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S8036 (16%) (s8036-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S8036 (16%) (s8036-il)
Reynolds number: 50,000
Max Cl/Cd: 26.64 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s8036-il-50000.txt
Download as CSV file: xf-s8036-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8036 (16%)                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3433   0.11608   0.10888  -0.0263   1.0000   0.3212
 -10.250  -0.5547   0.08229   0.07539  -0.0592   1.0000   0.1318
 -10.000  -0.5675   0.07801   0.07112  -0.0584   1.0000   0.1296
  -9.750  -0.5827   0.07421   0.06736  -0.0567   1.0000   0.1276
  -9.500  -0.6116   0.07114   0.06433  -0.0531   1.0000   0.1256
  -9.250  -0.6456   0.06817   0.06135  -0.0483   1.0000   0.1235
  -9.000  -0.7229   0.06590   0.05860  -0.0387   1.0000   0.1161
  -8.750  -0.7397   0.06348   0.05607  -0.0340   1.0000   0.1159
  -8.500  -0.7536   0.06107   0.05354  -0.0295   1.0000   0.1155
  -8.250  -0.7652   0.05873   0.05103  -0.0251   1.0000   0.1152
  -8.000  -0.7778   0.05637   0.04841  -0.0205   1.0000   0.1152
  -7.750  -0.7843   0.05396   0.04575  -0.0166   1.0000   0.1152
  -7.500  -0.7887   0.05152   0.04296  -0.0127   1.0000   0.1154
  -7.250  -0.7894   0.04913   0.04019  -0.0091   1.0000   0.1158
  -7.000  -0.7862   0.04659   0.03737  -0.0061   1.0000   0.1176
  -6.750  -0.7745   0.04467   0.03553  -0.0043   1.0000   0.1222
  -6.500  -0.7661   0.04282   0.03337  -0.0016   1.0000   0.1263
  -6.250  -0.7569   0.04099   0.03104   0.0012   1.0000   0.1303
  -6.000  -0.7418   0.03909   0.02918   0.0028   1.0000   0.1373
  -5.750  -0.7283   0.03763   0.02734   0.0051   1.0000   0.1458
  -5.500  -0.7108   0.03600   0.02581   0.0065   1.0000   0.1579
  -5.250  -0.6931   0.03456   0.02440   0.0080   1.0000   0.1726
  -5.000  -0.6759   0.03325   0.02306   0.0097   1.0000   0.1936
  -4.750  -0.6592   0.03183   0.02199   0.0114   1.0000   0.2230
  -4.500  -0.6466   0.03035   0.02092   0.0138   1.0000   0.2672
  -4.250  -0.6401   0.02843   0.01991   0.0171   1.0000   0.3541
  -4.000  -0.6461   0.02735   0.02056   0.0250   1.0000   0.5556
  -3.750  -0.6481   0.02819   0.02160   0.0331   1.0000   0.6647
  -3.500  -0.6401   0.02933   0.02278   0.0396   1.0000   0.7263
  -3.250  -0.6270   0.03040   0.02377   0.0449   1.0000   0.7756
  -3.000  -0.6025   0.03180   0.02502   0.0484   1.0000   0.8214
  -2.750  -0.5171   0.03543   0.02824   0.0428   1.0000   0.8713
  -2.500  -0.3011   0.04106   0.03296   0.0130   0.9927   0.9234
  -2.250  -0.1979   0.04201   0.03350  -0.0023   0.9853   0.9496
  -2.000  -0.1197   0.04230   0.03350  -0.0140   0.9776   0.9701
  -1.750  -0.0380   0.04231   0.03324  -0.0269   0.9706   0.9873
  -1.500   0.0273   0.04213   0.03286  -0.0369   0.9629   1.0000
  -1.250   0.0469   0.04204   0.03268  -0.0385   0.9540   1.0000
  -1.000   0.0744   0.04209   0.03261  -0.0413   0.9458   1.0000
  -0.750   0.0837   0.04209   0.03255  -0.0407   0.9366   1.0000
  -0.500   0.1035   0.04225   0.03263  -0.0419   0.9283   1.0000
  -0.250   0.1160   0.04240   0.03272  -0.0418   0.9192   1.0000
   0.000   0.1283   0.04265   0.03291  -0.0415   0.9109   1.0000
