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S1210 12% (s1210-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S1210 12% (s1210-il)
Reynolds number: 100,000
Max Cl/Cd: 59.3 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1210-il-100000.txt
Download as CSV file: xf-s1210-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.000  -0.1391   0.09951   0.09554  -0.0491   0.9590   0.1100
  -5.750  -0.1437   0.09788   0.09399  -0.0597   0.9378   0.1135
  -5.500  -0.1030   0.09237   0.08843  -0.0564   0.9365   0.1183
  -5.250  -0.0897   0.09004   0.08612  -0.0714   0.9169   0.1281
  -5.000  -0.0680   0.08539   0.08148  -0.0671   0.9103   0.1307
  -4.750  -0.0323   0.08146   0.07751  -0.0710   0.9052   0.1393
  -4.500  -0.0123   0.07740   0.07347  -0.0772   0.8914   0.1465
  -4.250   0.0107   0.07446   0.07051  -0.0789   0.8794   0.1542
  -4.000   0.2447   0.03335   0.02743  -0.1804   0.8884   0.0723
  -3.750   0.3203   0.02947   0.02275  -0.1914   0.8815   0.0691
  -3.500   0.3888   0.02631   0.01910  -0.1994   0.8780   0.0691
  -3.250   0.4511   0.02377   0.01636  -0.2053   0.8749   0.0713
  -3.000   0.5000   0.02226   0.01491  -0.2090   0.8640   0.0797
  -2.750   0.5706   0.02037   0.01296  -0.2168   0.8596   0.0978
  -2.500   0.6340   0.02020   0.01342  -0.2231   0.8473   0.3114
  -2.250   0.6577   0.02143   0.01489  -0.2196   0.8323   0.3615
  -2.000   0.6910   0.02178   0.01522  -0.2189   0.8177   0.3920
  -1.750   0.7380   0.02139   0.01458  -0.2222   0.8030   0.4088
  -1.500   0.7878   0.02095   0.01383  -0.2266   0.7881   0.4222
  -1.250   0.8301   0.02073   0.01336  -0.2294   0.7735   0.4322
  -1.000   0.8723   0.02052   0.01290  -0.2323   0.7598   0.4407
  -0.750   0.9103   0.02047   0.01262  -0.2345   0.7460   0.4492
  -0.500   0.9447   0.02047   0.01245  -0.2359   0.7327   0.4561
  -0.250   0.9773   0.02056   0.01242  -0.2370   0.7213   0.4629
   0.000   1.0159   0.02062   0.01224  -0.2392   0.7120   0.4718
   0.250   1.0435   0.02082   0.01242  -0.2393   0.7011   0.4790
   0.500   1.0781   0.02099   0.01243  -0.2408   0.6922   0.4877
   0.750   1.1074   0.02121   0.01263  -0.2411   0.6832   0.4966
   1.000   1.1389   0.02148   0.01283  -0.2419   0.6758   0.5074
   1.250   1.1688   0.02177   0.01310  -0.2424   0.6675   0.5198
   1.500   1.2005   0.02204   0.01332  -0.2432   0.6609   0.5324
   1.750   1.2266   0.02241   0.01378  -0.2430   0.6532   0.5457
   2.000   1.2585   0.02270   0.01402  -0.2437   0.6470   0.5638
   2.250   1.2848   0.02315   0.01458  -0.2436   0.6399   0.5838
   2.500   1.3125   0.02349   0.01499  -0.2435   0.6335   0.6055
   2.750   1.3425   0.02385   0.01536  -0.2439   0.6278   0.6338
   3.000   1.3646   0.02432   0.01600  -0.2428   0.6206   0.6640
   3.250   1.3920   0.02455   0.01632  -0.2424   0.6145   0.7043
   3.500   1.4122   0.02495   0.01691  -0.2408   0.6073   0.7534
   3.750   1.4292   0.02505   0.01720  -0.2382   0.6004   0.8270
   4.000   1.4486   0.02508   0.01723  -0.2364   0.5946   1.0000
   4.250   1.4760   0.02580   0.01798  -0.2368   0.5865   1.0000
   4.500   1.5096   0.02620   0.01824  -0.2378   0.5803   1.0000
   4.750   1.5315   0.02697   0.01911  -0.2370   0.5724   1.0000
   5.000   1.5612   0.02735   0.01944  -0.2372   0.5652   1.0000
   5.250   1.5842   0.02799   0.02014  -0.2363   0.5569   1.0000
