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S4158 (s4158-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S4158 (s4158-il)
Reynolds number: 50,000
Max Cl/Cd: 35.09 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4158-il-50000.txt
Download as CSV file: xf-s4158-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4158                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.4383   0.10745   0.10177  -0.0167   1.0000   0.2349
  -7.250  -0.4204   0.10301   0.09733  -0.0145   1.0000   0.2455
  -7.000  -0.4577   0.10346   0.09793  -0.0118   1.0000   0.2496
  -6.750  -0.4430   0.09951   0.09396  -0.0096   1.0000   0.2603
  -6.500  -0.4835   0.09976   0.09439  -0.0083   1.0000   0.2649
  -6.250  -0.4716   0.09612   0.09074  -0.0050   1.0000   0.2774
  -6.000  -0.4733   0.09334   0.08801  -0.0026   1.0000   0.2883
  -5.750  -0.4830   0.09108   0.08583  -0.0008   1.0000   0.2998
  -5.500  -0.4903   0.08875   0.08356   0.0010   1.0000   0.3138
  -5.250  -0.4929   0.08627   0.08112   0.0033   1.0000   0.3296
  -5.000  -0.4947   0.08387   0.07877   0.0061   1.0000   0.3503
  -4.750  -0.5013   0.08155   0.07651   0.0083   1.0000   0.3724
  -3.500  -0.3846   0.04862   0.04111  -0.0349   1.0000   0.1430
  -3.250  -0.3571   0.04459   0.03632  -0.0360   1.0000   0.1296
  -3.000  -0.3331   0.04146   0.03273  -0.0361   1.0000   0.1238
  -2.750  -0.3060   0.03880   0.02920  -0.0359   1.0000   0.1187
  -2.500  -0.2817   0.03689   0.02680  -0.0354   1.0000   0.1184
  -2.250  -0.2595   0.03523   0.02500  -0.0348   1.0000   0.1230
  -2.000  -0.2355   0.03410   0.02339  -0.0341   1.0000   0.1315
  -1.750  -0.2121   0.03272   0.02196  -0.0335   1.0000   0.1417
  -1.500  -0.1881   0.03175   0.02082  -0.0328   1.0000   0.1599
  -1.250  -0.1631   0.03070   0.01988  -0.0323   1.0000   0.1959
  -1.000  -0.1338   0.02938   0.01904  -0.0324   1.0000   0.2936
  -0.750  -0.0968   0.02636   0.01830  -0.0323   1.0000   1.0000
  -0.500  -0.0766   0.02687   0.01829  -0.0318   1.0000   1.0000
  -0.250  -0.0569   0.02742   0.01845  -0.0314   1.0000   1.0000
   0.000  -0.0376   0.02801   0.01871  -0.0310   1.0000   1.0000
   0.250  -0.0185   0.02864   0.01903  -0.0307   1.0000   1.0000
   0.500   0.0004   0.02931   0.01944  -0.0303   1.0000   1.0000
   0.750   0.0191   0.03002   0.01992  -0.0300   1.0000   1.0000
   1.000   0.0374   0.03078   0.02048  -0.0298   1.0000   1.0000
   1.250   0.0555   0.03157   0.02108  -0.0295   1.0000   1.0000
   1.500   0.0734   0.03241   0.02177  -0.0293   1.0000   1.0000
   1.750   0.0910   0.03330   0.02252  -0.0291   1.0000   1.0000
   2.000   0.1083   0.03424   0.02332  -0.0290   1.0000   1.0000
   2.250   0.1253   0.03523   0.02421  -0.0289   1.0000   1.0000
   2.500   0.1421   0.03627   0.02515  -0.0288   1.0000   1.0000
   2.750   0.1585   0.03737   0.02617  -0.0288   1.0000   1.0000
   3.000   0.1748   0.03851   0.02726  -0.0288   1.0000   1.0000
   3.250   0.1906   0.03972   0.02840  -0.0288   1.0000   1.0000
