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S4158 (s4158-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S4158 (s4158-il)
Reynolds number: 50,000
Max Cl/Cd: 32.66 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4158-il-50000-n5.txt
Download as CSV file: xf-s4158-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3642   0.11437   0.10803  -0.0347   1.0000   0.1103
  -9.000  -0.3724   0.11254   0.10627  -0.0333   1.0000   0.1113
  -8.750  -0.3813   0.11063   0.10443  -0.0321   1.0000   0.1118
  -8.500  -0.2892   0.09301   0.08703  -0.0466   0.9812   0.0593
  -8.250  -0.3935   0.09940   0.09319  -0.0422   0.9908   0.0605
  -8.000  -0.3828   0.09574   0.08953  -0.0425   0.9873   0.0577
  -7.750  -0.3806   0.09195   0.08576  -0.0453   0.9828   0.0555
  -7.250  -0.3897   0.07963   0.07332  -0.0593   0.9692   0.0485
  -7.000  -0.3844   0.07609   0.06975  -0.0603   0.9645   0.0479
  -6.750  -0.3755   0.07200   0.06558  -0.0628   0.9601   0.0472
  -6.500  -0.3701   0.06807   0.06153  -0.0644   0.9554   0.0466
  -6.250  -0.3638   0.06406   0.05735  -0.0659   0.9502   0.0459
  -6.000  -0.3511   0.05954   0.05256  -0.0684   0.9460   0.0454
  -5.750  -0.3431   0.05586   0.04860  -0.0687   0.9411   0.0449
  -5.500  -0.3302   0.05214   0.04451  -0.0694   0.9363   0.0447
  -5.250  -0.3103   0.04850   0.04037  -0.0707   0.9326   0.0454
  -5.000  -0.2943   0.04546   0.03678  -0.0703   0.9283   0.0470
  -4.750  -0.2758   0.04285   0.03356  -0.0698   0.9237   0.0482
  -4.500  -0.2513   0.04031   0.03051  -0.0701   0.9202   0.0495
  -4.250  -0.2227   0.03810   0.02797  -0.0710   0.9174   0.0509
  -4.000  -0.2053   0.03660   0.02619  -0.0695   0.9125   0.0524
  -3.750  -0.1798   0.03513   0.02440  -0.0692   0.9085   0.0548
  -3.500  -0.1494   0.03386   0.02276  -0.0696   0.9053   0.0593
  -3.250  -0.1231   0.03285   0.02159  -0.0695   0.9015   0.0661
  -3.000  -0.1008   0.03200   0.02050  -0.0684   0.8967   0.0735
  -2.750  -0.0712   0.03121   0.01958  -0.0688   0.8928   0.0886
  -2.500  -0.0380   0.03039   0.01876  -0.0700   0.8897   0.1168
  -2.250  -0.0195   0.02968   0.01822  -0.0687   0.8841   0.1563
  -2.000   0.0067   0.02861   0.01778  -0.0691   0.8797   0.2671
  -1.750   0.0298   0.02726   0.01784  -0.0681   0.8762   0.5668
  -1.500   0.1117   0.02670   0.01776  -0.0769   0.8762   1.0000
  -1.250   0.1260   0.02702   0.01775  -0.0749   0.8689   1.0000
  -1.000   0.1539   0.02735   0.01773  -0.0753   0.8636   1.0000
  -0.750   0.1758   0.02771   0.01781  -0.0746   0.8574   1.0000
  -0.500   0.1986   0.02807   0.01790  -0.0741   0.8508   1.0000
  -0.250   0.2334   0.02843   0.01800  -0.0755   0.8465   1.0000
   0.000   0.2452   0.02883   0.01823  -0.0731   0.8377   1.0000
   0.250   0.2794   0.02919   0.01838  -0.0744   0.8330   1.0000
   0.500   0.2929   0.02962   0.01866  -0.0723   0.8240   1.0000
   0.750   0.3264   0.02996   0.01885  -0.0735   0.8189   1.0000
   1.000   0.3410   0.03041   0.01919  -0.0715   0.8097   1.0000
   1.250   0.3750   0.03072   0.01938  -0.0727   0.8044   1.0000
   1.750   0.4244   0.03145   0.01995  -0.0720   0.7895   1.0000
   2.000   0.4376   0.03193   0.02038  -0.0699   0.7791   1.0000
   2.250   0.4665   0.03224   0.02064  -0.0701   0.7724   1.0000
   2.500   0.4869   0.03263   0.02101  -0.0691   0.7632   1.0000
   2.750   0.5061   0.03306   0.02142  -0.0680   0.7539   1.0000
