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S1221 w/o flap (s1221-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S1221 w/o flap (s1221-il)
Reynolds number: 1,000,000
Max Cl/Cd: 135.07 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1221-il-1000000-n5.txt
Download as CSV file: xf-s1221-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1221  w/o flap                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2693   0.10032   0.09855  -0.0399   0.9874   0.0069
  -9.000  -0.2709   0.09475   0.09299  -0.0422   0.9853   0.0070
  -8.750  -0.4493   0.05312   0.05112  -0.0646   0.9823   0.0072
  -8.250  -0.4375   0.02731   0.02460  -0.1093   0.9579   0.0071
  -8.000  -0.3973   0.02374   0.02074  -0.1183   0.9491   0.0072
  -7.500  -0.1903   0.01634   0.01166  -0.1595   0.7435   0.0075
  -7.250  -0.1643   0.01563   0.01062  -0.1601   0.6914   0.0075
  -7.000  -0.1358   0.01497   0.00972  -0.1609   0.6558   0.0076
  -6.750  -0.1070   0.01441   0.00894  -0.1617   0.6151   0.0077
  -6.500  -0.0782   0.01404   0.00836  -0.1623   0.5767   0.0078
  -6.250  -0.0485   0.01363   0.00777  -0.1630   0.5472   0.0080
  -6.000  -0.0185   0.01326   0.00724  -0.1636   0.5227   0.0081
  -5.750   0.0120   0.01286   0.00669  -0.1644   0.5028   0.0083
  -5.500   0.0431   0.01244   0.00614  -0.1652   0.4861   0.0083
  -5.250   0.0743   0.01205   0.00563  -0.1660   0.4720   0.0085
  -5.000   0.1056   0.01171   0.00517  -0.1668   0.4591   0.0086
  -4.750   0.1368   0.01141   0.00476  -0.1675   0.4469   0.0088
  -4.500   0.1679   0.01114   0.00438  -0.1682   0.4348   0.0090
  -4.250   0.1991   0.01089   0.00405  -0.1688   0.4254   0.0092
  -3.750   0.2606   0.01052   0.00352  -0.1698   0.4088   0.0096
  -3.500   0.2918   0.01031   0.00322  -0.1704   0.4007   0.0100
  -3.250   0.3228   0.01013   0.00298  -0.1709   0.3942   0.0104
  -3.000   0.3531   0.01001   0.00281  -0.1712   0.3871   0.0109
  -2.750   0.3833   0.00993   0.00266  -0.1715   0.3809   0.0114
  -2.500   0.4134   0.00985   0.00253  -0.1718   0.3744   0.0119
  -2.250   0.4433   0.00980   0.00242  -0.1720   0.3674   0.0126
  -2.000   0.4735   0.00972   0.00231  -0.1722   0.3621   0.0144
  -1.750   0.5037   0.00964   0.00222  -0.1725   0.3567   0.0206
  -1.500   0.5351   0.00947   0.00211  -0.1732   0.3512   0.0561
  -1.250   0.5684   0.00914   0.00199  -0.1744   0.3470   0.1358
  -1.000   0.6008   0.00889   0.00196  -0.1754   0.3425   0.2249
  -0.750   0.6303   0.00889   0.00200  -0.1756   0.3377   0.2550
  -0.500   0.6593   0.00894   0.00205  -0.1756   0.3329   0.2723
  -0.250   0.6885   0.00896   0.00208  -0.1756   0.3292   0.2831
   0.000   0.7174   0.00902   0.00211  -0.1755   0.3253   0.2872
   0.250   0.7462   0.00908   0.00213  -0.1755   0.3215   0.2897
   0.750   0.8039   0.00921   0.00221  -0.1753   0.3147   0.2962
   1.000   0.8327   0.00926   0.00226  -0.1753   0.3115   0.3005
   1.250   0.8614   0.00933   0.00231  -0.1752   0.3085   0.3045
   1.500   0.8900   0.00942   0.00237  -0.1751   0.3055   0.3080
   1.750   0.9186   0.00950   0.00244  -0.1751   0.3025   0.3126
   2.000   0.9473   0.00957   0.00252  -0.1750   0.3003   0.3179
   2.250   0.9759   0.00963   0.00259  -0.1749   0.2981   0.3232
   2.500   1.0044   0.00971   0.00267  -0.1748   0.2955   0.3287
   2.750   1.0329   0.00979   0.00276  -0.1748   0.2932   0.3356
   3.000   1.0612   0.00988   0.00286  -0.1747   0.2909   0.3424
   3.250   1.0896   0.00998   0.00297  -0.1746   0.2885   0.3512
   3.750   1.1463   0.01016   0.00321  -0.1744   0.2844   0.3713
