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S4158 (s4158-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S4158 (s4158-il)
Reynolds number: 100,000
Max Cl/Cd: 55.46 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4158-il-100000-n5.txt
Download as CSV file: xf-s4158-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2641   0.09879   0.09388  -0.0689   0.9506   0.0503
  -9.500  -0.2512   0.09367   0.08869  -0.0700   0.9475   0.0355
  -9.000  -0.2510   0.08296   0.07799  -0.0785   0.9375   0.0284
  -8.750  -0.2446   0.07972   0.07475  -0.0802   0.9338   0.0279
  -8.500  -0.2418   0.07605   0.07109  -0.0827   0.9293   0.0275
  -8.250  -0.2420   0.07235   0.06742  -0.0853   0.9237   0.0272
  -8.000  -0.2474   0.06782   0.06290  -0.0895   0.9181   0.0273
  -7.750  -0.2494   0.06372   0.05876  -0.0927   0.9125   0.0268
  -7.500  -0.2506   0.05894   0.05387  -0.0959   0.9073   0.0268
  -7.250  -0.2507   0.05416   0.04890  -0.0981   0.9030   0.0270
  -7.000  -0.2509   0.05006   0.04455  -0.0988   0.8975   0.0271
  -6.750  -0.2459   0.04635   0.04056  -0.0989   0.8931   0.0271
  -6.500  -0.2375   0.04270   0.03652  -0.0986   0.8897   0.0272
  -6.250  -0.2295   0.03973   0.03317  -0.0975   0.8850   0.0272
  -6.000  -0.2180   0.03682   0.02983  -0.0963   0.8808   0.0271
  -5.750  -0.2020   0.03418   0.02671  -0.0953   0.8775   0.0272
  -5.500  -0.1826   0.03182   0.02387  -0.0943   0.8750   0.0274
  -5.250  -0.1671   0.03012   0.02178  -0.0926   0.8703   0.0277
  -5.000  -0.1464   0.02845   0.01970  -0.0915   0.8667   0.0282
  -4.750  -0.1227   0.02705   0.01799  -0.0907   0.8639   0.0288
  -4.500  -0.0984   0.02570   0.01652  -0.0903   0.8616   0.0301
  -4.250  -0.0788   0.02514   0.01590  -0.0892   0.8574   0.0328
  -4.000  -0.0570   0.02449   0.01507  -0.0881   0.8534   0.0361
  -3.750  -0.0330   0.02358   0.01405  -0.0873   0.8503   0.0386
  -3.500  -0.0084   0.02283   0.01327  -0.0867   0.8478   0.0424
  -3.250   0.0118   0.02238   0.01270  -0.0854   0.8435   0.0483
  -2.750   0.0563   0.02137   0.01179  -0.0836   0.8357   0.0898
  -2.250   0.0988   0.02028   0.01137  -0.0819   0.8277   0.2364
  -2.000   0.1198   0.01967   0.01131  -0.0809   0.8233   0.3860
  -1.750   0.1432   0.01901   0.01124  -0.0798   0.8204   0.5646
  -1.500   0.1697   0.01842   0.01123  -0.0784   0.8183   0.7505
  -1.250   0.2557   0.01808   0.01101  -0.0888   0.8187   0.9533
  -1.000   0.3140   0.01807   0.01077  -0.0952   0.8168   1.0000
  -0.750   0.3287   0.01837   0.01094  -0.0932   0.8096   1.0000
  -0.500   0.3522   0.01841   0.01082  -0.0923   0.8057   1.0000
  -0.250   0.3717   0.01860   0.01089  -0.0909   0.8002   1.0000
   0.000   0.3911   0.01878   0.01096  -0.0895   0.7940   1.0000
   0.250   0.4170   0.01875   0.01082  -0.0888   0.7904   1.0000
   0.500   0.4337   0.01905   0.01104  -0.0871   0.7828   1.0000
   0.750   0.4577   0.01908   0.01098  -0.0862   0.7778   1.0000
   1.000   0.4859   0.01896   0.01078  -0.0858   0.7747   1.0000
   1.250   0.5007   0.01933   0.01112  -0.0838   0.7653   1.0000
   1.500   0.5283   0.01921   0.01094  -0.0834   0.7615   1.0000
   1.750   0.5455   0.01951   0.01122  -0.0817   0.7528   1.0000
   2.000   0.5721   0.01943   0.01111  -0.0811   0.7482   1.0000
   2.250   0.5918   0.01963   0.01131  -0.0798   0.7404   1.0000
   2.500   0.6171   0.01958   0.01125  -0.0791   0.7347   1.0000
   2.750   0.6387   0.01969   0.01137  -0.0779   0.7273   1.0000
   3.000   0.6634   0.01965   0.01135  -0.0771   0.7208   1.0000
   3.250   0.6847   0.01974   0.01148  -0.0759   0.7127   1.0000
   3.500   0.7111   0.01958   0.01134  -0.0753   0.7064   1.0000
