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S2062 8% (s2062-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S2062 8% (s2062-il)
Reynolds number: 200,000
Max Cl/Cd: 61.85 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2062-il-200000-n5.txt
Download as CSV file: xf-s2062-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2062 8%                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5245   0.07884   0.07533  -0.0277   1.0000   0.0114
  -8.750  -0.5326   0.07347   0.07003  -0.0307   1.0000   0.0113
  -8.500  -0.5454   0.06761   0.06425  -0.0343   1.0000   0.0112
  -8.250  -0.5572   0.06067   0.05733  -0.0405   1.0000   0.0110
  -8.000  -0.5688   0.05217   0.04869  -0.0451   1.0000   0.0108
  -7.750  -0.5782   0.04551   0.04177  -0.0466   1.0000   0.0106
  -7.500  -0.5827   0.03965   0.03551  -0.0467   1.0000   0.0105
  -7.250  -0.5812   0.03468   0.03005  -0.0458   1.0000   0.0104
  -7.000  -0.5740   0.03049   0.02534  -0.0445   1.0000   0.0104
  -6.750  -0.5620   0.02719   0.02152  -0.0430   1.0000   0.0104
  -6.500  -0.5465   0.02457   0.01846  -0.0416   1.0000   0.0105
  -6.250  -0.5288   0.02247   0.01597  -0.0403   1.0000   0.0106
  -6.000  -0.5097   0.02073   0.01393  -0.0390   1.0000   0.0108
  -5.750  -0.4896   0.01928   0.01218  -0.0378   1.0000   0.0111
  -5.500  -0.4664   0.01804   0.01073  -0.0371   0.9994   0.0114
  -5.250  -0.4347   0.01666   0.00918  -0.0383   0.9964   0.0121
  -5.000  -0.4024   0.01574   0.00815  -0.0397   0.9933   0.0139
  -4.750  -0.3702   0.01507   0.00736  -0.0409   0.9896   0.0162
  -4.500  -0.3371   0.01424   0.00639  -0.0422   0.9861   0.0193
  -4.250  -0.3028   0.01349   0.00561  -0.0437   0.9832   0.0291
  -4.000  -0.2721   0.01293   0.00510  -0.0445   0.9784   0.0517
  -3.750  -0.2393   0.01250   0.00481  -0.0459   0.9742   0.0849
  -3.500  -0.2045   0.01209   0.00451  -0.0476   0.9709   0.1165
  -3.250  -0.1732   0.01173   0.00419  -0.0485   0.9658   0.1461
  -3.000  -0.1404   0.01139   0.00393  -0.0498   0.9610   0.1814
  -2.750  -0.1051   0.01101   0.00370  -0.0516   0.9574   0.2317
  -2.500  -0.0739   0.01064   0.00350  -0.0525   0.9516   0.2867
  -2.250  -0.0418   0.01024   0.00331  -0.0535   0.9460   0.3573
  -2.000  -0.0090   0.00981   0.00316  -0.0547   0.9410   0.4413
  -1.750   0.0190   0.00938   0.00307  -0.0547   0.9332   0.5348
  -1.500   0.0491   0.00895   0.00301  -0.0550   0.9274   0.6400
  -1.250   0.0747   0.00870   0.00302  -0.0540   0.9185   0.7266
  -1.000   0.1023   0.00854   0.00299  -0.0534   0.9105   0.7875
  -0.750   0.1301   0.00841   0.00294  -0.0528   0.9017   0.8329
  -0.500   0.1567   0.00832   0.00288  -0.0519   0.8911   0.8701
  -0.250   0.1864   0.00824   0.00281  -0.0517   0.8809   0.9033
   0.000   0.2209   0.00816   0.00271  -0.0526   0.8706   0.9332
   0.250   0.2590   0.00809   0.00261  -0.0544   0.8586   0.9593
   0.500   0.2986   0.00803   0.00251  -0.0567   0.8447   0.9814
   0.750   0.3365   0.00799   0.00242  -0.0587   0.8285   1.0000
