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S2048 (s2048-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S2048 (s2048-il)
Reynolds number: 50,000
Max Cl/Cd: 37.45 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2048-il-50000-n5.txt
Download as CSV file: xf-s2048-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4719   0.12355   0.11623  -0.0228   1.0000   0.1030
 -10.250  -0.4791   0.12074   0.11352  -0.0257   1.0000   0.1040
 -10.000  -0.4804   0.11723   0.11007  -0.0275   1.0000   0.1042
  -9.750  -0.4810   0.11356   0.10648  -0.0291   1.0000   0.1042
  -9.250  -0.4755   0.09820   0.09113  -0.0356   1.0000   0.0505
  -9.000  -0.4770   0.09413   0.08713  -0.0371   1.0000   0.0504
  -8.750  -0.4787   0.09018   0.08325  -0.0383   1.0000   0.0502
  -8.500  -0.4838   0.08599   0.07915  -0.0399   1.0000   0.0501
  -8.250  -0.4894   0.08209   0.07533  -0.0411   1.0000   0.0498
  -8.000  -0.4952   0.07796   0.07125  -0.0426   1.0000   0.0495
  -7.750  -0.4994   0.07410   0.06740  -0.0433   1.0000   0.0491
  -7.500  -0.5040   0.07006   0.06334  -0.0441   1.0000   0.0488
  -7.250  -0.5072   0.06604   0.05926  -0.0446   1.0000   0.0485
  -7.000  -0.5081   0.06205   0.05516  -0.0448   1.0000   0.0480
  -6.750  -0.5069   0.05803   0.05097  -0.0448   1.0000   0.0475
  -6.500  -0.5030   0.05397   0.04667  -0.0447   1.0000   0.0471
  -6.250  -0.4959   0.04997   0.04235  -0.0445   1.0000   0.0468
  -6.000  -0.4856   0.04615   0.03813  -0.0441   1.0000   0.0467
  -5.750  -0.4722   0.04258   0.03412  -0.0436   1.0000   0.0468
  -5.500  -0.4560   0.03927   0.03033  -0.0429   1.0000   0.0472
  -5.250  -0.4373   0.03633   0.02683  -0.0421   1.0000   0.0486
  -5.000  -0.4173   0.03386   0.02377  -0.0414   1.0000   0.0516
  -4.750  -0.3978   0.03200   0.02178  -0.0407   1.0000   0.0553
  -4.500  -0.3757   0.02999   0.01941  -0.0397   1.0000   0.0571
  -4.250  -0.3530   0.02821   0.01732  -0.0385   1.0000   0.0592
  -4.000  -0.3303   0.02670   0.01550  -0.0372   1.0000   0.0618
  -3.750  -0.3085   0.02540   0.01403  -0.0357   1.0000   0.0648
  -3.500  -0.2874   0.02428   0.01285  -0.0345   1.0000   0.0699
  -3.250  -0.2655   0.02333   0.01173  -0.0335   1.0000   0.0806
  -3.000  -0.2434   0.02240   0.01078  -0.0328   1.0000   0.0999
  -2.750  -0.2198   0.02116   0.00972  -0.0327   1.0000   0.1447
  -2.500  -0.1991   0.01867   0.00920  -0.0327   1.0000   0.4526
  -2.250  -0.1888   0.01821   0.00941  -0.0280   1.0000   0.6694
  -2.000  -0.1784   0.01806   0.00940  -0.0234   1.0000   0.7667
  -1.750  -0.1664   0.01786   0.00930  -0.0189   1.0000   0.8570
  -1.500  -0.1213   0.01757   0.00879  -0.0219   1.0000   1.0000
  -1.250  -0.1005   0.01760   0.00851  -0.0218   1.0000   1.0000
  -1.000  -0.0786   0.01771   0.00832  -0.0218   1.0000   1.0000
  -0.750  -0.0564   0.01787   0.00822  -0.0217   1.0000   1.0000
  -0.500  -0.0271   0.01815   0.00822  -0.0230   0.9967   1.0000
  -0.250   0.0103   0.01854   0.00837  -0.0258   0.9893   1.0000
   0.000   0.0492   0.01899   0.00862  -0.0288   0.9822   1.0000
