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S1210 12% (s1210-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S1210 12% (s1210-il)
Reynolds number: 50,000
Max Cl/Cd: 42.15 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1210-il-50000-n5.txt
Download as CSV file: xf-s1210-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.500  -0.1678   0.10774   0.10191  -0.0418   0.9704   0.1176
  -6.250  -0.1520   0.10424   0.09841  -0.0457   0.9599   0.1179
  -5.750  -0.1495   0.09120   0.08532  -0.0606   0.9286   0.0579
  -5.500  -0.1296   0.08700   0.08112  -0.0646   0.9179   0.0576
  -5.250  -0.1103   0.08331   0.07744  -0.0676   0.9063   0.0568
  -5.000  -0.0938   0.07934   0.07346  -0.0712   0.8930   0.0558
  -4.750  -0.0754   0.07498   0.06910  -0.0760   0.8799   0.0547
  -4.500  -0.0522   0.06961   0.06371  -0.0834   0.8679   0.0535
  -4.250  -0.0112   0.06085   0.05484  -0.0987   0.8594   0.0517
  -4.000   0.1366   0.04041   0.03296  -0.1515   0.8596   0.0503
  -3.750   0.2034   0.03648   0.02842  -0.1631   0.8513   0.0541
  -3.500   0.2696   0.03340   0.02459  -0.1721   0.8455   0.0578
  -3.250   0.3160   0.03156   0.02264  -0.1761   0.8363   0.0610
  -3.000   0.3680   0.02993   0.02076  -0.1808   0.8287   0.0670
  -2.750   0.4223   0.02848   0.01919  -0.1866   0.8189   0.0802
  -2.500   0.5049   0.02630   0.01776  -0.1989   0.8128   0.1824
  -2.250   0.5394   0.02744   0.01874  -0.1990   0.7995   0.3033
  -2.000   0.5607   0.02838   0.01975  -0.1958   0.7870   0.3456
  -1.750   0.6082   0.02803   0.01902  -0.1989   0.7780   0.3710
  -1.500   0.6468   0.02779   0.01850  -0.2008   0.7652   0.3850
  -1.250   0.6854   0.02752   0.01800  -0.2026   0.7537   0.3954
  -1.000   0.7336   0.02708   0.01721  -0.2064   0.7443   0.4066
  -0.750   0.7716   0.02697   0.01688  -0.2084   0.7322   0.4160
  -0.500   0.8096   0.02688   0.01658  -0.2104   0.7211   0.4246
  -0.250   0.8537   0.02668   0.01609  -0.2135   0.7120   0.4341
   0.000   0.8849   0.02683   0.01613  -0.2142   0.7007   0.4422
   0.250   0.9230   0.02690   0.01598  -0.2163   0.6916   0.4531
   0.500   0.9552   0.02704   0.01603  -0.2171   0.6825   0.4616
   0.750   0.9887   0.02724   0.01610  -0.2183   0.6736   0.4721
   1.000   1.0224   0.02743   0.01619  -0.2195   0.6653   0.4846
   1.250   1.0525   0.02772   0.01647  -0.2199   0.6572   0.4964
   1.500   1.0840   0.02799   0.01671  -0.2207   0.6495   0.5098
   1.750   1.1152   0.02830   0.01699  -0.2214   0.6424   0.5251
   2.000   1.1433   0.02871   0.01745  -0.2216   0.6347   0.5423
   2.250   1.1771   0.02893   0.01763  -0.2225   0.6289   0.5636
   2.500   1.2004   0.02954   0.01837  -0.2220   0.6210   0.5848
   2.750   1.2301   0.02984   0.01876  -0.2223   0.6149   0.6112
   3.000   1.2548   0.03035   0.01940  -0.2218   0.6082   0.6413
   3.250   1.2786   0.03083   0.02003  -0.2211   0.6015   0.6781
   3.500   1.3061   0.03099   0.02029  -0.2206   0.5963   0.7292
   3.750   1.3168   0.03161   0.02121  -0.2176   0.5890   0.7930
   4.000   1.3321   0.03178   0.02149  -0.2150   0.5831   1.0000
   4.250   1.3638   0.03249   0.02210  -0.2161   0.5767   1.0000
   4.500   1.3874   0.03343   0.02306  -0.2158   0.5690   1.0000