   4.000   1.1747   0.01024   0.00332  -0.1743   0.2825   0.3817
   4.250   1.2030   0.01033   0.00344  -0.1743   0.2805   0.3937
   4.500   1.2313   0.01042   0.00357  -0.1742   0.2784   0.4071
   4.750   1.2594   0.01052   0.00372  -0.1741   0.2759   0.4215
   5.000   1.2874   0.01065   0.00387  -0.1740   0.2728   0.4372
   5.250   1.3153   0.01079   0.00404  -0.1739   0.2697   0.4546
   5.500   1.3436   0.01086   0.00418  -0.1738   0.2674   0.4740
   5.750   1.3718   0.01095   0.00434  -0.1738   0.2640   0.4974
   6.000   1.3999   0.01106   0.00451  -0.1738   0.2603   0.5254
   6.250   1.4279   0.01120   0.00470  -0.1737   0.2569   0.5568
   6.500   1.4561   0.01131   0.00490  -0.1737   0.2540   0.5929
   6.750   1.4848   0.01138   0.00510  -0.1739   0.2512   0.6412
   7.000   1.5137   0.01145   0.00534  -0.1740   0.2473   0.7235
   7.250   1.5410   0.01161   0.00558  -0.1739   0.2419   0.7764
   7.500   1.5681   0.01175   0.00579  -0.1737   0.2368   0.8133
   7.750   1.5941   0.01190   0.00602  -0.1732   0.2297   0.8567
   8.000   1.6127   0.01194   0.00618  -0.1711   0.2216   1.0000
   8.250   1.6384   0.01229   0.00646  -0.1707   0.2100   1.0000
   8.500   1.6640   0.01264   0.00676  -0.1703   0.1989   1.0000
   8.750   1.6897   0.01296   0.00706  -0.1699   0.1900   1.0000
   9.000   1.7146   0.01337   0.00743  -0.1694   0.1793   1.0000
   9.250   1.7387   0.01388   0.00786  -0.1688   0.1650   1.0000
   9.500   1.7620   0.01448   0.00837  -0.1681   0.1490   1.0000
   9.750   1.7852   0.01507   0.00890  -0.1673   0.1357   1.0000
  10.000   1.8082   0.01566   0.00944  -0.1666   0.1242   1.0000
  10.250   1.8307   0.01630   0.01002  -0.1658   0.1125   1.0000
  10.500   1.8527   0.01695   0.01062  -0.1649   0.1017   1.0000
  10.750   1.8743   0.01763   0.01126  -0.1639   0.0918   1.0000
  11.000   1.8957   0.01831   0.01190  -0.1630   0.0826   1.0000
  11.250   1.9163   0.01904   0.01260  -0.1619   0.0734   1.0000
  11.500   1.9357   0.01987   0.01338  -0.1606   0.0639   1.0000
  11.750   1.9549   0.02066   0.01415  -0.1594   0.0566   1.0000
  12.000   1.9731   0.02151   0.01498  -0.1580   0.0502   1.0000
  12.250   1.9916   0.02228   0.01576  -0.1566   0.0459   1.0000
  12.500   2.0089   0.02311   0.01660  -0.1551   0.0418   1.0000
  12.750   2.0256   0.02392   0.01744  -0.1535   0.0388   1.0000
  13.000   2.0399   0.02488   0.01842  -0.1515   0.0354   1.0000
  13.250   2.0534   0.02579   0.01937  -0.1494   0.0332   1.0000
  13.500   2.0614   0.02682   0.02045  -0.1464   0.0315   1.0000
  13.750   2.0677   0.02788   0.02157  -0.1432   0.0301   1.0000
  14.000   2.0748   0.02895   0.02271  -0.1403   0.0289   1.0000
  14.250   2.0806   0.03017   0.02400  -0.1374   0.0280   1.0000
  14.500   2.0833   0.03167   0.02557  -0.1343   0.0268   1.0000
  14.750   2.0832   0.03346   0.02744  -0.1313   0.0257   1.0000
  15.000   2.0821   0.03546   0.02953  -0.1287   0.0247   1.0000
  15.250   2.0810   0.03765   0.03182  -0.1265   0.0241   1.0000
  15.500   2.0769   0.04036   0.03463  -0.1247   0.0235   1.0000
  15.750   2.0687   0.04388   0.03827  -0.1237   0.0226   1.0000
  16.000   2.0589   0.04817   0.04269  -0.1238   0.0223   1.0000
  16.250   2.0436   0.05382   0.04849  -0.1249   0.0216   1.0000
  16.500   2.0246   0.06055   0.05537  -0.1268   0.0211   1.0000
  16.750   2.0036   0.06794   0.06293  -0.1291   0.0210   1.0000
  17.000   1.9754   0.07668   0.07184  -0.1320   0.0205   1.0000
  17.250   1.9506   0.08491   0.08024  -0.1347   0.0209   1.0000
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