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S1210 12% (s1210-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S1210 12% (s1210-il)
Reynolds number: 100,000
Max Cl/Cd: 66.01 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1210-il-100000-n5.txt
Download as CSV file: xf-s1210-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.0903   0.09671   0.09217  -0.0619   0.9502   0.0644
  -6.750  -0.0796   0.09354   0.08901  -0.0647   0.9400   0.0659
  -6.250  -0.0710   0.08243   0.07791  -0.0724   0.9169   0.0375
  -6.000  -0.0595   0.07910   0.07458  -0.0742   0.9063   0.0360
  -5.750  -0.0586   0.06967   0.06516  -0.0839   0.8908   0.0315
  -5.250  -0.0272   0.06185   0.05734  -0.0910   0.8660   0.0307
  -5.000   0.0007   0.05371   0.04912  -0.1032   0.8560   0.0299
  -4.750   0.1657   0.02996   0.02361  -0.1687   0.8550   0.0299
  -4.500   0.2353   0.02644   0.01929  -0.1800   0.8476   0.0316
  -4.250   0.2874   0.02422   0.01683  -0.1857   0.8398   0.0323
  -4.000   0.3357   0.02265   0.01509  -0.1900   0.8294   0.0334
  -3.750   0.3837   0.02141   0.01370  -0.1940   0.8174   0.0349
  -3.500   0.4355   0.02037   0.01246  -0.1987   0.8045   0.0374
  -3.250   0.4946   0.01935   0.01127  -0.2053   0.7902   0.0429
  -3.000   0.5582   0.01838   0.01001  -0.2130   0.7741   0.0504
  -2.750   0.6331   0.01677   0.00869  -0.2241   0.7573   0.1607
  -2.500   0.6727   0.01719   0.00903  -0.2261   0.7387   0.2745
  -2.250   0.7060   0.01787   0.00957  -0.2267   0.7209   0.3168
  -2.000   0.7409   0.01794   0.00942  -0.2278   0.7045   0.3269
  -1.750   0.7775   0.01795   0.00911  -0.2294   0.6892   0.3365
  -1.500   0.8099   0.01800   0.00901  -0.2301   0.6756   0.3423
  -1.250   0.8434   0.01806   0.00884  -0.2312   0.6633   0.3492
  -1.000   0.8755   0.01811   0.00873  -0.2320   0.6517   0.3548
  -0.750   0.9066   0.01821   0.00871  -0.2325   0.6416   0.3604
  -0.500   0.9381   0.01833   0.00866  -0.2331   0.6317   0.3673
  -0.250   0.9684   0.01845   0.00869  -0.2336   0.6222   0.3728
   0.000   0.9989   0.01860   0.00873  -0.2340   0.6139   0.3788
   0.250   1.0290   0.01876   0.00881  -0.2344   0.6056   0.3867
   0.500   1.0587   0.01893   0.00895  -0.2347   0.5985   0.3938
   0.750   1.0887   0.01914   0.00907  -0.2351   0.5915   0.4030
   1.000   1.1176   0.01933   0.00927  -0.2352   0.5844   0.4106
   1.250   1.1478   0.01956   0.00941  -0.2356   0.5785   0.4207
   1.500   1.1759   0.01977   0.00969  -0.2356   0.5719   0.4312
   1.750   1.2049   0.02001   0.00992  -0.2358   0.5661   0.4435
   2.000   1.2337   0.02027   0.01017  -0.2359   0.5608   0.4575
   2.250   1.2611   0.02053   0.01049  -0.2358   0.5546   0.4727
   2.500   1.2894   0.02080   0.01079  -0.2358   0.5493   0.4895
   2.750   1.3178   0.02108   0.01110  -0.2359   0.5444   0.5091
   3.000   1.3445   0.02137   0.01150  -0.2356   0.5384   0.5321
   3.250   1.3721   0.02165   0.01187  -0.2355   0.5332   0.5584
   3.500   1.3996   0.02194   0.01221  -0.2354   0.5281   0.5891
   3.750   1.4244   0.02222   0.01266  -0.2347   0.5212   0.6241
   4.000   1.4503   0.02246   0.01297  -0.2342   0.5148   0.6674
   4.250   1.4729   0.02269   0.01341  -0.2330   0.5081   0.7198
   4.500   1.4922   0.02284   0.01374  -0.2310   0.5018   0.7954
   4.750   1.5083   0.02285   0.01381  -0.2283   0.4970   1.0000
   5.000   1.5331   0.02329   0.01435  -0.2279   0.4900   1.0000
   5.250   1.5593   0.02367   0.01472  -0.2275   0.4833   1.0000
   5.500   1.5839   0.02408   0.01515  -0.2269   0.4759   1.0000
