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S2050 8.93% (s2050-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S2050 8.93% (s2050-il)
Reynolds number: 500,000
Max Cl/Cd: 80.88 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2050-il-500000.txt
Download as CSV file: xf-s2050-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2050 8.93%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5540   0.08338   0.08111  -0.0251   1.0000   0.0241
  -9.250  -0.5561   0.07934   0.07710  -0.0271   1.0000   0.0246
  -9.000  -0.7402   0.03712   0.03375  -0.0465   1.0000   0.0123
  -8.750  -0.7393   0.03347   0.02977  -0.0452   1.0000   0.0123
  -8.500  -0.7303   0.03071   0.02667  -0.0439   1.0000   0.0122
  -8.250  -0.7201   0.02769   0.02330  -0.0427   1.0000   0.0122
  -8.000  -0.7041   0.02566   0.02100  -0.0416   1.0000   0.0121
  -7.750  -0.6860   0.02393   0.01903  -0.0405   1.0000   0.0120
  -7.500  -0.6678   0.02187   0.01671  -0.0395   1.0000   0.0119
  -7.250  -0.6485   0.01979   0.01436  -0.0385   1.0000   0.0119
  -7.000  -0.6291   0.01746   0.01176  -0.0375   1.0000   0.0121
  -6.750  -0.6082   0.01570   0.00982  -0.0367   1.0000   0.0125
  -6.500  -0.5857   0.01463   0.00868  -0.0360   1.0000   0.0132
  -6.250  -0.5623   0.01389   0.00788  -0.0354   1.0000   0.0139
  -6.000  -0.5384   0.01323   0.00715  -0.0348   1.0000   0.0149
  -5.750  -0.5142   0.01264   0.00647  -0.0342   1.0000   0.0159
  -5.500  -0.4898   0.01185   0.00560  -0.0338   1.0000   0.0175
  -5.250  -0.4651   0.01140   0.00515  -0.0333   1.0000   0.0206
  -5.000  -0.4398   0.01080   0.00454  -0.0330   1.0000   0.0288
  -4.750  -0.4146   0.01029   0.00412  -0.0327   1.0000   0.0468
  -4.500  -0.3896   0.01004   0.00389  -0.0323   1.0000   0.0589
  -4.250  -0.3634   0.00982   0.00371  -0.0322   0.9997   0.0719
  -4.000  -0.3250   0.00961   0.00354  -0.0346   0.9969   0.0897
  -3.750  -0.2861   0.00935   0.00338  -0.0372   0.9943   0.1145
  -3.500  -0.2491   0.00903   0.00317  -0.0393   0.9906   0.1428
  -3.250  -0.2108   0.00869   0.00298  -0.0418   0.9870   0.1818
  -3.000  -0.1712   0.00830   0.00282  -0.0446   0.9843   0.2406
  -2.750  -0.1363   0.00782   0.00262  -0.0463   0.9795   0.3177
  -2.500  -0.0996   0.00722   0.00244  -0.0486   0.9751   0.4333
  -2.250  -0.0611   0.00664   0.00236  -0.0511   0.9718   0.5680
  -2.000  -0.0279   0.00641   0.00230  -0.0521   0.9645   0.6367
  -1.750   0.0105   0.00627   0.00222  -0.0541   0.9594   0.6717
  -1.500   0.0444   0.00614   0.00213  -0.0551   0.9510   0.6936
  -1.250   0.0818   0.00602   0.00201  -0.0568   0.9440   0.7131
  -1.000   0.1155   0.00592   0.00192  -0.0578   0.9318   0.7282
  -0.750   0.1511   0.00582   0.00184  -0.0591   0.9180   0.7433
  -0.500   0.1861   0.00577   0.00175  -0.0603   0.8997   0.7564
  -0.250   0.2175   0.00575   0.00170  -0.0606   0.8752   0.7673
   0.000   0.2461   0.00580   0.00167  -0.0604   0.8477   0.7771
   0.250   0.2733   0.00589   0.00167  -0.0600   0.8197   0.7875
   0.500   0.2994   0.00600   0.00169  -0.0593   0.7923   0.7986
   0.750   0.3251   0.00610   0.00173  -0.0585   0.7661   0.8089
   1.000   0.3509   0.00622   0.00177  -0.0578   0.7405   0.8186
   1.250   0.3769   0.00634   0.00181  -0.0572   0.7146   0.8289