   3.000   0.5374   0.03326   0.02162  -0.0684   0.7473   1.0000
   3.250   0.5530   0.03373   0.02210  -0.0668   0.7364   1.0000
   3.500   0.5763   0.03406   0.02245  -0.0661   0.7277   1.0000
   3.750   0.6040   0.03423   0.02268  -0.0660   0.7196   1.0000
   4.000   0.6209   0.03467   0.02316  -0.0645   0.7084   1.0000
   4.250   0.6421   0.03499   0.02353  -0.0635   0.6981   1.0000
   4.500   0.6748   0.03488   0.02351  -0.0638   0.6910   1.0000
   4.750   0.6926   0.03525   0.02398  -0.0624   0.6790   1.0000
   5.000   0.7127   0.03552   0.02433  -0.0612   0.6671   1.0000
   5.250   0.7357   0.03561   0.02452  -0.0602   0.6558   1.0000
   5.500   0.7727   0.03492   0.02397  -0.0603   0.6485   1.0000
   5.750   0.7938   0.03492   0.02413  -0.0589   0.6355   1.0000
   6.000   0.8163   0.03480   0.02414  -0.0576   0.6224   1.0000
   6.250   0.8397   0.03459   0.02407  -0.0562   0.6092   1.0000
   6.500   0.8647   0.03428   0.02391  -0.0549   0.5957   1.0000
   6.750   0.8904   0.03390   0.02374  -0.0537   0.5816   1.0000
   7.000   0.9168   0.03345   0.02346  -0.0524   0.5665   1.0000
   7.250   0.9449   0.03289   0.02307  -0.0512   0.5503   1.0000
   7.500   0.9713   0.03245   0.02278  -0.0498   0.5315   1.0000
   7.750   0.9929   0.03234   0.02284  -0.0481   0.5090   1.0000
   8.000   1.0161   0.03212   0.02272  -0.0465   0.4836   1.0000
   8.250   1.0367   0.03207   0.02271  -0.0445   0.4536   1.0000
   8.500   1.0539   0.03227   0.02285  -0.0423   0.4195   1.0000
   8.750   1.0647   0.03298   0.02348  -0.0399   0.3839   1.0000
   9.000   1.0729   0.03397   0.02439  -0.0374   0.3484   1.0000
   9.250   1.0788   0.03521   0.02551  -0.0350   0.3138   1.0000
   9.500   1.0828   0.03670   0.02688  -0.0327   0.2801   1.0000
   9.750   1.0860   0.03837   0.02841  -0.0306   0.2492   1.0000
  10.000   1.0881   0.04025   0.03015  -0.0286   0.2203   1.0000
  10.250   1.0904   0.04225   0.03205  -0.0268   0.1947   1.0000
  10.500   1.0923   0.04440   0.03407  -0.0251   0.1728   1.0000
  10.750   1.0960   0.04656   0.03621  -0.0237   0.1531   1.0000
  11.000   1.0996   0.04878   0.03843  -0.0223   0.1369   1.0000
  11.250   1.1036   0.05104   0.04068  -0.0211   0.1228   1.0000
  11.500   1.1105   0.05320   0.04288  -0.0199   0.1116   1.0000
  11.750   1.1181   0.05537   0.04509  -0.0188   0.1021   1.0000
  12.000   1.1240   0.05760   0.04730  -0.0178   0.0939   1.0000
  12.250   1.1354   0.05973   0.04968  -0.0168   0.0862   1.0000
  12.500   1.1469   0.06180   0.05173  -0.0159   0.0801   1.0000
  12.750   1.1548   0.06435   0.05461  -0.0151   0.0743   1.0000
  13.000   1.1642   0.06659   0.05688  -0.0144   0.0695   1.0000
  13.250   1.1726   0.06965   0.06029  -0.0136   0.0658   1.0000
  13.500   1.1733   0.07305   0.06400  -0.0132   0.0624   1.0000
  13.750   1.1739   0.07623   0.06733  -0.0129   0.0595   1.0000
  14.000   1.1783   0.07935   0.07048  -0.0126   0.0567   1.0000
  14.250   1.1677   0.08427   0.07580  -0.0131   0.0556   1.0000
  14.500   1.1542   0.08967   0.08155  -0.0141   0.0547   1.0000
  14.750   1.1371   0.09577   0.08796  -0.0159   0.0542   1.0000
  15.000   1.1169   0.10271   0.09517  -0.0187   0.0539   1.0000
  15.250   1.0939   0.11070   0.10340  -0.0226   0.0540   1.0000
  15.500   1.0674   0.12016   0.11305  -0.0278   0.0543   1.0000
  15.750   1.0400   0.13096   0.12399  -0.0343   0.0550   1.0000
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