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S1210 12% (s1210-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S1210 12% (s1210-il)
Reynolds number: 200,000
Max Cl/Cd: 87.97 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1210-il-200000-n5.txt
Download as CSV file: xf-s1210-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1210 12%                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.1054   0.10394   0.10042  -0.0664   0.9687   0.0311
  -8.250  -0.0986   0.09996   0.09646  -0.0704   0.9616   0.0314
  -8.000  -0.0893   0.09631   0.09282  -0.0731   0.9546   0.0315
  -7.750  -0.0782   0.09212   0.08865  -0.0768   0.9483   0.0315
  -7.000  -0.0515   0.07969   0.07624  -0.0799   0.9227   0.0213
  -6.750  -0.0440   0.07663   0.07318  -0.0810   0.9113   0.0204
  -6.500  -0.0351   0.07346   0.07002  -0.0828   0.9006   0.0201
  -6.250  -0.0290   0.06886   0.06543  -0.0863   0.8893   0.0203
  -6.000  -0.0209   0.06149   0.05805  -0.0937   0.8753   0.0207
  -5.750  -0.0026   0.05598   0.05252  -0.1006   0.8621   0.0203
  -5.500   0.1441   0.02501   0.01997  -0.1768   0.8560   0.0187
  -5.250   0.2194   0.02117   0.01543  -0.1901   0.8472   0.0190
  -5.000   0.2862   0.01881   0.01260  -0.1994   0.8356   0.0196
  -4.750   0.3508   0.01718   0.01059  -0.2075   0.8201   0.0204
  -4.500   0.4139   0.01605   0.00925  -0.2154   0.8007   0.0222
  -4.000   0.5172   0.01473   0.00749  -0.2258   0.7536   0.0243
  -3.750   0.5593   0.01438   0.00688  -0.2289   0.7301   0.0254
  -3.500   0.5991   0.01406   0.00634  -0.2317   0.7080   0.0270
  -3.250   0.6350   0.01388   0.00593  -0.2335   0.6876   0.0295
  -3.000   0.6702   0.01371   0.00556  -0.2351   0.6694   0.0356
  -2.750   0.7095   0.01332   0.00514  -0.2379   0.6533   0.0743
  -2.500   0.7481   0.01299   0.00508  -0.2407   0.6390   0.2181
  -2.250   0.7763   0.01326   0.00528  -0.2406   0.6265   0.2616
  -2.000   0.8041   0.01356   0.00544  -0.2403   0.6148   0.2866
  -1.750   0.8322   0.01375   0.00554  -0.2402   0.6043   0.2989
  -1.500   0.8610   0.01387   0.00551  -0.2403   0.5947   0.3042
  -1.250   0.8896   0.01396   0.00552  -0.2403   0.5850   0.3086
  -1.000   0.9183   0.01408   0.00553  -0.2403   0.5765   0.3129
  -0.750   0.9471   0.01419   0.00554  -0.2404   0.5682   0.3174
  -0.500   0.9759   0.01431   0.00559  -0.2404   0.5614   0.3220
  -0.250   1.0046   0.01441   0.00566  -0.2405   0.5544   0.3267
   0.000   1.0332   0.01456   0.00573  -0.2405   0.5481   0.3317
   0.250   1.0618   0.01469   0.00582  -0.2406   0.5419   0.3370
   0.500   1.0903   0.01482   0.00594  -0.2406   0.5356   0.3421
   0.750   1.1188   0.01500   0.00606  -0.2406   0.5304   0.3487
   1.000   1.1475   0.01513   0.00621  -0.2407   0.5253   0.3558
   1.250   1.1760   0.01529   0.00638  -0.2408   0.5199   0.3639
   1.500   1.2043   0.01548   0.00654  -0.2408   0.5151   0.3723
   1.750   1.2328   0.01565   0.00674  -0.2409   0.5106   0.3815
   2.000   1.2612   0.01581   0.00694  -0.2409   0.5056   0.3915
   2.500   1.3177   0.01623   0.00738  -0.2409   0.4969   0.4166
   2.750   1.3456   0.01639   0.00763  -0.2409   0.4916   0.4320
   3.000   1.3729   0.01658   0.00788  -0.2407   0.4852   0.4494
   3.250   1.3999   0.01682   0.00812  -0.2405   0.4791   0.4686
