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S2048 (s2048-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S2048 (s2048-il)
Reynolds number: 100,000
Max Cl/Cd: 52.74 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2048-il-100000-n5.txt
Download as CSV file: xf-s2048-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2048                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3752   0.08999   0.08519  -0.0330   1.0000   0.0326
  -9.250  -0.3799   0.08527   0.08051  -0.0342   1.0000   0.0312
  -9.000  -0.3878   0.07993   0.07524  -0.0359   1.0000   0.0299
  -8.500  -0.4842   0.07726   0.07243  -0.0424   1.0000   0.0270
  -8.250  -0.4941   0.07346   0.06870  -0.0432   1.0000   0.0267
  -8.000  -0.5040   0.06921   0.06447  -0.0446   1.0000   0.0264
  -7.750  -0.5116   0.06523   0.06046  -0.0453   1.0000   0.0261
  -7.500  -0.5186   0.06103   0.05620  -0.0456   1.0000   0.0258
  -7.250  -0.5231   0.05685   0.05190  -0.0455   1.0000   0.0256
  -7.000  -0.5247   0.05268   0.04755  -0.0451   1.0000   0.0254
  -6.750  -0.5231   0.04845   0.04307  -0.0446   1.0000   0.0252
  -6.500  -0.5181   0.04425   0.03854  -0.0439   1.0000   0.0252
  -6.250  -0.5095   0.04016   0.03404  -0.0431   1.0000   0.0253
  -6.000  -0.4972   0.03641   0.02981  -0.0422   1.0000   0.0255
  -5.750  -0.4808   0.03356   0.02634  -0.0412   1.0000   0.0269
  -5.500  -0.4650   0.03063   0.02310  -0.0406   1.0000   0.0287
  -5.250  -0.4458   0.02849   0.02064  -0.0398   1.0000   0.0297
  -5.000  -0.4249   0.02641   0.01820  -0.0389   1.0000   0.0303
  -4.750  -0.4030   0.02464   0.01606  -0.0380   1.0000   0.0312
  -4.500  -0.3806   0.02313   0.01428  -0.0371   1.0000   0.0324
  -4.250  -0.3496   0.02175   0.01266  -0.0378   0.9973   0.0344
  -4.000  -0.3162   0.02090   0.01157  -0.0391   0.9940   0.0384
  -3.750  -0.2857   0.01962   0.01027  -0.0400   0.9903   0.0408
  -3.500  -0.2536   0.01875   0.00932  -0.0411   0.9864   0.0436
  -3.250  -0.2197   0.01805   0.00845  -0.0425   0.9829   0.0484
  -3.000  -0.1889   0.01735   0.00770  -0.0434   0.9781   0.0573
  -2.750  -0.1565   0.01666   0.00709  -0.0447   0.9736   0.0898
  -2.500  -0.1240   0.01559   0.00674  -0.0466   0.9702   0.2310
  -2.250  -0.1018   0.01424   0.00694  -0.0460   0.9652   0.5800
  -2.000  -0.0731   0.01413   0.00694  -0.0458   0.9597   0.6689
  -1.750  -0.0422   0.01411   0.00696  -0.0460   0.9552   0.7295
  -1.500  -0.0184   0.01404   0.00696  -0.0446   0.9480   0.7795
  -1.250   0.0091   0.01398   0.00697  -0.0437   0.9432   0.8372
  -1.000   0.0340   0.01389   0.00691  -0.0423   0.9363   0.8884
  -0.750   0.0741   0.01385   0.00681  -0.0446   0.9321   0.9253
  -0.500   0.1236   0.01382   0.00667  -0.0492   0.9293   0.9580
  -0.250   0.1651   0.01376   0.00651  -0.0524   0.9226   1.0000
   0.000   0.2032   0.01373   0.00637  -0.0548   0.9165   1.0000
   0.250   0.2348   0.01369   0.00625  -0.0558   0.9071   1.0000
   0.500   0.2744   0.01358   0.00608  -0.0581   0.9002   1.0000
   0.750   0.3082   0.01345   0.00590  -0.0591   0.8894   1.0000
