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S8038 (13%) (s8038-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S8038 (13%) (s8038-il)
Reynolds number: 100,000
Max Cl/Cd: 45.2 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s8038-il-100000.txt
Download as CSV file: xf-s8038-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8038 (13%)                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4917   0.08638   0.08142  -0.0409   1.0000   0.0749
 -11.000  -0.4919   0.08179   0.07685  -0.0410   1.0000   0.0727
 -10.750  -0.6215   0.07784   0.07261  -0.0463   1.0000   0.0724
 -10.500  -0.6561   0.07065   0.06535  -0.0500   1.0000   0.0701
 -10.250  -0.7008   0.06488   0.05942  -0.0507   1.0000   0.0682
 -10.000  -0.7827   0.06131   0.05521  -0.0435   1.0000   0.0644
  -9.750  -0.7748   0.05694   0.05079  -0.0424   1.0000   0.0626
  -9.500  -0.7798   0.05318   0.04687  -0.0400   1.0000   0.0614
  -9.250  -0.7855   0.04957   0.04300  -0.0370   1.0000   0.0602
  -9.000  -0.7892   0.04607   0.03918  -0.0338   1.0000   0.0590
  -8.750  -0.7897   0.04273   0.03546  -0.0305   1.0000   0.0581
  -8.500  -0.7858   0.03968   0.03200  -0.0274   1.0000   0.0576
  -8.250  -0.7774   0.03703   0.02898  -0.0247   1.0000   0.0575
  -8.000  -0.7653   0.03487   0.02655  -0.0223   1.0000   0.0585
  -7.750  -0.7514   0.03303   0.02445  -0.0201   1.0000   0.0602
  -7.500  -0.7362   0.03134   0.02245  -0.0179   1.0000   0.0622
  -7.250  -0.7192   0.02980   0.02061  -0.0157   1.0000   0.0638
  -7.000  -0.6983   0.02746   0.01832  -0.0146   1.0000   0.0661
  -6.750  -0.6798   0.02606   0.01695  -0.0129   1.0000   0.0692
  -6.500  -0.6622   0.02484   0.01566  -0.0109   1.0000   0.0738
  -6.250  -0.6477   0.02351   0.01444  -0.0087   1.0000   0.0809
  -6.000  -0.6347   0.02238   0.01334  -0.0061   1.0000   0.0912
  -5.750  -0.6248   0.02117   0.01230  -0.0031   1.0000   0.1066
  -5.500  -0.6174   0.01986   0.01128   0.0002   1.0000   0.1406
  -5.250  -0.6116   0.01851   0.01045   0.0034   1.0000   0.2055
  -5.000  -0.6054   0.01743   0.00995   0.0065   1.0000   0.2893
  -4.750  -0.5977   0.01668   0.00970   0.0096   1.0000   0.3767
  -4.500  -0.5883   0.01625   0.00966   0.0126   1.0000   0.4541
  -4.250  -0.5772   0.01613   0.00980   0.0157   1.0000   0.5183
  -4.000  -0.5653   0.01624   0.01005   0.0186   1.0000   0.5711
  -3.750  -0.5527   0.01645   0.01032   0.0215   1.0000   0.6138
  -3.500  -0.5309   0.01680   0.01066   0.0227   0.9970   0.6527
  -3.250  -0.4909   0.01735   0.01118   0.0207   0.9872   0.6903
  -3.000  -0.4526   0.01779   0.01159   0.0191   0.9774   0.7218
  -2.750  -0.4144   0.01814   0.01187   0.0176   0.9678   0.7495
  -2.500  -0.3743   0.01844   0.01214   0.0159   0.9588   0.7731
  -2.250  -0.3408   0.01860   0.01224   0.0154   0.9481   0.7960
  -2.000  -0.3043   0.01875   0.01233   0.0142   0.9385   0.8164
  -1.750  -0.2614   0.01890   0.01242   0.0120   0.9303   0.8347
  -1.500  -0.2256   0.01900   0.01247   0.0110   0.9199   0.8520
  -1.250  -0.1721   0.01913   0.01252   0.0069   0.9139   0.8678
  -1.000  -0.1311   0.01923   0.01256   0.0048   0.9035   0.8823
  -0.750  -0.0692   0.01923   0.01248  -0.0012   0.8986   0.8946
  -0.500  -0.0088   0.01938   0.01257  -0.0070   0.8905   0.9034
  -0.250   0.0585   0.01927   0.01240  -0.0141   0.8847   0.9116
   0.000   0.1286   0.01917   0.01226  -0.0218   0.8774   0.9172
   0.250   0.1856   0.01890   0.01195  -0.0271   0.8683   0.9256
