1.0000   0.0035
  -7.250  -0.5741   0.04410   0.04222  -0.0333   1.0000   0.0036
  -7.000  -0.5662   0.03578   0.03358  -0.0349   1.0000   0.0037
  -6.750  -0.5557   0.02869   0.02604  -0.0352   1.0000   0.0037
  -6.500  -0.5390   0.02458   0.02153  -0.0349   1.0000   0.0037
  -6.250  -0.5131   0.02237   0.01902  -0.0355   0.9939   0.0038
  -6.000  -0.4832   0.02003   0.01630  -0.0368   0.9851   0.0040
  -5.750  -0.4554   0.01726   0.01314  -0.0377   0.9751   0.0040
  -5.500  -0.4270   0.01600   0.01166  -0.0381   0.9652   0.0040
  -5.250  -0.4005   0.01478   0.01024  -0.0380   0.9545   0.0040
  -5.000  -0.3754   0.01365   0.00890  -0.0374   0.9433   0.0039
  -4.750  -0.3509   0.01248   0.00754  -0.0367   0.9315   0.0039
  -4.500  -0.3265   0.01126   0.00614  -0.0360   0.9199   0.0040
  -4.250  -0.3019   0.01014   0.00486  -0.0353   0.9082   0.0041
  -4.000  -0.2768   0.00928   0.00386  -0.0347   0.8970   0.0043
  -3.750  -0.2507   0.00878   0.00325  -0.0343   0.8860   0.0046
  -3.500  -0.2242   0.00844   0.00284  -0.0340   0.8747   0.0050
  -3.250  -0.1972   0.00815   0.00248  -0.0338   0.8631   0.0055
  -3.000  -0.1702   0.00791   0.00217  -0.0335   0.8510   0.0060
  -2.750  -0.1430   0.00771   0.00188  -0.0333   0.8379   0.0064
  -2.500  -0.1158   0.00757   0.00168  -0.0331   0.8243   0.0070
  -2.250  -0.0884   0.00743   0.00146  -0.0329   0.8103   0.0073
  -2.000  -0.0609   0.00729   0.00121  -0.0327   0.7958   0.0080
  -1.750  -0.0333   0.00719   0.00103  -0.0325   0.7804   0.0104
  -1.500  -0.0060   0.00702   0.00088  -0.0324   0.7637   0.0340
  -1.250   0.0210   0.00673   0.00076  -0.0323   0.7460   0.1013
  -1.000   0.0476   0.00633   0.00066  -0.0323   0.7267   0.2085
  -0.750   0.0741   0.00594   0.00060  -0.0323   0.7069   0.3301
  -0.500   0.1004   0.00554   0.00055  -0.0323   0.6859   0.4684
  -0.250   0.1274   0.00542   0.00053  -0.0322   0.6632   0.5302
   0.000   0.1542   0.00529   0.00053  -0.0320   0.6384   0.6009
   0.250   0.1810   0.00520   0.00054  -0.0318   0.6119   0.6636
   0.500   0.2075   0.00514   0.00056  -0.0316   0.5849   0.7212
   0.750   0.2337   0.00510   0.00060  -0.0312   0.5585   0.7777
   1.000   0.2594   0.00507   0.00065  -0.0306   0.5317   0.8319
   1.250   0.2844   0.00507   0.00071  -0.0299   0.5049   0.8774
   1.500   0.3082   0.00524   0.00079  -0.0290   0.4513   0.9174
   1.750   0.3337   0.00562   0.00088  -0.0285   0.3635   0.9559
   2.000   0.3685   0.00597   0.00098  -0.0303   0.2984   0.9856
   2.250   0.4000   0.00637   0.00111  -0.0314   0.2311   1.0000
   2.500   0.4253   0.00688   0.00129  -0.0311   0.1543   1.0000
   3.000   0.4758   0.00802   0.00182  -0.0306   0.0121   1.0000
   3.250   0.5028   0.00820   0.00198  -0.0305   0.0106   1.0000
   3.500   0.5299   0.00838   0.00217  -0.0303   0.0095   1.0000
   3.750   0.5569   0.00858   0.00240  -0.0302   0.0085   1.0000
   4.000   0.5838   0.00885   0.00272  -0.0299   0.0075   1.0000
   4.250   0.6104   0.00917   0.00309  -0.0297   0.0072   1.0000
   4.500   0.6369   0.00949   0.00346  -0.0295   0.0071   1.0000
   4.750   0.6634   0.00983   0.00383  -0.0293   0.0070   1.0000
   5.000   0.6898   0.01015   0.00418  -0.0291   0.0068   1.0000
   5.250   0.7160   0.01051   0.00458  -0.0288   0.0065   1.0000
   5.500   0.7418   0.01095   0.00507  -0.0285   0.0064   1.0000
   5.750   0.7674   0.01144   0.00564  -0.0282   0.0062   1.0000
   6.000   0.7927   0.01196   0.00622  -0.0278   0.0060   1.0000
   6.250   0.8177   0.01253   0.00685  -0.0274   0.0058   1.0000
   6.500   0.8424   0.01315   0.00754  -0.0270   0.0056   1.0000
   6.750   0.8669   0.01378   0.00823  -0.0266   0.0053   1.0000
   7.000   0.8910   0.01450   0.00903  -0.0261   0.0051   1.0000
   7.250   0.9149   0.01521   0.00981  -0.0256   0.0049   1.0000
   7.500   0.9385   0.01599   0.01069  -0.0251   0.0047   1.0000
   7.750   0.9614   0.01690   0.01168  -0.0245   0.0046   1.0000
   8.000   0.9837   0.01792   0.01280  -0.0238   0.0045   1.0000
   8.250   1.0048   0.01920   0.01420  -0.0231   0.0043   1.0000
   8.500   1.0251   0.02067   0.01583  -0.0222   0.0043   1.0000
   8.750   1.0441   0.02239   0.01774  -0.0213   0.0042   1.0000
   9.000   1.0606   0.02457   0.02015  -0.0201   0.0042   1.0000
   9.250   1.0661   0.02904   0.02505  -0.0181   0.0040   1.0000
   9.500   1.0812   0.03071   0.02695  -0.0171   0.0040   1.0000
   9.750   1.0938   0.03262   0.02909  -0.0158   0.0039   1.0000
  10.000   1.1033   0.03477   0.03146  -0.0144   0.0039   1.0000
  10.250   1.1077   0.03732   0.03425  -0.0127   0.0039   1.0000
  10.500   1.1060   0.04019   0.03736  -0.0108   0.0039   1.0000
  10.750   1.0945   0.04292   0.04028  -0.0077   0.0039   1.0000
  11.000   1.0821   0.04562   0.04315  -0.0057   0.0038   1.0000
  11.250   1.0675   0.04919   0.04689  -0.0054   0.0038   1.0000
  11.500   1.0501   0.05398   0.05184  -0.0072   0.0038   1.0000
  11.750   1.0334   0.05994   0.05795  -0.0111   0.0038   1.0000
  12.000   1.0027   0.07049   0.06867  -0.0193   0.0039   1.0000
  12.250   0.9784   0.08222   0.08054  -0.0282   0.0039   1.0000
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