   5.500   1.6131   0.02825   0.02033  -0.2362   0.5485   1.0000
   5.750   1.6347   0.02884   0.02104  -0.2351   0.5393   1.0000
   6.000   1.6650   0.02897   0.02107  -0.2351   0.5309   1.0000
   6.250   1.6839   0.02957   0.02182  -0.2335   0.5209   1.0000
   6.500   1.7147   0.02963   0.02177  -0.2336   0.5123   1.0000
   6.750   1.7332   0.03010   0.02240  -0.2317   0.5014   1.0000
   7.000   1.7564   0.03042   0.02276  -0.2306   0.4915   1.0000
   7.250   1.7832   0.03049   0.02279  -0.2301   0.4817   1.0000
   7.500   1.8004   0.03096   0.02344  -0.2280   0.4702   1.0000
   7.750   1.8232   0.03117   0.02368  -0.2268   0.4595   1.0000
   8.000   1.8483   0.03117   0.02364  -0.2258   0.4482   1.0000
   8.250   1.8625   0.03159   0.02424  -0.2232   0.4351   1.0000
   8.500   1.8784   0.03194   0.02470  -0.2208   0.4219   1.0000
   8.750   1.8940   0.03225   0.02509  -0.2183   0.4079   1.0000
   9.000   1.9071   0.03260   0.02552  -0.2154   0.3928   1.0000
   9.250   1.9165   0.03306   0.02607  -0.2119   0.3762   1.0000
   9.500   1.9222   0.03367   0.02676  -0.2078   0.3586   1.0000
   9.750   1.9233   0.03446   0.02759  -0.2031   0.3410   1.0000
  10.000   1.9224   0.03547   0.02856  -0.1981   0.3237   1.0000
  10.250   1.9217   0.03678   0.02978  -0.1936   0.3066   1.0000
  10.500   1.9200   0.03850   0.03144  -0.1892   0.2895   1.0000
  10.750   1.9196   0.04043   0.03329  -0.1853   0.2738   1.0000
  11.000   1.9217   0.04247   0.03524  -0.1820   0.2596   1.0000
  11.250   1.9244   0.04459   0.03732  -0.1790   0.2469   1.0000
  11.500   1.9263   0.04686   0.03966  -0.1761   0.2355   1.0000
  11.750   1.9328   0.04904   0.04181  -0.1738   0.2253   1.0000
  12.000   1.9478   0.05083   0.04345  -0.1725   0.2158   1.0000
  12.250   1.9488   0.05336   0.04622  -0.1699   0.2085   1.0000
  12.500   1.9765   0.05472   0.04738  -0.1698   0.2002   1.0000
  12.750   1.9720   0.05756   0.05056  -0.1669   0.1952   1.0000
  13.000   1.9814   0.05965   0.05273  -0.1653   0.1891   1.0000
  13.250   1.9998   0.06159   0.05468  -0.1646   0.1834   1.0000
  13.500   1.9962   0.06460   0.05800  -0.1622   0.1793   1.0000
  13.750   2.0064   0.06678   0.06028  -0.1609   0.1746   1.0000
  14.000   2.0294   0.06855   0.06205  -0.1606   0.1694   1.0000
  14.250   2.0148   0.07241   0.06628  -0.1580   0.1665   1.0000
  14.500   2.0078   0.07591   0.07005  -0.1562   0.1631   1.0000
  14.750   2.0300   0.07718   0.07125  -0.1556   0.1579   1.0000
  15.000   2.0266   0.08079   0.07509  -0.1543   0.1546   1.0000
  15.250   2.0057   0.08568   0.08035  -0.1528   0.1523   1.0000
  15.500   1.9889   0.09050   0.08548  -0.1520   0.1497   1.0000
  15.750   1.9839   0.09403   0.08916  -0.1515   0.1462   1.0000
  16.000   2.0068   0.09518   0.09024  -0.1509   0.1412   1.0000
  16.250   1.9755   0.10180   0.09727  -0.1513   0.1398   1.0000
  16.500   1.9446   0.10906   0.10489  -0.1527   0.1384   1.0000
  16.750   1.9125   0.11701   0.11317  -0.1552   0.1369   1.0000
  17.000   1.8731   0.12676   0.12325  -0.1594   0.1359   1.0000
  17.500   1.8408   0.13956   0.13638  -0.1654   0.1308   1.0000
  17.750   1.8052   0.15029   0.14732  -0.1717   0.1297   1.0000
  18.000   1.7672   0.16251   0.15970  -0.1793   0.1284   1.0000
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