   0.500   0.2492   0.01869   0.01172  -0.0337   0.8568   0.9307
   0.750   0.2961   0.01844   0.01146  -0.0371   0.8436   0.9395
   1.000   0.3505   0.01815   0.01115  -0.0419   0.8294   0.9455
   1.250   0.3904   0.01797   0.01095  -0.0441   0.8133   0.9547
   1.500   0.4370   0.01773   0.01069  -0.0476   0.7959   0.9616
   1.750   0.4744   0.01755   0.01049  -0.0493   0.7772   0.9707
   2.000   0.5176   0.01725   0.01013  -0.0520   0.7572   0.9783
   2.250   0.5571   0.01700   0.00985  -0.0542   0.7361   0.9868
   2.500   0.5965   0.01674   0.00958  -0.0566   0.7140   0.9954
   2.750   0.6270   0.01652   0.00931  -0.0572   0.6937   1.0000
   3.000   0.6420   0.01647   0.00921  -0.0550   0.6747   1.0000
   3.250   0.6555   0.01642   0.00918  -0.0526   0.6544   1.0000
   3.500   0.6695   0.01636   0.00908  -0.0501   0.6340   1.0000
   3.750   0.6842   0.01628   0.00893  -0.0477   0.6139   1.0000
   4.000   0.6960   0.01626   0.00890  -0.0449   0.5912   1.0000
   4.250   0.7086   0.01624   0.00882  -0.0420   0.5683   1.0000
   4.500   0.7197   0.01627   0.00882  -0.0389   0.5432   1.0000
   4.750   0.7313   0.01633   0.00879  -0.0358   0.5166   1.0000
   5.000   0.7426   0.01646   0.00880  -0.0326   0.4869   1.0000
   5.250   0.7539   0.01668   0.00890  -0.0294   0.4534   1.0000
   5.500   0.7652   0.01700   0.00908  -0.0262   0.4166   1.0000
   5.750   0.7764   0.01748   0.00931  -0.0231   0.3786   1.0000
   6.000   0.7877   0.01810   0.00971  -0.0201   0.3403   1.0000
   6.250   0.7997   0.01883   0.01018  -0.0173   0.3069   1.0000
   6.500   0.8128   0.01963   0.01078  -0.0147   0.2783   1.0000
   6.750   0.8277   0.02052   0.01144  -0.0125   0.2556   1.0000
   7.000   0.8440   0.02138   0.01220  -0.0106   0.2358   1.0000
   7.250   0.8614   0.02227   0.01299  -0.0089   0.2192   1.0000
   7.500   0.8798   0.02321   0.01386  -0.0074   0.2052   1.0000
   7.750   0.9003   0.02425   0.01481  -0.0062   0.1939   1.0000
   8.000   0.9218   0.02529   0.01574  -0.0053   0.1835   1.0000
   8.250   0.9405   0.02629   0.01687  -0.0039   0.1739   1.0000
   8.500   0.9637   0.02755   0.01804  -0.0034   0.1659   1.0000
   8.750   0.9824   0.02861   0.01928  -0.0020   0.1586   1.0000
   9.000   1.0061   0.03005   0.02062  -0.0016   0.1518   1.0000
   9.250   1.0217   0.03115   0.02199   0.0002   0.1454   1.0000
   9.500   1.0454   0.03257   0.02330   0.0005   0.1395   1.0000
   9.750   1.0589   0.03407   0.02512   0.0025   0.1345   1.0000
  10.000   1.0744   0.03533   0.02654   0.0041   0.1291   1.0000
  10.250   1.0982   0.03740   0.02848   0.0040   0.1242   1.0000
  10.500   1.1026   0.03896   0.03052   0.0072   0.1206   1.0000
  10.750   1.1133   0.04052   0.03232   0.0092   0.1162   1.0000
  11.000   1.1303   0.04214   0.03396   0.0102   0.1124   1.0000
  11.250   1.1393   0.04497   0.03697   0.0119   0.1097   1.0000
  11.500   1.1321   0.04733   0.03978   0.0157   0.1077   1.0000
  11.750   1.1235   0.04990   0.04271   0.0193   0.1058   1.0000
  12.000   1.1137   0.05234   0.04542   0.0228   0.1039   1.0000
  12.250   1.1049   0.05463   0.04788   0.0260   0.1021   1.0000
  12.500   1.1185   0.05639   0.04963   0.0269   0.0993   1.0000
  12.750   1.1236   0.05982   0.05309   0.0277   0.0974   1.0000
  13.000   1.1009   0.06362   0.05709   0.0305   0.0970   1.0000
  13.250   1.0732   0.06759   0.06130   0.0325   0.0970   1.0000
  13.500   0.6912   0.14456   0.13879  -0.0102   0.1822   1.0000
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