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S6063 7.05% (s6063-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S6063 7.05% (s6063-il)
Reynolds number: 50,000
Max Cl/Cd: 34.67 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s6063-il-50000-n5.txt
Download as CSV file: xf-s6063-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5418   0.10089   0.09403  -0.0033   1.0000   0.0549
  -8.500  -0.5418   0.09595   0.08913  -0.0069   1.0000   0.0481
  -8.250  -0.5386   0.09187   0.08510  -0.0084   1.0000   0.0463
  -8.000  -0.5377   0.08765   0.08096  -0.0108   1.0000   0.0448
  -7.750  -0.5384   0.08307   0.07645  -0.0142   1.0000   0.0434
  -7.500  -0.5365   0.07783   0.07125  -0.0188   1.0000   0.0418
  -7.250  -0.5347   0.07165   0.06504  -0.0242   1.0000   0.0399
  -6.750  -0.5222   0.06025   0.05312  -0.0320   1.0000   0.0365
  -6.500  -0.5122   0.05585   0.04855  -0.0332   1.0000   0.0361
  -6.250  -0.5002   0.05153   0.04398  -0.0342   1.0000   0.0356
  -6.000  -0.4861   0.04732   0.03944  -0.0350   1.0000   0.0353
  -5.750  -0.4697   0.04333   0.03497  -0.0354   1.0000   0.0350
  -5.500  -0.4513   0.03965   0.03084  -0.0354   1.0000   0.0349
  -5.250  -0.4310   0.03625   0.02693  -0.0351   1.0000   0.0349
  -5.000  -0.4092   0.03324   0.02342  -0.0346   1.0000   0.0352
  -4.750  -0.3862   0.03062   0.02031  -0.0338   1.0000   0.0358
  -4.500  -0.3630   0.02832   0.01763  -0.0329   1.0000   0.0377
  -4.250  -0.3410   0.02649   0.01568  -0.0321   1.0000   0.0419
  -4.000  -0.3176   0.02488   0.01382  -0.0310   1.0000   0.0458
  -3.750  -0.2944   0.02338   0.01198  -0.0296   1.0000   0.0491
  -3.500  -0.2719   0.02195   0.01045  -0.0284   1.0000   0.0546
  -3.250  -0.2485   0.02064   0.00904  -0.0275   1.0000   0.0678
  -3.000  -0.2264   0.01885   0.00785  -0.0270   1.0000   0.1504
  -2.750  -0.2106   0.01660   0.00729  -0.0257   1.0000   0.4407
  -2.500  -0.2002   0.01547   0.00716  -0.0208   1.0000   0.6802
  -2.250  -0.1617   0.01494   0.00674  -0.0200   1.0000   0.9081
  -2.000  -0.1075   0.01471   0.00597  -0.0253   1.0000   1.0000
  -1.750  -0.0908   0.01467   0.00562  -0.0238   1.0000   1.0000
  -1.500  -0.0730   0.01468   0.00534  -0.0225   1.0000   1.0000
  -1.250  -0.0544   0.01472   0.00509  -0.0213   1.0000   1.0000
  -1.000  -0.0353   0.01479   0.00494  -0.0202   1.0000   1.0000
  -0.750  -0.0157   0.01489   0.00484  -0.0192   1.0000   1.0000
  -0.500   0.0040   0.01502   0.00480  -0.0183   1.0000   1.0000
  -0.250   0.0238   0.01518   0.00481  -0.0175   1.0000   1.0000
   0.000   0.0438   0.01538   0.00486  -0.0167   1.0000   1.0000
   0.250   0.0685   0.01562   0.00500  -0.0170   0.9971   1.0000
   0.500   0.1131   0.01598   0.00527  -0.0210   0.9834   1.0000
   0.750   0.1570   0.01629   0.00554  -0.0248   0.9688   1.0000
   1.000   0.2006   0.01657   0.00581  -0.0283   0.9536   1.0000
   1.250   0.2445   0.01682   0.00609  -0.0318   0.9379   1.0000
   1.500   0.2880   0.01702   0.00637  -0.0349   0.9216   1.0000
   1.750   0.3294   0.01718   0.00664  -0.0375   0.9041   1.0000
   2.000   0.3665   0.01730   0.00688  -0.0390   0.8845   1.0000
   2.250   0.4011   0.01740   0.00711  -0.0398   0.8632   1.0000
   2.500   0.4328   0.01749   0.00737  -0.0400   0.8402   1.0000
   2.750   0.4635   0.01755   0.00756  -0.0397   0.8164   1.0000
   3.000   0.4916   0.01761   0.00776  -0.0388   0.7901   1.0000
   3.250   0.5177   0.01768   0.00796  -0.0376   0.7611   1.0000
   3.500   0.5426   0.01778   0.00825  -0.0361   0.7287   1.0000
   3.750   0.5673   0.01788   0.00846  -0.0344   0.6941   1.0000
   4.000   0.5911   0.01804   0.00872  -0.0326   0.6551   1.0000
   4.250   0.6144   0.01825   0.00899  -0.0307   0.6121   1.0000
   4.500   0.6368   0.01856   0.00940  -0.0287   0.5637   1.0000
   4.750   0.6584   0.01899   0.00982  -0.0268   0.5087   1.0000
   5.000   0.6782   0.01958   0.01029  -0.0247   0.4355   1.0000
   5.250   0.6903   0.02093   0.01064  -0.0222   0.2767   1.0000
   5.500   0.7041   0.02333   0.01181  -0.0213   0.1098   1.0000
   5.750   0.7228   0.02553   0.01369  -0.0203   0.0655   1.0000
   6.000   0.7428   0.02731   0.01556  -0.0192   0.0545   1.0000
   6.250   0.7622   0.02914   0.01751  -0.0181   0.0493   1.0000
   6.500   0.7841   0.03089   0.01957  -0.0167   0.0461   1.0000
   6.750   0.8067   0.03279   0.02174  -0.0156   0.0430   1.0000
   7.000   0.8282   0.03478   0.02389  -0.0147   0.0394   1.0000
   7.250   0.8488   0.03738   0.02662  -0.0140   0.0368   1.0000
   7.500   0.8704   0.04000   0.02972  -0.0130   0.0355   1.0000
   7.750   0.8894   0.04313   0.03334  -0.0120   0.0350   1.0000
   8.000   0.9048   0.04664   0.03735  -0.0110   0.0346   1.0000
   8.250   0.9162   0.05046   0.04168  -0.0100   0.0344   1.0000
   8.500   0.9232   0.05451   0.04622  -0.0090   0.0344   1.0000
   8.750   0.9255   0.05878   0.05091  -0.0083   0.0344   1.0000
   9.000   0.9230   0.06319   0.05568  -0.0077   0.0346   1.0000
   9.250   0.9158   0.06764   0.06043  -0.0075   0.0347   1.0000
   9.500   0.9036   0.07206   0.06506  -0.0076   0.0349   1.0000
   9.750   0.8874   0.07662   0.06976  -0.0085   0.0351   1.0000
  10.000   0.8709   0.08193   0.07517  -0.0112   0.0354   1.0000
  10.250   0.8555   0.08815   0.08145  -0.0155   0.0357   1.0000
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