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S4110 (s4110-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S4110 (s4110-il)
Reynolds number: 50,000
Max Cl/Cd: 40.79 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4110-il-50000-n5.txt
Download as CSV file: xf-s4110-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4110                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3861   0.09744   0.09024  -0.0317   1.0000   0.0567
  -8.250  -0.3880   0.09390   0.08679  -0.0326   1.0000   0.0548
  -7.750  -0.4126   0.08542   0.07859  -0.0383   1.0000   0.0496
  -7.500  -0.4112   0.08218   0.07542  -0.0385   1.0000   0.0492
  -7.250  -0.4110   0.07871   0.07201  -0.0394   1.0000   0.0487
  -7.000  -0.4110   0.07494   0.06830  -0.0408   1.0000   0.0483
  -6.750  -0.4106   0.07097   0.06437  -0.0424   1.0000   0.0479
  -6.500  -0.4093   0.06678   0.06018  -0.0441   1.0000   0.0475
  -6.250  -0.4065   0.06234   0.05568  -0.0460   1.0000   0.0473
  -6.000  -0.4015   0.05754   0.05073  -0.0483   1.0000   0.0475
  -5.750  -0.3930   0.05254   0.04546  -0.0507   1.0000   0.0480
  -5.500  -0.3800   0.04735   0.03980  -0.0532   1.0000   0.0491
  -5.250  -0.3643   0.04327   0.03531  -0.0545   1.0000   0.0506
  -5.000  -0.3477   0.04078   0.03265  -0.0545   1.0000   0.0522
  -4.750  -0.3276   0.03767   0.02916  -0.0551   1.0000   0.0536
  -4.500  -0.3053   0.03469   0.02571  -0.0556   1.0000   0.0556
  -4.250  -0.2810   0.03194   0.02237  -0.0559   1.0000   0.0594
  -4.000  -0.2578   0.03003   0.02011  -0.0559   1.0000   0.0653
  -3.750  -0.2340   0.02843   0.01816  -0.0556   1.0000   0.0724
  -3.500  -0.2110   0.02718   0.01671  -0.0552   1.0000   0.0821
  -3.250  -0.1873   0.02602   0.01534  -0.0548   1.0000   0.0942
  -3.000  -0.1638   0.02503   0.01419  -0.0543   1.0000   0.1076
  -2.750  -0.1410   0.02427   0.01330  -0.0536   1.0000   0.1222
  -2.500  -0.1175   0.02359   0.01250  -0.0531   0.9996   0.1372
  -2.250  -0.0806   0.02298   0.01175  -0.0551   0.9936   0.1593
  -2.000  -0.0442   0.02244   0.01120  -0.0572   0.9870   0.1903
  -1.750  -0.0075   0.02183   0.01081  -0.0594   0.9807   0.2377
  -1.500   0.0282   0.02107   0.01058  -0.0616   0.9739   0.3469
  -1.250   0.0581   0.02019   0.01066  -0.0620   0.9672   0.5695
  -1.000   0.0884   0.01923   0.01051  -0.0609   0.9582   1.0000
  -0.750   0.1238   0.01949   0.01036  -0.0628   0.9489   1.0000
  -0.500   0.1624   0.01978   0.01032  -0.0652   0.9407   1.0000
  -0.250   0.1980   0.02004   0.01032  -0.0670   0.9311   1.0000
   0.000   0.2324   0.02029   0.01035  -0.0685   0.9211   1.0000
   0.250   0.2712   0.02053   0.01040  -0.0708   0.9124   1.0000
   0.500   0.3061   0.02074   0.01048  -0.0723   0.9018   1.0000
   0.750   0.3396   0.02096   0.01057  -0.0735   0.8907   1.0000
   1.000   0.3761   0.02113   0.01066  -0.0751   0.8804   1.0000
   1.250   0.4164   0.02123   0.01070  -0.0772   0.8710   1.0000
   1.500   0.4484   0.02138   0.01081  -0.0778   0.8583   1.0000
   1.750   0.4810   0.02148   0.01089  -0.0784   0.8454   1.0000