   3.500   0.2063   0.04098   0.02962  -0.0289   1.0000   1.0000
   3.750   0.2216   0.04230   0.03092  -0.0291   1.0000   1.0000
   4.000   0.2366   0.04369   0.03229  -0.0293   1.0000   1.0000
   4.250   0.3024   0.04796   0.03655  -0.0391   0.9705   1.0000
   4.500   0.4633   0.05090   0.03955  -0.0569   0.8221   1.0000
   4.750   0.5049   0.05228   0.04100  -0.0594   0.8036   1.0000
   5.000   0.5224   0.05324   0.04202  -0.0587   0.7851   1.0000
   5.250   0.5478   0.05426   0.04312  -0.0590   0.7670   1.0000
   5.500   0.5796   0.05521   0.04416  -0.0599   0.7492   1.0000
   5.750   0.6190   0.05595   0.04505  -0.0613   0.7321   1.0000
   6.000   0.6344   0.05685   0.04604  -0.0603   0.7135   1.0000
   6.250   0.6622   0.05751   0.04682  -0.0604   0.6953   1.0000
   6.500   0.7007   0.05772   0.04720  -0.0611   0.6780   1.0000
   6.750   0.7252   0.05823   0.04785  -0.0605   0.6592   1.0000
   7.000   0.7510   0.05859   0.04841  -0.0599   0.6400   1.0000
   7.250   0.7927   0.05793   0.04798  -0.0599   0.6219   1.0000
   7.500   0.8207   0.05783   0.04808  -0.0588   0.6020   1.0000
   7.750   0.8535   0.05713   0.04765  -0.0577   0.5814   1.0000
   8.000   0.9176   0.05324   0.04417  -0.0568   0.5633   1.0000
   8.250   0.9487   0.05162   0.04280  -0.0544   0.5401   1.0000
   8.500   1.1118   0.03599   0.02794  -0.0542   0.5004   1.0000
   8.750   1.1552   0.03334   0.02518  -0.0517   0.4438   1.0000
   9.000   1.1720   0.03340   0.02487  -0.0481   0.3879   1.0000
   9.250   1.1740   0.03463   0.02581  -0.0439   0.3388   1.0000
   9.500   1.1763   0.03617   0.02696  -0.0400   0.2926   1.0000
   9.750   1.1839   0.03815   0.02856  -0.0370   0.2503   1.0000
  10.000   1.2011   0.04046   0.03055  -0.0354   0.2132   1.0000
  10.250   1.2262   0.04316   0.03311  -0.0349   0.1848   1.0000
  10.500   1.2446   0.04572   0.03572  -0.0337   0.1653   1.0000
  10.750   1.2681   0.04871   0.03880  -0.0332   0.1502   1.0000
  11.000   1.2813   0.05178   0.04212  -0.0317   0.1398   1.0000
  11.250   1.2969   0.05503   0.04550  -0.0306   0.1304   1.0000
  11.500   1.2966   0.05845   0.04937  -0.0279   0.1262   1.0000
  11.750   1.3149   0.06223   0.05321  -0.0274   0.1187   1.0000
  12.000   1.2971   0.06537   0.05679  -0.0233   0.1172   1.0000
  12.250   1.2780   0.06881   0.06059  -0.0199   0.1159   1.0000
  12.500   1.2570   0.07267   0.06476  -0.0172   0.1152   1.0000
  12.750   1.2335   0.07702   0.06939  -0.0151   0.1150   1.0000
  13.000   1.2070   0.08196   0.07454  -0.0139   0.1155   1.0000
  13.250   1.1782   0.08759   0.08038  -0.0137   0.1163   1.0000
  13.500   1.1493   0.09392   0.08688  -0.0145   0.1174   1.0000
  13.750   1.1229   0.10087   0.09396  -0.0163   0.1185   1.0000
  14.000   1.0979   0.10852   0.10169  -0.0189   0.1194   1.0000
  14.250   0.9391   0.14896   0.14177  -0.0477   0.1592   1.0000
  14.500   0.9214   0.16071   0.15345  -0.0544   0.1751   1.0000
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