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S2050 8.93% (s2050-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S2050 8.93% (s2050-il)
Reynolds number: 100,000
Max Cl/Cd: 48.78 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2050-il-100000.txt
Download as CSV file: xf-s2050-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5099   0.10065   0.09556  -0.0162   1.0000   0.1126
  -9.000  -0.5421   0.09710   0.09218  -0.0244   1.0000   0.1162
  -8.750  -0.5337   0.09214   0.08726  -0.0233   1.0000   0.1179
  -8.500  -0.5167   0.08889   0.08398  -0.0206   1.0000   0.1210
  -8.250  -0.5170   0.08543   0.08057  -0.0213   1.0000   0.1243
  -7.750  -0.5631   0.07547   0.07080  -0.0324   1.0000   0.1319
  -7.500  -0.5501   0.07214   0.06751  -0.0300   1.0000   0.1341
  -7.250  -0.5940   0.05017   0.04439  -0.0428   1.0000   0.0615
  -7.000  -0.5854   0.04547   0.03956  -0.0424   1.0000   0.0593
  -6.750  -0.5763   0.04037   0.03403  -0.0421   1.0000   0.0568
  -6.500  -0.5635   0.03527   0.02829  -0.0415   1.0000   0.0550
  -6.250  -0.5457   0.03147   0.02389  -0.0407   1.0000   0.0552
  -6.000  -0.5250   0.02893   0.02092  -0.0399   1.0000   0.0588
  -5.750  -0.5026   0.02638   0.01776  -0.0389   1.0000   0.0634
  -5.500  -0.4803   0.02424   0.01557  -0.0381   1.0000   0.0695
  -5.250  -0.4571   0.02248   0.01364  -0.0373   1.0000   0.0809
  -5.000  -0.4337   0.02113   0.01218  -0.0365   1.0000   0.0982
  -4.750  -0.4101   0.01989   0.01082  -0.0358   1.0000   0.1182
  -4.500  -0.3869   0.01880   0.00983  -0.0351   1.0000   0.1386
  -4.250  -0.3630   0.01775   0.00877  -0.0343   1.0000   0.1609
  -4.000  -0.3393   0.01682   0.00793  -0.0337   1.0000   0.1877
  -3.750  -0.3160   0.01585   0.00722  -0.0330   1.0000   0.2213
  -3.500  -0.2925   0.01489   0.00656  -0.0325   1.0000   0.2732
  -3.250  -0.2697   0.01361   0.00602  -0.0320   1.0000   0.3817
  -3.000  -0.2537   0.01267   0.00624  -0.0292   1.0000   0.6003
  -2.750  -0.2380   0.01278   0.00651  -0.0256   1.0000   0.7025
  -2.500  -0.2233   0.01292   0.00666  -0.0221   1.0000   0.7572
  -2.250  -0.2113   0.01303   0.00678  -0.0179   1.0000   0.7964
  -2.000  -0.2008   0.01308   0.00684  -0.0137   1.0000   0.8316
  -1.750  -0.1922   0.01309   0.00684  -0.0091   1.0000   0.8644
  -1.500  -0.1832   0.01304   0.00678  -0.0048   1.0000   0.8986
  -1.250  -0.1657   0.01297   0.00668  -0.0023   1.0000   0.9368
  -1.000  -0.1107   0.01303   0.00661  -0.0074   1.0000   0.9777
  -0.750  -0.0740   0.01299   0.00647  -0.0107   1.0000   1.0000
  -0.500  -0.0633   0.01298   0.00638  -0.0097   1.0000   1.0000
  -0.250  -0.0432   0.01313   0.00643  -0.0102   1.0000   1.0000
   0.000  -0.0034   0.01354   0.00674  -0.0141   0.9942   1.0000
   0.250   0.0514   0.01396   0.00708  -0.0202   0.9815   1.0000
   0.500   0.1045   0.01424   0.00731  -0.0259   0.9678   1.0000
   0.750   0.1557   0.01439   0.00743  -0.0309   0.9535   1.0000
   1.000   0.2058   0.01442   0.00746  -0.0355   0.9387   1.0000
   1.250   0.2561   0.01434   0.00741  -0.0398   0.9237   1.0000
   1.500   0.3076   0.01414   0.00727  -0.0441   0.9090   1.0000
   1.750   0.3585   0.01384   0.00703  -0.0479   0.8935   1.0000
   2.000   0.4063   0.01349   0.00675  -0.0510   0.8759   1.0000
   2.250   0.4489   0.01319   0.00652  -0.0529   0.8547   1.0000
   2.500   0.4873   0.01297   0.00632  -0.0539   0.8298   1.0000
   2.750   0.5196   0.01289   0.00623  -0.0539   0.8011   1.0000
   3.000   0.5492   0.01291   0.00623  -0.0534   0.7703   1.0000
   3.250   0.5753   0.01304   0.00632  -0.0524   0.7363   1.0000
   3.500   0.6011   0.01321   0.00641  -0.0513   0.7014   1.0000
   3.750   0.6260   0.01343   0.00654  -0.0501   0.6649   1.0000
   4.000   0.6501   0.01368   0.00672  -0.0488   0.6262   1.0000
   4.250   0.6737   0.01397   0.00691  -0.0475   0.5852   1.0000
   4.500   0.6969   0.01433   0.00715  -0.0462   0.5425   1.0000
   4.750   0.7195   0.01475   0.00742  -0.0449   0.4978   1.0000
   5.000   0.7415   0.01524   0.00777  -0.0435   0.4513   1.0000
   5.250   0.7630   0.01581   0.00817  -0.0422   0.4023   1.0000
   5.500   0.7839   0.01647   0.00865  -0.0409   0.3518   1.0000
   5.750   0.8043   0.01726   0.00922  -0.0396   0.3008   1.0000
   6.000   0.8240   0.01821   0.00996  -0.0383   0.2496   1.0000
   6.250   0.8430   0.01933   0.01082  -0.0370   0.1989   1.0000
   6.500   0.8615   0.02059   0.01183  -0.0358   0.1534   1.0000
   6.750   0.8798   0.02211   0.01312  -0.0345   0.1181   1.0000
   7.000   0.8990   0.02397   0.01476  -0.0332   0.0947   1.0000
   7.250   0.9205   0.02577   0.01658  -0.0322   0.0796   1.0000
   7.500   0.9438   0.02754   0.01840  -0.0313   0.0709   1.0000
   7.750   0.9687   0.03016   0.02116  -0.0306   0.0662   1.0000
   8.000   0.9921   0.03236   0.02366  -0.0297   0.0621   1.0000
   8.250   1.0135   0.03451   0.02586  -0.0291   0.0578   1.0000
   8.500   1.0323   0.03820   0.02987  -0.0281   0.0559   1.0000
   8.750   1.0474   0.04138   0.03362  -0.0265   0.0552   1.0000
   9.000   1.0587   0.04511   0.03786  -0.0247   0.0550   1.0000
   9.250   1.0658   0.04932   0.04255  -0.0229   0.0552   1.0000
   9.500   1.0695   0.05397   0.04761  -0.0212   0.0556   1.0000
   9.750   1.0691   0.05877   0.05276  -0.0196   0.0559   1.0000
  10.000   1.0657   0.06377   0.05807  -0.0182   0.0562   1.0000
  10.250   1.0604   0.06864   0.06322  -0.0170   0.0565   1.0000
  10.500   1.0473   0.07177   0.06668  -0.0152   0.0569   1.0000
  10.750   0.8582   0.07520   0.07098  -0.0136   0.0624   1.0000
  11.000   0.8134   0.08643   0.08231  -0.0207   0.0641   1.0000
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