   1.500   0.4023   0.00643   0.00186  -0.0565   0.6885   0.8380
   1.750   0.4280   0.00655   0.00191  -0.0558   0.6612   0.8470
   2.000   0.4535   0.00668   0.00198  -0.0552   0.6318   0.8560
   2.250   0.4785   0.00681   0.00204  -0.0544   0.6009   0.8646
   2.500   0.5036   0.00697   0.00211  -0.0538   0.5689   0.8746
   3.000   0.5520   0.00730   0.00231  -0.0520   0.5048   0.8962
   3.250   0.5756   0.00748   0.00241  -0.0510   0.4710   0.9087
   3.500   0.5978   0.00768   0.00252  -0.0497   0.4340   0.9237
   3.750   0.6194   0.00787   0.00262  -0.0483   0.3968   0.9443
   4.000   0.6471   0.00808   0.00274  -0.0483   0.3620   0.9734
   4.250   0.6786   0.00839   0.00292  -0.0493   0.3249   1.0000
   4.500   0.7055   0.00879   0.00314  -0.0494   0.2828   1.0000
   4.750   0.7317   0.00924   0.00340  -0.0494   0.2390   1.0000
   5.000   0.7573   0.00973   0.00368  -0.0493   0.1955   1.0000
   5.250   0.7830   0.01020   0.00399  -0.0491   0.1613   1.0000
   5.500   0.8086   0.01066   0.00432  -0.0489   0.1315   1.0000
   5.750   0.8339   0.01114   0.00469  -0.0486   0.1043   1.0000
   6.000   0.8588   0.01167   0.00510  -0.0482   0.0790   1.0000
   6.250   0.8831   0.01228   0.00557  -0.0478   0.0541   1.0000
   6.500   0.9062   0.01310   0.00626  -0.0471   0.0333   1.0000
   6.750   0.9291   0.01395   0.00711  -0.0463   0.0259   1.0000
   7.000   0.9538   0.01447   0.00772  -0.0457   0.0239   1.0000
   7.250   0.9777   0.01509   0.00840  -0.0451   0.0222   1.0000
   7.500   1.0002   0.01587   0.00922  -0.0443   0.0205   1.0000
   7.750   1.0187   0.01723   0.01069  -0.0429   0.0190   1.0000
   8.000   1.0418   0.01792   0.01146  -0.0421   0.0184   1.0000
   8.250   1.0634   0.01881   0.01247  -0.0412   0.0177   1.0000
   8.500   1.0844   0.01980   0.01356  -0.0402   0.0171   1.0000
   8.750   1.1050   0.02086   0.01472  -0.0392   0.0165   1.0000
   9.000   1.1250   0.02200   0.01596  -0.0381   0.0160   1.0000
   9.250   1.1449   0.02309   0.01713  -0.0371   0.0154   1.0000
   9.500   1.1632   0.02441   0.01852  -0.0360   0.0147   1.0000
   9.750   1.1752   0.02741   0.02175  -0.0343   0.0140   1.0000
  10.000   1.1891   0.02976   0.02435  -0.0327   0.0137   1.0000
  10.250   1.2043   0.03132   0.02612  -0.0312   0.0135   1.0000
  10.500   1.2170   0.03311   0.02815  -0.0296   0.0132   1.0000
  10.750   1.2255   0.03539   0.03068  -0.0276   0.0130   1.0000
  11.000   1.2298   0.03787   0.03343  -0.0253   0.0128   1.0000
  11.250   1.2285   0.04035   0.03617  -0.0224   0.0126   1.0000
  11.500   1.2204   0.04288   0.03893  -0.0190   0.0125   1.0000
  11.750   1.2100   0.04557   0.04184  -0.0161   0.0123   1.0000
  12.000   1.1975   0.04867   0.04515  -0.0143   0.0122   1.0000
  12.250   1.1824   0.05243   0.04912  -0.0137   0.0121   1.0000
  12.500   1.1673   0.05672   0.05359  -0.0144   0.0120   1.0000
  12.750   1.1482   0.06225   0.05932  -0.0167   0.0120   1.0000
  13.000   1.1238   0.06957   0.06686  -0.0209   0.0121   1.0000
  13.250   1.0958   0.07875   0.07624  -0.0271   0.0124   1.0000
  13.500   1.0645   0.08993   0.08760  -0.0351   0.0128   1.0000
  13.750   1.0350   0.10203   0.09985  -0.0437   0.0130   1.0000
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