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S1210 12% (s1210-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S1210 12% (s1210-il)
Reynolds number: 200,000
Max Cl/Cd: 86.32 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1210-il-200000.txt
Download as CSV file: xf-s1210-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.1522   0.10650   0.10334  -0.0472   0.9821   0.0446
  -7.500  -0.1418   0.10289   0.09974  -0.0560   0.9744   0.0470
  -7.250  -0.1336   0.09908   0.09596  -0.0648   0.9649   0.0475
  -7.000  -0.1041   0.09416   0.09103  -0.0628   0.9637   0.0491
  -6.750  -0.0772   0.09084   0.08770  -0.0659   0.9603   0.0512
  -6.500  -0.0614   0.08763   0.08450  -0.0690   0.9516   0.0535
  -6.250  -0.0571   0.08411   0.08101  -0.0761   0.9386   0.0572
  -6.000  -0.0469   0.07849   0.07543  -0.0829   0.9273   0.0587
  -5.750  -0.0209   0.07590   0.07282  -0.0821   0.9233   0.0603
  -5.500   0.0099   0.07271   0.06962  -0.0861   0.9197   0.0658
  -5.000   0.0454   0.06393   0.06087  -0.0969   0.8952   0.0734
  -4.750   0.0786   0.06039   0.05730  -0.1021   0.8904   0.0787
  -4.500   0.2838   0.02417   0.01915  -0.1912   0.8914   0.0449
  -4.250   0.3625   0.01990   0.01396  -0.2029   0.8891   0.0398
  -4.000   0.4117   0.01807   0.01192  -0.2073   0.8782   0.0404
  -3.750   0.4649   0.01663   0.01038  -0.2123   0.8678   0.0431
  -3.500   0.5260   0.01515   0.00878  -0.2187   0.8564   0.0443
  -3.250   0.5922   0.01406   0.00755  -0.2263   0.8388   0.0470
  -3.000   0.6633   0.01311   0.00640  -0.2355   0.8150   0.0557
  -2.750   0.7298   0.01233   0.00587  -0.2441   0.7873   0.2664
  -2.500   0.7639   0.01284   0.00613  -0.2449   0.7606   0.2941
  -2.250   0.7915   0.01347   0.00659  -0.2444   0.7364   0.3217
  -2.000   0.8176   0.01397   0.00700  -0.2435   0.7163   0.3410
  -1.750   0.8469   0.01426   0.00704  -0.2436   0.6986   0.3525
  -1.500   0.8756   0.01434   0.00700  -0.2436   0.6829   0.3578
  -1.250   0.9047   0.01447   0.00698  -0.2437   0.6689   0.3639
  -1.000   0.9354   0.01462   0.00689  -0.2442   0.6567   0.3698
  -0.750   0.9649   0.01472   0.00690  -0.2444   0.6463   0.3747
  -0.500   0.9937   0.01482   0.00693  -0.2446   0.6357   0.3797
  -0.250   1.0245   0.01500   0.00692  -0.2451   0.6269   0.3857
   0.000   1.0530   0.01509   0.00700  -0.2451   0.6177   0.3913
   0.250   1.0830   0.01528   0.00710  -0.2455   0.6103   0.3979
   0.500   1.1122   0.01541   0.00718  -0.2457   0.6026   0.4047
   0.750   1.1423   0.01562   0.00732  -0.2461   0.5964   0.4117
   1.000   1.1708   0.01577   0.00747  -0.2462   0.5893   0.4204
   1.250   1.1998   0.01593   0.00766  -0.2464   0.5831   0.4296
   1.500   1.2298   0.01617   0.00786  -0.2468   0.5777   0.4409
   1.750   1.2580   0.01634   0.00808  -0.2468   0.5715   0.4537
   2.000   1.2874   0.01654   0.00829  -0.2470   0.5661   0.4677
   2.250   1.3172   0.01680   0.00856  -0.2474   0.5612   0.4842
   2.500   1.3448   0.01697   0.00885  -0.2473   0.5551   0.5031
   2.750   1.3736   0.01715   0.00907  -0.2474   0.5490   0.5252
   3.000   1.4016   0.01738   0.00938  -0.2474   0.5427   0.5530
   3.250   1.4291   0.01754   0.00967  -0.2473   0.5362   0.5847
   3.500   1.4583   0.01777   0.00995  -0.2474   0.5312   0.6218
   3.750   1.4853   0.01799   0.01035  -0.2472   0.5259   0.6670
   4.000   1.5105   0.01813   0.01067  -0.2465   0.5199   0.7224
   4.250   1.5332   0.01822   0.01085  -0.2452   0.5144   0.8020
   4.500   1.5442   0.01812   0.01095  -0.2413   0.5085   1.0000
   4.750   1.5714   0.01836   0.01117  -0.2412   0.5014   1.0000
   5.000   1.5991   0.01868   0.01142  -0.2411   0.4951   1.0000