   5.750   1.6078   0.02445   0.01555  -0.2261   0.4676   1.0000
   6.000   1.6311   0.02485   0.01601  -0.2253   0.4595   1.0000
   6.250   1.6537   0.02523   0.01643  -0.2243   0.4508   1.0000
   6.500   1.6755   0.02565   0.01693  -0.2231   0.4419   1.0000
   6.750   1.6973   0.02604   0.01735  -0.2219   0.4329   1.0000
   7.000   1.7169   0.02651   0.01795  -0.2204   0.4229   1.0000
   7.250   1.7374   0.02695   0.01841  -0.2190   0.4136   1.0000
   7.500   1.7556   0.02746   0.01907  -0.2173   0.4029   1.0000
   7.750   1.7732   0.02799   0.01972  -0.2154   0.3918   1.0000
   8.000   1.7899   0.02855   0.02034  -0.2134   0.3805   1.0000
   8.250   1.8044   0.02916   0.02104  -0.2111   0.3678   1.0000
   8.500   1.8168   0.02986   0.02188  -0.2084   0.3534   1.0000
   8.750   1.8262   0.03064   0.02275  -0.2052   0.3385   1.0000
   9.000   1.8341   0.03154   0.02369  -0.2019   0.3226   1.0000
   9.250   1.8398   0.03262   0.02477  -0.1983   0.3059   1.0000
   9.500   1.8438   0.03391   0.02607  -0.1947   0.2888   1.0000
   9.750   1.8458   0.03545   0.02759  -0.1911   0.2723   1.0000
  10.000   1.8461   0.03723   0.02938  -0.1874   0.2570   1.0000
  10.250   1.8451   0.03924   0.03138  -0.1839   0.2433   1.0000
  10.500   1.8430   0.04147   0.03363  -0.1805   0.2312   1.0000
  10.750   1.8418   0.04378   0.03602  -0.1776   0.2201   1.0000
  11.000   1.8393   0.04634   0.03864  -0.1748   0.2107   1.0000
  11.250   1.8357   0.04915   0.04150  -0.1723   0.2022   1.0000
  11.500   1.8336   0.05199   0.04445  -0.1702   0.1941   1.0000
  11.750   1.8293   0.05519   0.04773  -0.1683   0.1870   1.0000
  12.000   1.8273   0.05831   0.05097  -0.1668   0.1803   1.0000
  12.250   1.8239   0.06171   0.05446  -0.1654   0.1741   1.0000
  12.500   1.8210   0.06517   0.05798  -0.1643   0.1686   1.0000
  12.750   1.8202   0.06853   0.06149  -0.1635   0.1629   1.0000
  13.000   1.8173   0.07217   0.06517  -0.1628   0.1580   1.0000
  13.250   1.8175   0.07552   0.06862  -0.1622   0.1536   1.0000
  13.500   1.8185   0.07881   0.07208  -0.1617   0.1492   1.0000
  13.750   1.8194   0.08213   0.07550  -0.1613   0.1454   1.0000
  14.000   1.8223   0.08507   0.07842  -0.1607   0.1421   1.0000
  14.250   1.8244   0.08837   0.08194  -0.1605   0.1384   1.0000
  14.500   1.8260   0.09172   0.08545  -0.1604   0.1348   1.0000
  14.750   1.8280   0.09494   0.08876  -0.1604   0.1314   1.0000
  15.000   1.8344   0.09736   0.09117  -0.1599   0.1284   1.0000
  15.250   1.8357   0.10087   0.09491  -0.1602   0.1256   1.0000
  15.500   1.8367   0.10440   0.09865  -0.1605   0.1226   1.0000
  15.750   1.8384   0.10776   0.10218  -0.1609   0.1197   1.0000
  16.000   1.8411   0.11087   0.10537  -0.1613   0.1168   1.0000
  16.250   1.8470   0.11344   0.10798  -0.1614   0.1140   1.0000
  16.500   1.8415   0.11820   0.11303  -0.1629   0.1112   1.0000
  16.750   1.8384   0.12250   0.11755  -0.1643   0.1084   1.0000
  17.000   1.8377   0.12633   0.12151  -0.1655   0.1056   1.0000
  17.250   1.8411   0.12925   0.12447  -0.1663   0.1028   1.0000
  17.500   1.8391   0.13336   0.12875  -0.1679   0.1003   1.0000
  17.750   1.8294   0.13913   0.13481  -0.1708   0.0978   1.0000
  18.000   1.8217   0.14454   0.14043  -0.1736   0.0949   1.0000
  18.250   1.8195   0.14876   0.14476  -0.1758   0.0922   1.0000
  18.500   1.8264   0.15088   0.14686  -0.1766   0.0892   1.0000
  18.750   1.8101   0.15842   0.15474  -0.1813   0.0871   1.0000
  19.000   1.7946   0.16590   0.16250  -0.1862   0.0848   1.0000
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