   3.500   1.4271   0.01698   0.00839  -0.2403   0.4728   0.4891
   3.750   1.4543   0.01720   0.00867  -0.2401   0.4677   0.5123
   4.000   1.4816   0.01745   0.00897  -0.2400   0.4631   0.5386
   4.250   1.5082   0.01762   0.00930  -0.2397   0.4568   0.5694
   4.500   1.5339   0.01785   0.00959  -0.2392   0.4501   0.6045
   4.750   1.5590   0.01805   0.00992  -0.2386   0.4432   0.6449
   5.000   1.5832   0.01825   0.01023  -0.2377   0.4358   0.6916
   5.250   1.6058   0.01844   0.01054  -0.2366   0.4288   0.7506
   5.500   1.6232   0.01850   0.01079  -0.2342   0.4211   0.8445
   5.750   1.6397   0.01864   0.01098  -0.2318   0.4142   1.0000
   6.000   1.6640   0.01893   0.01133  -0.2311   0.4058   1.0000
   6.250   1.6872   0.01930   0.01168  -0.2302   0.3982   1.0000
   6.500   1.7105   0.01961   0.01208  -0.2293   0.3887   1.0000
   6.750   1.7328   0.01999   0.01248  -0.2282   0.3793   1.0000
   7.000   1.7543   0.02038   0.01290  -0.2270   0.3687   1.0000
   7.250   1.7756   0.02078   0.01336  -0.2258   0.3563   1.0000
   7.500   1.7948   0.02126   0.01385  -0.2242   0.3411   1.0000
   7.750   1.8109   0.02185   0.01441  -0.2220   0.3227   1.0000
   8.000   1.8237   0.02258   0.01508  -0.2193   0.3024   1.0000
   8.250   1.8343   0.02347   0.01590  -0.2163   0.2816   1.0000
   8.500   1.8443   0.02448   0.01684  -0.2132   0.2628   1.0000
   8.750   1.8535   0.02559   0.01790  -0.2101   0.2461   1.0000
   9.000   1.8627   0.02674   0.01903  -0.2072   0.2312   1.0000
   9.250   1.8715   0.02796   0.02023  -0.2042   0.2176   1.0000
   9.500   1.8801   0.02921   0.02151  -0.2013   0.2056   1.0000
   9.750   1.8877   0.03057   0.02290  -0.1984   0.1948   1.0000
  10.000   1.8933   0.03210   0.02444  -0.1954   0.1848   1.0000
  10.250   1.9000   0.03360   0.02599  -0.1926   0.1752   1.0000
  10.500   1.9047   0.03531   0.02775  -0.1898   0.1665   1.0000
  10.750   1.9083   0.03717   0.02965  -0.1870   0.1588   1.0000
  11.000   1.9118   0.03911   0.03168  -0.1844   0.1522   1.0000
  11.250   1.9144   0.04122   0.03386  -0.1820   0.1463   1.0000
  11.500   1.9142   0.04369   0.03640  -0.1795   0.1416   1.0000
  11.750   1.9178   0.04592   0.03875  -0.1776   0.1370   1.0000
  12.000   1.9181   0.04857   0.04150  -0.1757   0.1329   1.0000
  12.250   1.9156   0.05168   0.04468  -0.1739   0.1293   1.0000
  12.500   1.9161   0.05457   0.04770  -0.1725   0.1262   1.0000
  12.750   1.9173   0.05752   0.05080  -0.1714   0.1229   1.0000
  13.000   1.9160   0.06088   0.05427  -0.1704   0.1195   1.0000
  13.250   1.9126   0.06464   0.05811  -0.1696   0.1168   1.0000
  13.500   1.9088   0.06852   0.06207  -0.1690   0.1144   1.0000
  13.750   1.9104   0.07177   0.06549  -0.1685   0.1122   1.0000
  14.000   1.9108   0.07524   0.06911  -0.1681   0.1095   1.0000
  14.250   1.9095   0.07898   0.07297  -0.1679   0.1071   1.0000
  14.500   1.9059   0.08315   0.07722  -0.1679   0.1042   1.0000
  14.750   1.9006   0.08757   0.08167  -0.1680   0.1016   1.0000
  15.000   1.9021   0.09108   0.08540  -0.1682   0.0984   1.0000
  15.250   1.9011   0.09503   0.08949  -0.1686   0.0951   1.0000
  15.500   1.8964   0.09959   0.09411  -0.1693   0.0915   1.0000
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