   1.000   0.3609   0.00802   0.00239  -0.0578   0.8099   1.0000
   1.250   0.3859   0.00806   0.00237  -0.0570   0.7903   1.0000
   1.500   0.4108   0.00812   0.00236  -0.0563   0.7687   1.0000
   1.750   0.4360   0.00821   0.00237  -0.0555   0.7452   1.0000
   2.000   0.4611   0.00832   0.00241  -0.0547   0.7187   1.0000
   2.250   0.4859   0.00847   0.00245  -0.0539   0.6892   1.0000
   2.500   0.5106   0.00865   0.00252  -0.0531   0.6564   1.0000
   2.750   0.5348   0.00888   0.00261  -0.0522   0.6203   1.0000
   3.000   0.5589   0.00914   0.00276  -0.0513   0.5808   1.0000
   3.250   0.5826   0.00945   0.00291  -0.0504   0.5390   1.0000
   3.500   0.6061   0.00980   0.00310  -0.0496   0.4961   1.0000
   3.750   0.6295   0.01019   0.00333  -0.0487   0.4520   1.0000
   4.250   0.6732   0.01132   0.00392  -0.0468   0.3235   1.0000
   4.500   0.6951   0.01196   0.00427  -0.0459   0.2602   1.0000
   4.750   0.7178   0.01258   0.00466  -0.0452   0.2074   1.0000
   5.000   0.7391   0.01339   0.00512  -0.0445   0.1406   1.0000
   5.250   0.7612   0.01417   0.00563  -0.0438   0.0911   1.0000
   5.500   0.7833   0.01497   0.00627  -0.0430   0.0517   1.0000
   5.750   0.8055   0.01579   0.00699  -0.0422   0.0306   1.0000
   6.000   0.8285   0.01651   0.00773  -0.0414   0.0248   1.0000
   6.250   0.8514   0.01724   0.00856  -0.0406   0.0226   1.0000
   6.500   0.8740   0.01797   0.00944  -0.0397   0.0214   1.0000
   6.750   0.8960   0.01878   0.01037  -0.0388   0.0203   1.0000
   7.000   0.9177   0.01961   0.01128  -0.0379   0.0189   1.0000
   7.250   0.9383   0.02056   0.01236  -0.0370   0.0174   1.0000
   7.500   0.9569   0.02186   0.01375  -0.0357   0.0167   1.0000
   7.750   0.9748   0.02349   0.01548  -0.0343   0.0161   1.0000
   8.000   0.9951   0.02479   0.01693  -0.0333   0.0158   1.0000
   8.250   1.0152   0.02627   0.01859  -0.0322   0.0155   1.0000
   8.500   1.0349   0.02795   0.02048  -0.0311   0.0152   1.0000
   8.750   1.0537   0.02984   0.02261  -0.0299   0.0149   1.0000
   9.000   1.0712   0.03166   0.02474  -0.0287   0.0142   1.0000
   9.250   1.0872   0.03341   0.02676  -0.0274   0.0134   1.0000
   9.500   1.1008   0.03546   0.02908  -0.0259   0.0128   1.0000
   9.750   1.1112   0.03790   0.03184  -0.0241   0.0124   1.0000
  10.000   1.1179   0.04048   0.03475  -0.0221   0.0121   1.0000
  10.250   1.1206   0.04324   0.03782  -0.0199   0.0119   1.0000
  10.500   1.1180   0.04607   0.04095  -0.0173   0.0117   1.0000
  10.750   1.1093   0.04886   0.04400  -0.0143   0.0116   1.0000
  11.000   1.0970   0.05201   0.04740  -0.0119   0.0115   1.0000
  11.250   1.0824   0.05556   0.05118  -0.0105   0.0114   1.0000
  11.500   1.0650   0.05986   0.05572  -0.0103   0.0114   1.0000
  11.750   1.0461   0.06497   0.06104  -0.0118   0.0114   1.0000
  12.000   1.0253   0.07123   0.06751  -0.0151   0.0114   1.0000
  12.250   0.9981   0.08017   0.07668  -0.0212   0.0117   1.0000
  12.500   0.9623   0.09362   0.09036  -0.0313   0.0121   1.0000
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