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S1210 12% (s1210-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S1210 12% (s1210-il)
Reynolds number: 50,000
Max Cl/Cd: 14.88 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1210-il-50000.txt
Download as CSV file: xf-s1210-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2320   0.12285   0.11714  -0.0197   1.0000   0.1820
  -7.000  -0.2460   0.12309   0.11752  -0.0179   1.0000   0.1862
  -6.750  -0.2712   0.12504   0.11965  -0.0158   1.0000   0.1878
  -6.500  -0.2700   0.12198   0.11670  -0.0139   1.0000   0.1900
  -6.250  -0.2661   0.11944   0.11423  -0.0115   1.0000   0.1944
  -6.000  -0.2775   0.11917   0.11408  -0.0092   1.0000   0.1985
  -5.750  -0.2982   0.12016   0.11522  -0.0070   1.0000   0.2014
  -5.500  -0.3284   0.12228   0.11750  -0.0044   1.0000   0.2028
  -5.250  -0.3353   0.12093   0.11626  -0.0037   0.9987   0.2045
  -5.000  -0.2967   0.11644   0.11170  -0.0092   0.9885   0.2171
  -4.750  -0.2686   0.11223   0.10749  -0.0140   0.9774   0.2245
  -4.500  -0.2638   0.11238   0.10767  -0.0211   0.9618   0.2349
  -4.250  -0.2327   0.10671   0.10198  -0.0220   0.9517   0.2411
  -4.000  -0.2244   0.10662   0.10192  -0.0312   0.9365   0.2519
  -3.750  -0.2016   0.10153   0.09683  -0.0300   0.9264   0.2557
  -3.500  -0.1820   0.09875   0.09403  -0.0330   0.9152   0.2644
  -3.250  -0.1590   0.09563   0.09091  -0.0402   0.9048   0.2713
  -3.000  -0.1478   0.09300   0.08829  -0.0400   0.8932   0.2756
  -2.750  -0.1243   0.09126   0.08653  -0.0520   0.8806   0.2859
  -2.500  -0.0982   0.08699   0.08223  -0.0540   0.8730   0.2875
  -2.250  -0.0861   0.08454   0.07978  -0.0551   0.8629   0.2893
  -2.000   0.4236   0.04045   0.03240  -0.1956   0.8760   0.1766
  -1.750   0.4506   0.04195   0.03445  -0.1945   0.8634   0.2720
  -0.500   0.4736   0.04877   0.04174  -0.1658   0.8137   0.5092
  -0.250   0.5077   0.04905   0.04180  -0.1682   0.8055   0.5314
   0.000   0.5514   0.04911   0.04160  -0.1725   0.7978   0.5495
   0.250   0.5876   0.04946   0.04178  -0.1753   0.7910   0.5626
   0.500   0.6198   0.05027   0.04245  -0.1782   0.7827   0.5732
   0.750   0.6871   0.04952   0.04142  -0.1853   0.7778   0.5876
   1.000   0.6877   0.05207   0.04397  -0.1845   0.7683   0.5928
   1.250   0.7420   0.05197   0.04370  -0.1895   0.7628   0.6062
   1.500   0.7526   0.05437   0.04606  -0.1902   0.7546   0.6129
   1.750   0.7885   0.05520   0.04681  -0.1929   0.7483   0.6245
   2.000   0.8195   0.05649   0.04801  -0.1952   0.7423   0.6374
   2.250   0.8274   0.05908   0.05061  -0.1952   0.7349   0.6466
   2.500   0.8794   0.05910   0.05052  -0.1991   0.7294   0.6658
   2.750   0.8676   0.06284   0.05435  -0.1971   0.7224   0.6724
   3.000   0.8916   0.06439   0.05590  -0.1981   0.7159   0.6905
   3.250   0.9202   0.06582   0.05733  -0.1995   0.7098   0.7133
   3.500   0.9149   0.06926   0.06086  -0.1983   0.7030   0.7260
   3.750   0.9583   0.06924   0.06089  -0.1999   0.6964   0.7651
   4.000   0.9438   0.07334   0.06511  -0.1980   0.6895   0.7815
   4.250   0.9575   0.07475   0.06668  -0.1970   0.6827   0.8277
   4.500   0.9565   0.07581   0.06794  -0.1937   0.6764   0.9767
   4.750   1.0008   0.07925   0.07120  -0.2010   0.6656   1.0000
   5.000   1.0160   0.08284   0.07467  -0.2030   0.6562   1.0000
   5.250   1.0747   0.08289   0.07452  -0.2060   0.6453   1.0000
   5.500   1.0481   0.08867   0.08039  -0.2045   0.6369   1.0000
   5.750   1.0784   0.09033   0.08198  -0.2052   0.6261   1.0000
   6.000   1.0933   0.09297   0.08462  -0.2051   0.6154   1.0000
   6.250   1.0898   0.09721   0.08890  -0.2046   0.6052   1.0000
   6.500   1.1174   0.09880   0.09050  -0.2046   0.5926   1.0000
   6.750   1.1669   0.09824   0.08991  -0.2046   0.5793   1.0000
   7.000   1.1349   0.10502   0.09682  -0.2038   0.5680   1.0000
   7.250   1.1445   0.10804   0.09987  -0.2032   0.5545   1.0000
   7.500   1.1624   0.11025   0.10213  -0.2027   0.5407   1.0000
   7.750   1.1857   0.11177   0.10372  -0.2020   0.5260   1.0000
   8.000   1.2188   0.11215   0.10413  -0.2010   0.5118   1.0000
   8.250   1.2413   0.11338   0.10543  -0.2000   0.4974   1.0000
   8.500   1.2293   0.11867   0.11080  -0.1998   0.4831   1.0000
   8.750   1.2297   0.12255   0.11479  -0.1994   0.4688   1.0000
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