   2.000   0.5136   0.02155   0.01096  -0.0790   0.8322   1.0000
   2.250   0.5463   0.02159   0.01102  -0.0793   0.8185   1.0000
   2.500   0.5785   0.02159   0.01105  -0.0795   0.8039   1.0000
   2.750   0.6102   0.02155   0.01105  -0.0795   0.7885   1.0000
   3.000   0.6417   0.02147   0.01104  -0.0794   0.7721   1.0000
   3.250   0.6734   0.02134   0.01096  -0.0791   0.7550   1.0000
   3.500   0.6998   0.02136   0.01104  -0.0781   0.7343   1.0000
   3.750   0.7289   0.02126   0.01103  -0.0773   0.7134   1.0000
   4.000   0.7554   0.02124   0.01106  -0.0762   0.6895   1.0000
   4.250   0.7826   0.02119   0.01105  -0.0750   0.6637   1.0000
   4.500   0.8085   0.02120   0.01109  -0.0737   0.6347   1.0000
   4.750   0.8335   0.02129   0.01122  -0.0723   0.6021   1.0000
   5.000   0.8584   0.02143   0.01131  -0.0709   0.5669   1.0000
   5.250   0.8811   0.02172   0.01155  -0.0693   0.5277   1.0000
   5.500   0.9030   0.02214   0.01186  -0.0677   0.4866   1.0000
   5.750   0.9236   0.02271   0.01228  -0.0660   0.4444   1.0000
   6.000   0.9431   0.02342   0.01288  -0.0644   0.4035   1.0000
   6.250   0.9618   0.02425   0.01355  -0.0628   0.3645   1.0000
   6.500   0.9803   0.02519   0.01437  -0.0613   0.3291   1.0000
   6.750   0.9985   0.02620   0.01528  -0.0599   0.2970   1.0000
   7.000   1.0169   0.02727   0.01631  -0.0585   0.2691   1.0000
   7.250   1.0352   0.02839   0.01737  -0.0573   0.2443   1.0000
   7.500   1.0540   0.02955   0.01851  -0.0561   0.2223   1.0000
   7.750   1.0726   0.03076   0.01970  -0.0549   0.2027   1.0000
   8.000   1.0915   0.03201   0.02102  -0.0538   0.1849   1.0000
   8.250   1.1096   0.03330   0.02240  -0.0526   0.1687   1.0000
   8.500   1.1279   0.03467   0.02385  -0.0515   0.1545   1.0000
   8.750   1.1452   0.03610   0.02536  -0.0503   0.1411   1.0000
   9.000   1.1630   0.03766   0.02704  -0.0491   0.1297   1.0000
   9.250   1.1796   0.03928   0.02872  -0.0480   0.1195   1.0000
   9.500   1.1943   0.04089   0.03042  -0.0466   0.1097   1.0000
   9.750   1.2109   0.04296   0.03285  -0.0454   0.1014   1.0000
  10.000   1.2249   0.04481   0.03472  -0.0441   0.0943   1.0000
  10.250   1.2349   0.04698   0.03727  -0.0425   0.0871   1.0000
  10.500   1.2488   0.04913   0.03939  -0.0413   0.0822   1.0000
  10.750   1.2527   0.05199   0.04279  -0.0392   0.0772   1.0000
  11.000   1.2560   0.05411   0.04507  -0.0372   0.0729   1.0000
  11.250   1.2606   0.05659   0.04762  -0.0356   0.0694   1.0000
  11.500   1.2535   0.06025   0.05177  -0.0334   0.0673   1.0000
  11.750   1.2431   0.06402   0.05591  -0.0316   0.0654   1.0000
  12.000   1.2310   0.06791   0.06009  -0.0305   0.0636   1.0000
  12.250   1.2185   0.07195   0.06436  -0.0301   0.0621   1.0000
  12.500   1.2090   0.07582   0.06837  -0.0302   0.0605   1.0000
  12.750   1.2078   0.07900   0.07153  -0.0302   0.0584   1.0000
  13.000   1.1840   0.08532   0.07813  -0.0323   0.0583   1.0000
  13.250   1.1592   0.09251   0.08554  -0.0355   0.0583   1.0000
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