   0.250   0.0853   0.01935   0.00883  -0.0312   0.9734   1.0000
   0.500   0.1222   0.01973   0.00906  -0.0337   0.9647   1.0000
   0.750   0.1621   0.02015   0.00938  -0.0366   0.9562   1.0000
   1.000   0.1972   0.02045   0.00961  -0.0386   0.9454   1.0000
   1.250   0.2336   0.02074   0.00986  -0.0408   0.9341   1.0000
   1.500   0.2710   0.02100   0.01011  -0.0430   0.9222   1.0000
   1.750   0.3092   0.02118   0.01031  -0.0451   0.9092   1.0000
   2.000   0.3477   0.02129   0.01047  -0.0472   0.8948   1.0000
   2.250   0.3872   0.02131   0.01056  -0.0492   0.8794   1.0000
   2.500   0.4277   0.02123   0.01061  -0.0512   0.8638   1.0000
   2.750   0.4687   0.02107   0.01057  -0.0530   0.8479   1.0000
   3.000   0.5038   0.02091   0.01055  -0.0537   0.8300   1.0000
   3.250   0.5371   0.02075   0.01053  -0.0539   0.8103   1.0000
   3.500   0.5734   0.02049   0.01048  -0.0544   0.7906   1.0000
   3.750   0.6033   0.02035   0.01050  -0.0539   0.7661   1.0000
   4.000   0.6336   0.02019   0.01051  -0.0533   0.7387   1.0000
   4.250   0.6637   0.02004   0.01050  -0.0526   0.7067   1.0000
   4.500   0.6922   0.01996   0.01061  -0.0517   0.6673   1.0000
   4.750   0.7197   0.01997   0.01067  -0.0505   0.6192   1.0000
   5.000   0.7467   0.02012   0.01074  -0.0491   0.5616   1.0000
   5.250   0.7707   0.02058   0.01096  -0.0475   0.4995   1.0000
   5.500   0.7909   0.02134   0.01145  -0.0457   0.4392   1.0000
   5.750   0.8094   0.02225   0.01211  -0.0440   0.3852   1.0000
   6.000   0.8273   0.02323   0.01299  -0.0424   0.3367   1.0000
   6.250   0.8447   0.02425   0.01387  -0.0409   0.2919   1.0000
   6.500   0.8620   0.02532   0.01484  -0.0394   0.2489   1.0000
   6.750   0.8792   0.02650   0.01594  -0.0380   0.2060   1.0000
   7.000   0.8959   0.02782   0.01714  -0.0367   0.1648   1.0000
   7.250   0.9144   0.02936   0.01861  -0.0355   0.1343   1.0000
   7.500   0.9321   0.03092   0.02009  -0.0343   0.1108   1.0000
   7.750   0.9523   0.03271   0.02195  -0.0332   0.0958   1.0000
   8.000   0.9715   0.03454   0.02397  -0.0321   0.0825   1.0000
   8.250   0.9913   0.03666   0.02617  -0.0311   0.0727   1.0000
   8.500   1.0108   0.03889   0.02858  -0.0301   0.0642   1.0000
   8.750   1.0279   0.04135   0.03139  -0.0288   0.0559   1.0000
   9.000   1.0448   0.04413   0.03427  -0.0278   0.0511   1.0000
   9.250   1.0564   0.04728   0.03796  -0.0261   0.0462   1.0000
   9.500   1.0644   0.04985   0.04082  -0.0244   0.0418   1.0000
   9.750   1.0721   0.05303   0.04415  -0.0229   0.0395   1.0000
  10.000   1.0728   0.05702   0.04854  -0.0209   0.0384   1.0000
  10.250   1.0656   0.06089   0.05290  -0.0185   0.0376   1.0000
  10.500   1.0525   0.06464   0.05701  -0.0160   0.0371   1.0000
  10.750   1.0362   0.06866   0.06134  -0.0143   0.0368   1.0000
  11.000   1.0186   0.07304   0.06597  -0.0138   0.0368   1.0000
  11.250   0.9985   0.07808   0.07123  -0.0146   0.0368   1.0000
  11.500   0.9790   0.08380   0.07711  -0.0167   0.0372   1.0000
  11.750   0.9594   0.09028   0.08373  -0.0202   0.0376   1.0000
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