   5.250   1.6234   0.01890   0.01171  -0.2404   0.4873   1.0000
   5.500   1.6507   0.01919   0.01190  -0.2402   0.4806   1.0000
   5.750   1.6736   0.01944   0.01227  -0.2392   0.4729   1.0000
   6.000   1.6991   0.01969   0.01249  -0.2386   0.4659   1.0000
   6.250   1.7227   0.01999   0.01286  -0.2378   0.4586   1.0000
   6.500   1.7463   0.02023   0.01314  -0.2369   0.4508   1.0000
   6.750   1.7694   0.02054   0.01350  -0.2359   0.4431   1.0000
   7.000   1.7917   0.02081   0.01382  -0.2347   0.4349   1.0000
   7.250   1.8134   0.02112   0.01421  -0.2335   0.4261   1.0000
   7.500   1.8343   0.02141   0.01451  -0.2321   0.4166   1.0000
   7.750   1.8530   0.02172   0.01495  -0.2302   0.4057   1.0000
   8.000   1.8717   0.02207   0.01536  -0.2284   0.3945   1.0000
   8.250   1.8888   0.02247   0.01578  -0.2263   0.3824   1.0000
   8.500   1.9041   0.02290   0.01629  -0.2239   0.3680   1.0000
   8.750   1.9168   0.02343   0.01688  -0.2210   0.3514   1.0000
   9.000   1.9259   0.02406   0.01756  -0.2175   0.3317   1.0000
   9.250   1.9314   0.02497   0.01842  -0.2134   0.3098   1.0000
   9.500   1.9346   0.02618   0.01954  -0.2092   0.2878   1.0000
   9.750   1.9364   0.02765   0.02092  -0.2050   0.2662   1.0000
  10.000   1.9364   0.02938   0.02256  -0.2008   0.2475   1.0000
  10.250   1.9360   0.03124   0.02436  -0.1967   0.2315   1.0000
  10.500   1.9361   0.03320   0.02628  -0.1929   0.2172   1.0000
  10.750   1.9371   0.03519   0.02830  -0.1895   0.2051   1.0000
  11.000   1.9370   0.03735   0.03049  -0.1862   0.1951   1.0000
  11.250   1.9354   0.03976   0.03287  -0.1830   0.1867   1.0000
  11.500   1.9376   0.04196   0.03517  -0.1805   0.1788   1.0000
  11.750   1.9361   0.04460   0.03781  -0.1778   0.1724   1.0000
  12.000   1.9381   0.04704   0.04034  -0.1756   0.1666   1.0000
  12.250   1.9395   0.04960   0.04298  -0.1737   0.1611   1.0000
  12.500   1.9391   0.05249   0.04581  -0.1717   0.1563   1.0000
  12.750   1.9427   0.05499   0.04852  -0.1702   0.1521   1.0000
  13.000   1.9454   0.05766   0.05131  -0.1688   0.1480   1.0000
  13.250   1.9485   0.06039   0.05404  -0.1675   0.1444   1.0000
  13.500   1.9540   0.06290   0.05660  -0.1662   0.1408   1.0000
  13.750   1.9558   0.06584   0.05974  -0.1652   0.1374   1.0000
  14.000   1.9567   0.06891   0.06293  -0.1644   0.1336   1.0000
  14.250   1.9609   0.07162   0.06564  -0.1635   0.1304   1.0000
  14.500   1.9628   0.07467   0.06880  -0.1628   0.1266   1.0000
  14.750   1.9602   0.07836   0.07270  -0.1626   0.1232   1.0000
  15.000   1.9580   0.08203   0.07649  -0.1625   0.1195   1.0000
  15.250   1.9605   0.08503   0.07943  -0.1621   0.1155   1.0000
  15.500   1.9556   0.08928   0.08390  -0.1624   0.1123   1.0000
  15.750   1.9543   0.09304   0.08784  -0.1627   0.1096   1.0000
  16.000   1.9503   0.09723   0.09216  -0.1634   0.1061   1.0000
  16.250   1.9514   0.10050   0.09542  -0.1636   0.1029   1.0000
  16.500   1.9496   0.10441   0.09948  -0.1642   0.1000   1.0000
  16.750   1.9445   0.10901   0.10430  -0.1654   0.0972   1.0000
  17.000   1.9400   0.11352   0.10895  -0.1668   0.0940   1.0000
  17.250   1.9379   0.11750   0.11297  -0.1679   0.0909   1.0000
  17.500   1.9341   0.12188   0.11747  -0.1694   0.0876   1.0000
  17.750   1.9296   0.12658   0.12239  -0.1712   0.0850   1.0000
  18.000   1.9236   0.13163   0.12759  -0.1735   0.0816   1.0000
  18.250   1.9200   0.13601   0.13200  -0.1754   0.0786   1.0000
  18.500   1.9166   0.14048   0.13660  -0.1773   0.0758   1.0000
  18.750   1.9096   0.14595   0.14230  -0.1802   0.0724   1.0000
  19.000   1.9032   0.15123   0.14770  -0.1831   0.0690   1.0000
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