   0.250   0.1401   0.04289   0.03310  -0.0411   0.9021   1.0000
   0.500   0.1472   0.04320   0.03336  -0.0399   0.8936   1.0000
   0.750   0.1564   0.04351   0.03362  -0.0389   0.8850   1.0000
   1.000   0.1594   0.04386   0.03392  -0.0369   0.8767   1.0000
   1.250   0.1641   0.04418   0.03420  -0.0351   0.8679   1.0000
   1.500   0.1643   0.04455   0.03453  -0.0326   0.8598   1.0000
   1.750   0.1617   0.04484   0.03477  -0.0294   0.8513   1.0000
   2.000   0.1649   0.04531   0.03517  -0.0271   0.8427   1.0000
   2.250   0.1646   0.04577   0.03556  -0.0241   0.8340   1.0000
   2.500   0.1745   0.04648   0.03619  -0.0226   0.8242   1.0000
   2.750   0.1950   0.04731   0.03695  -0.0226   0.8137   1.0000
   3.000   0.1968   0.04811   0.03768  -0.0199   0.8033   1.0000
   3.250   0.2240   0.04913   0.03865  -0.0207   0.7914   1.0000
   3.500   0.2405   0.05004   0.03952  -0.0199   0.7793   1.0000
   3.750   0.2474   0.05106   0.04050  -0.0180   0.7676   1.0000
   4.000   0.2706   0.05210   0.04152  -0.0180   0.7542   1.0000
   4.250   0.3030   0.05310   0.04252  -0.0190   0.7402   1.0000
   4.500   0.3199   0.05408   0.04349  -0.0182   0.7261   1.0000
   4.750   0.3301   0.05514   0.04454  -0.0165   0.7114   1.0000
   5.000   0.3459   0.05622   0.04563  -0.0155   0.6964   1.0000
   5.250   0.3661   0.05721   0.04663  -0.0149   0.6806   1.0000
   5.500   0.3872   0.05818   0.04762  -0.0143   0.6646   1.0000
   5.750   0.4091   0.05909   0.04856  -0.0137   0.6481   1.0000
   6.000   0.4310   0.05994   0.04945  -0.0130   0.6314   1.0000
   6.250   0.4528   0.06072   0.05028  -0.0122   0.6144   1.0000
   6.500   0.4745   0.06146   0.05108  -0.0112   0.5972   1.0000
   6.750   0.4964   0.06212   0.05179  -0.0102   0.5798   1.0000
   7.000   0.5187   0.06271   0.05244  -0.0092   0.5625   1.0000
   7.250   0.5417   0.06316   0.05295  -0.0081   0.5450   1.0000
   7.500   0.5671   0.06334   0.05322  -0.0069   0.5274   1.0000
   7.750   0.5922   0.06345   0.05342  -0.0056   0.5102   1.0000
   8.000   0.6217   0.06305   0.05311  -0.0042   0.4930   1.0000
   8.250   0.6508   0.06251   0.05268  -0.0027   0.4762   1.0000
   8.500   0.6866   0.06105   0.05134  -0.0009   0.4595   1.0000
   8.750   0.7243   0.05905   0.04948   0.0012   0.4433   1.0000
   9.250   1.0015   0.03991   0.03058  -0.0057   0.3888   1.0000
   9.500   1.0132   0.04056   0.03119  -0.0029   0.3685   1.0000
   9.750   1.0657   0.04000   0.03036  -0.0047   0.3426   1.0000
  10.000   1.0779   0.04121   0.03153  -0.0024   0.3258   1.0000
  10.250   1.0953   0.04249   0.03277  -0.0009   0.3100   1.0000
  10.500   1.1105   0.04389   0.03416   0.0008   0.2956   1.0000
  10.750   1.0885   0.04636   0.03686   0.0065   0.2885   1.0000
  11.000   1.1105   0.04791   0.03837   0.0071   0.2762   1.0000
  11.250   1.0870   0.05058   0.04124   0.0125   0.2708   1.0000
  11.500   1.1068   0.05229   0.04294   0.0132   0.2603   1.0000
  11.750   1.0674   0.05605   0.04693   0.0187   0.2581   1.0000
  12.000   1.0106   0.06194   0.05301   0.0227   0.2580   1.0000
  12.250   0.9109   0.07449   0.06565   0.0229   0.2616   1.0000
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