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S4053 (s4053-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S4053 (s4053-il)
Reynolds number: 100,000
Max Cl/Cd: 57.79 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4053-il-100000-n5.txt
Download as CSV file: xf-s4053-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4053                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3946   0.09180   0.08701  -0.0362   1.0000   0.0604
  -8.000  -0.4099   0.08928   0.08462  -0.0388   1.0000   0.0610
  -7.750  -0.4182   0.08568   0.08108  -0.0432   1.0000   0.0613
  -6.750  -0.4186   0.06617   0.06157  -0.0444   1.0000   0.0361
  -6.500  -0.4198   0.06386   0.05934  -0.0418   1.0000   0.0346
  -6.250  -0.4222   0.06070   0.05617  -0.0409   1.0000   0.0333
  -6.000  -0.4017   0.05450   0.04975  -0.0464   0.9940   0.0308
  -5.500  -0.3432   0.04060   0.03463  -0.0565   0.9766   0.0258
  -5.250  -0.3133   0.03636   0.02992  -0.0594   0.9701   0.0254
  -5.000  -0.2866   0.03288   0.02596  -0.0608   0.9613   0.0252
  -4.750  -0.2547   0.02972   0.02226  -0.0625   0.9551   0.0251
  -4.500  -0.2250   0.02721   0.01926  -0.0633   0.9472   0.0252
  -4.250  -0.1906   0.02518   0.01672  -0.0648   0.9418   0.0266
  -4.000  -0.1612   0.02330   0.01466  -0.0657   0.9341   0.0289
  -3.750  -0.1253   0.02171   0.01279  -0.0672   0.9297   0.0301
  -3.500  -0.0958   0.02043   0.01133  -0.0673   0.9213   0.0308
  -3.250  -0.0613   0.01923   0.00999  -0.0685   0.9161   0.0319
  -3.000  -0.0326   0.01832   0.00897  -0.0685   0.9074   0.0334
  -2.750   0.0014   0.01751   0.00799  -0.0696   0.9018   0.0355
  -2.500   0.0296   0.01682   0.00719  -0.0696   0.8927   0.0394
  -2.250   0.0625   0.01617   0.00654  -0.0704   0.8864   0.0542
  -2.000   0.0896   0.01518   0.00601  -0.0705   0.8775   0.1543
  -1.750   0.1132   0.01350   0.00593  -0.0702   0.8702   0.5375
  -1.500   0.1664   0.01245   0.00589  -0.0732   0.8672   0.9241
  -1.250   0.2292   0.01232   0.00546  -0.0803   0.8631   1.0000
  -1.000   0.2567   0.01233   0.00525  -0.0803   0.8533   1.0000
  -0.750   0.2864   0.01233   0.00503  -0.0805   0.8451   1.0000
  -0.500   0.3116   0.01240   0.00494  -0.0800   0.8347   1.0000
  -0.250   0.3378   0.01246   0.00485  -0.0796   0.8251   1.0000
   0.000   0.3659   0.01250   0.00474  -0.0795   0.8168   1.0000
   0.250   0.3906   0.01261   0.00474  -0.0788   0.8066   1.0000
   0.500   0.4161   0.01271   0.00474  -0.0783   0.7972   1.0000
   0.750   0.4434   0.01279   0.00471  -0.0780   0.7888   1.0000
   1.000   0.4678   0.01292   0.00478  -0.0772   0.7785   1.0000
   1.250   0.4929   0.01304   0.00484  -0.0766   0.7688   1.0000
   1.500   0.5193   0.01314   0.00487  -0.0761   0.7598   1.0000
   1.750   0.5441   0.01327   0.00496  -0.0754   0.7492   1.0000
   2.000   0.5688   0.01341   0.00508  -0.0746   0.7383   1.0000
   2.250   0.5939   0.01354   0.00518  -0.0739   0.7276   1.0000
   2.500   0.6195   0.01366   0.00527  -0.0732   0.7168   1.0000
   2.750   0.6447   0.01378   0.00538  -0.0725   0.7055   1.0000
   3.000   0.6690   0.01393   0.00556  -0.0717   0.6930   1.0000
   3.250   0.6935   0.01406   0.00571  -0.0708   0.6799   1.0000