   1.000   0.3414   0.01330   0.00571  -0.0599   0.8772   1.0000
   1.250   0.3743   0.01315   0.00554  -0.0606   0.8644   1.0000
   1.500   0.4065   0.01302   0.00540  -0.0611   0.8513   1.0000
   1.750   0.4378   0.01292   0.00530  -0.0615   0.8377   1.0000
   2.000   0.4686   0.01285   0.00524  -0.0617   0.8235   1.0000
   2.250   0.4990   0.01280   0.00522  -0.0619   0.8081   1.0000
   2.500   0.5294   0.01275   0.00519  -0.0620   0.7917   1.0000
   2.750   0.5570   0.01277   0.00524  -0.0616   0.7717   1.0000
   3.000   0.5860   0.01277   0.00529  -0.0614   0.7504   1.0000
   3.250   0.6131   0.01282   0.00536  -0.0608   0.7245   1.0000
   3.500   0.6402   0.01289   0.00543  -0.0603   0.6941   1.0000
   3.750   0.6661   0.01301   0.00552  -0.0594   0.6554   1.0000
   4.000   0.6915   0.01321   0.00562  -0.0585   0.6066   1.0000
   4.250   0.7152   0.01356   0.00580  -0.0573   0.5453   1.0000
   4.500   0.7362   0.01413   0.00604  -0.0557   0.4760   1.0000
   4.750   0.7561   0.01482   0.00641  -0.0542   0.4119   1.0000
   5.000   0.7762   0.01553   0.00687  -0.0529   0.3588   1.0000
   5.250   0.7971   0.01621   0.00736  -0.0518   0.3146   1.0000
   5.500   0.8182   0.01687   0.00790  -0.0508   0.2772   1.0000
   5.750   0.8398   0.01752   0.00853  -0.0499   0.2415   1.0000
   6.000   0.8610   0.01822   0.00913  -0.0489   0.2052   1.0000
   6.250   0.8819   0.01897   0.00979  -0.0480   0.1678   1.0000
   6.500   0.9020   0.01988   0.01053  -0.0470   0.1264   1.0000
   6.750   0.9213   0.02094   0.01145  -0.0458   0.0977   1.0000
   7.000   0.9402   0.02206   0.01254  -0.0446   0.0798   1.0000
   7.250   0.9589   0.02319   0.01369  -0.0433   0.0667   1.0000
   7.500   0.9765   0.02448   0.01512  -0.0418   0.0585   1.0000
   7.750   0.9930   0.02586   0.01650  -0.0404   0.0502   1.0000
   8.000   1.0118   0.02705   0.01790  -0.0391   0.0429   1.0000
   8.250   1.0281   0.02850   0.01946  -0.0376   0.0361   1.0000
   8.500   1.0448   0.02986   0.02096  -0.0363   0.0304   1.0000
   8.750   1.0594   0.03166   0.02291  -0.0347   0.0260   1.0000
   9.000   1.0752   0.03343   0.02492  -0.0331   0.0225   1.0000
   9.250   1.0890   0.03537   0.02703  -0.0315   0.0207   1.0000
   9.500   1.1001   0.03788   0.02969  -0.0298   0.0193   1.0000
   9.750   1.1104   0.04104   0.03323  -0.0280   0.0184   1.0000
  10.000   1.1181   0.04392   0.03653  -0.0259   0.0176   1.0000
  10.250   1.1208   0.04666   0.03967  -0.0234   0.0166   1.0000
  10.500   1.1185   0.04933   0.04266  -0.0207   0.0158   1.0000
  10.750   1.1132   0.05202   0.04563  -0.0181   0.0152   1.0000
  11.000   1.1053   0.05492   0.04879  -0.0159   0.0147   1.0000
  11.250   1.0950   0.05812   0.05224  -0.0144   0.0143   1.0000
  11.500   1.0824   0.06179   0.05615  -0.0136   0.0141   1.0000
  11.750   1.0646   0.06664   0.06126  -0.0140   0.0142   1.0000
  12.000   1.0462   0.07198   0.06683  -0.0157   0.0141   1.0000
  12.250   1.0215   0.07927   0.07436  -0.0194   0.0144   1.0000
  12.500   0.9888   0.08980   0.08515  -0.0264   0.0152   1.0000
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