   3.750   0.7313   0.01969   0.01149  -0.0739   0.6967   1.0000
   4.000   0.7613   0.01930   0.01116  -0.0736   0.6909   1.0000
   4.250   0.7816   0.01932   0.01123  -0.0722   0.6792   1.0000
   4.500   0.8043   0.01920   0.01116  -0.0709   0.6675   1.0000
   4.750   0.8290   0.01899   0.01101  -0.0699   0.6555   1.0000
   5.000   0.8550   0.01876   0.01085  -0.0691   0.6431   1.0000
   5.250   0.8814   0.01855   0.01069  -0.0683   0.6297   1.0000
   5.500   0.9074   0.01840   0.01058  -0.0675   0.6147   1.0000
   5.750   0.9333   0.01829   0.01051  -0.0667   0.5980   1.0000
   6.000   0.9596   0.01819   0.01046  -0.0659   0.5795   1.0000
   6.250   0.9837   0.01824   0.01052  -0.0649   0.5582   1.0000
   6.500   1.0078   0.01832   0.01058  -0.0639   0.5342   1.0000
   6.750   1.0288   0.01855   0.01074  -0.0625   0.5050   1.0000
   7.000   1.0465   0.01893   0.01105  -0.0606   0.4708   1.0000
   7.250   1.0617   0.01946   0.01143  -0.0585   0.4342   1.0000
   7.500   1.0742   0.02012   0.01194  -0.0562   0.3977   1.0000
   7.750   1.0839   0.02087   0.01255  -0.0535   0.3623   1.0000
   8.000   1.0914   0.02172   0.01326  -0.0506   0.3279   1.0000
   8.250   1.0980   0.02270   0.01408  -0.0478   0.2922   1.0000
   8.750   1.1114   0.02493   0.01604  -0.0428   0.2283   1.0000
   9.000   1.1185   0.02616   0.01714  -0.0406   0.1995   1.0000
   9.250   1.1256   0.02744   0.01831  -0.0386   0.1737   1.0000
   9.500   1.1331   0.02876   0.01955  -0.0366   0.1489   1.0000
   9.750   1.1404   0.03014   0.02087  -0.0348   0.1273   1.0000
  10.000   1.1471   0.03161   0.02228  -0.0329   0.1096   1.0000
  10.250   1.1532   0.03317   0.02381  -0.0311   0.0955   1.0000
  10.500   1.1599   0.03473   0.02538  -0.0294   0.0845   1.0000
  10.750   1.1659   0.03637   0.02706  -0.0278   0.0765   1.0000
  11.000   1.1705   0.03816   0.02885  -0.0261   0.0700   1.0000
  11.250   1.1771   0.03985   0.03065  -0.0247   0.0639   1.0000
  11.500   1.1822   0.04169   0.03255  -0.0233   0.0593   1.0000
  11.750   1.1865   0.04369   0.03461  -0.0218   0.0555   1.0000
  12.000   1.1934   0.04550   0.03657  -0.0206   0.0513   1.0000
  12.250   1.1977   0.04754   0.03871  -0.0195   0.0480   1.0000
  12.500   1.2017   0.04975   0.04097  -0.0184   0.0452   1.0000
  12.750   1.2091   0.05174   0.04317  -0.0174   0.0424   1.0000
  13.000   1.2141   0.05392   0.04549  -0.0165   0.0398   1.0000
  13.250   1.2166   0.05633   0.04796  -0.0158   0.0375   1.0000
  13.500   1.2204   0.05886   0.05057  -0.0150   0.0356   1.0000
  13.750   1.2257   0.06136   0.05334  -0.0143   0.0339   1.0000
  14.000   1.2282   0.06414   0.05633  -0.0138   0.0320   1.0000
  14.250   1.2285   0.06707   0.05942  -0.0136   0.0304   1.0000
  14.500   1.2281   0.07013   0.06259  -0.0136   0.0292   1.0000
  14.750   1.2273   0.07339   0.06591  -0.0137   0.0280   1.0000
  15.000   1.2259   0.07709   0.06985  -0.0138   0.0272   1.0000
  15.250   1.2207   0.08135   0.07441  -0.0143   0.0266   1.0000
  15.500   1.2127   0.08614   0.07949  -0.0153   0.0260   1.0000
  15.750   1.2028   0.09134   0.08496  -0.0167   0.0255   1.0000
  16.000   1.1900   0.09718   0.09105  -0.0188   0.0251   1.0000
  16.250   1.1755   0.10357   0.09770  -0.0216   0.0248   1.0000
  16.500   1.1585   0.11074   0.10511  -0.0252   0.0246   1.0000
  16.750   1.1394   0.11878   0.11338  -0.0296   0.0245   1.0000
  17.000   1.1164   0.12827   0.12309  -0.0352   0.0249   1.0000
  17.250   1.0887   0.13972   0.13472  -0.0425   0.0252   1.0000
  17.500   1.0549   0.15419   0.14933  -0.0517   0.0259   1.0000
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