   4.750   1.4226   0.03378   0.02332  -0.2169   0.5630   1.0000
   5.000   1.4382   0.03496   0.02463  -0.2153   0.5540   1.0000
   5.250   1.4705   0.03531   0.02491  -0.2159   0.5472   1.0000
   5.500   1.4860   0.03647   0.02623  -0.2142   0.5384   1.0000
   5.750   1.5160   0.03686   0.02660  -0.2143   0.5313   1.0000
   6.000   1.5310   0.03802   0.02790  -0.2125   0.5225   1.0000
   6.250   1.5595   0.03840   0.02829  -0.2124   0.5149   1.0000
   6.500   1.5728   0.03958   0.02966  -0.2103   0.5056   1.0000
   6.750   1.6036   0.03970   0.02977  -0.2103   0.4975   1.0000
   7.000   1.6117   0.04103   0.03130  -0.2074   0.4870   1.0000
   7.250   1.6364   0.04134   0.03167  -0.2065   0.4777   1.0000
   7.500   1.6510   0.04216   0.03263  -0.2044   0.4671   1.0000
   7.750   1.6613   0.04322   0.03385  -0.2017   0.4564   1.0000
   8.000   1.6857   0.04334   0.03400  -0.2006   0.4463   1.0000
   8.250   1.6906   0.04459   0.03546  -0.1972   0.4349   1.0000
   8.500   1.6938   0.04589   0.03694  -0.1937   0.4238   1.0000
   8.750   1.7071   0.04644   0.03757  -0.1911   0.4129   1.0000
   9.000   1.7079   0.04779   0.03908  -0.1873   0.4014   1.0000
   9.250   1.6990   0.04999   0.04147  -0.1829   0.3896   1.0000
   9.500   1.6976   0.05176   0.04339  -0.1794   0.3778   1.0000
   9.750   1.7005   0.05325   0.04500  -0.1765   0.3658   1.0000
  10.000   1.6917   0.05596   0.04788  -0.1732   0.3533   1.0000
  10.250   1.6773   0.05962   0.05172  -0.1703   0.3405   1.0000
  10.500   1.6689   0.06294   0.05517  -0.1681   0.3274   1.0000
  10.750   1.6656   0.06588   0.05820  -0.1664   0.3145   1.0000
  11.000   1.6670   0.06836   0.06074  -0.1649   0.3018   1.0000
  11.250   1.6729   0.07033   0.06270  -0.1635   0.2896   1.0000
  11.500   1.6729   0.07325   0.06568  -0.1623   0.2773   1.0000
  11.750   1.6672   0.07720   0.06972  -0.1615   0.2654   1.0000
  12.000   1.6672   0.08041   0.07297  -0.1607   0.2547   1.0000
  12.250   1.6760   0.08226   0.07476  -0.1596   0.2448   1.0000
  12.500   1.6690   0.08684   0.07949  -0.1594   0.2352   1.0000
  12.750   1.6727   0.08975   0.08244  -0.1588   0.2268   1.0000
  13.000   1.6736   0.09313   0.08590  -0.1585   0.2184   1.0000
  13.250   1.6723   0.09701   0.08988  -0.1585   0.2109   1.0000
  13.500   1.6738   0.10041   0.09340  -0.1584   0.2037   1.0000
  13.750   1.6783   0.10344   0.09651  -0.1583   0.1976   1.0000
  14.000   1.6685   0.10908   0.10239  -0.1595   0.1918   1.0000
  14.250   1.6859   0.10980   0.10313  -0.1584   0.1866   1.0000
  14.500   1.6731   0.11616   0.10973  -0.1603   0.1819   1.0000
  14.750   1.6541   0.12383   0.11766  -0.1632   0.1770   1.0000
  15.000   1.6722   0.12423   0.11809  -0.1621   0.1723   1.0000
  15.250   1.6543   0.13194   0.12602  -0.1655   0.1683   1.0000
  15.500   1.5704   0.15515   0.14956  -0.1795   0.1626   1.0000
  15.750   1.5795   0.15739   0.15189  -0.1800   0.1590   1.0000
  16.000   1.6173   0.15285   0.14743  -0.1757   0.1568   1.0000
  16.250   1.4850   0.19456   0.18909  -0.2045   0.1469   1.0000
  16.500   1.4985   0.19564   0.19030  -0.2045   0.1442   1.0000
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