   3.500   0.7179   0.01420   0.00586  -0.0700   0.6660   1.0000
   3.750   0.7422   0.01433   0.00601  -0.0690   0.6512   1.0000
   4.000   0.7665   0.01446   0.00620  -0.0681   0.6356   1.0000
   4.250   0.7901   0.01460   0.00638  -0.0671   0.6181   1.0000
   4.500   0.8133   0.01476   0.00658  -0.0660   0.5985   1.0000
   4.750   0.8365   0.01491   0.00674  -0.0648   0.5768   1.0000
   5.000   0.8589   0.01509   0.00692  -0.0636   0.5513   1.0000
   5.250   0.8806   0.01531   0.00718  -0.0622   0.5215   1.0000
   5.500   0.9016   0.01560   0.00742  -0.0607   0.4865   1.0000
   5.750   0.9216   0.01598   0.00770  -0.0591   0.4467   1.0000
   6.000   0.9401   0.01650   0.00806  -0.0574   0.4015   1.0000
   6.250   0.9573   0.01716   0.00852  -0.0555   0.3540   1.0000
   6.500   0.9734   0.01793   0.00914  -0.0536   0.3055   1.0000
   6.750   0.9889   0.01880   0.00980  -0.0518   0.2601   1.0000
   7.000   1.0041   0.01972   0.01054  -0.0500   0.2183   1.0000
   7.250   1.0194   0.02066   0.01135  -0.0482   0.1818   1.0000
   7.500   1.0342   0.02166   0.01221  -0.0465   0.1514   1.0000
   7.750   1.0494   0.02264   0.01314  -0.0447   0.1294   1.0000
   8.000   1.0638   0.02367   0.01415  -0.0429   0.1122   1.0000
   8.250   1.0775   0.02474   0.01525  -0.0410   0.0983   1.0000
   8.500   1.0910   0.02581   0.01635  -0.0391   0.0867   1.0000
   8.750   1.1030   0.02699   0.01757  -0.0370   0.0790   1.0000
   9.000   1.1144   0.02816   0.01880  -0.0349   0.0719   1.0000
   9.250   1.1253   0.02933   0.02008  -0.0327   0.0653   1.0000
   9.500   1.1347   0.03056   0.02137  -0.0305   0.0596   1.0000
   9.750   1.1448   0.03193   0.02286  -0.0283   0.0544   1.0000
  10.000   1.1540   0.03318   0.02420  -0.0264   0.0487   1.0000
  10.250   1.1619   0.03476   0.02593  -0.0244   0.0443   1.0000
  10.500   1.1709   0.03618   0.02754  -0.0226   0.0395   1.0000
  10.750   1.1763   0.03793   0.02935  -0.0207   0.0365   1.0000
  11.000   1.1837   0.04002   0.03162  -0.0190   0.0336   1.0000
  11.250   1.1902   0.04195   0.03379  -0.0174   0.0303   1.0000
  11.500   1.1940   0.04386   0.03582  -0.0160   0.0280   1.0000
  11.750   1.1947   0.04625   0.03827  -0.0147   0.0262   1.0000
  12.000   1.1982   0.04900   0.04128  -0.0134   0.0249   1.0000
  12.250   1.1995   0.05201   0.04461  -0.0122   0.0238   1.0000
  12.500   1.1979   0.05529   0.04818  -0.0112   0.0229   1.0000
  12.750   1.1932   0.05888   0.05205  -0.0106   0.0221   1.0000
  13.000   1.1860   0.06278   0.05622  -0.0104   0.0216   1.0000
  13.250   1.1761   0.06701   0.06071  -0.0108   0.0211   1.0000
  13.500   1.1642   0.07174   0.06568  -0.0117   0.0209   1.0000
  13.750   1.1509   0.07673   0.07088  -0.0132   0.0204   1.0000
  14.000   1.1345   0.08261   0.07700  -0.0155   0.0203   1.0000
  14.250   1.1146   0.08956   0.08419  -0.0188   0.0204   1.0000
  14.500   1.0907   0.09792   0.09279  -0.0235   0.0206   1.0000
  14.750   1.0621   0.10831   0.10341  -0.0299   0.0211   1.0000
  15.000   1.0291   0.12118   0.11646  -0.0383   0.0220   1.0000
  15.250   0.9904   0.13776   0.13312  -0.0486   0.0232   1.0000
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