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S1221 w/o flap (s1221-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S1221 w/o flap (s1221-il)
Reynolds number: 1,000,000
Max Cl/Cd: 137.86 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1221-il-1000000.txt
Download as CSV file: xf-s1221-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3344   0.11526   0.11361  -0.0162   1.0000   0.0124
  -9.250  -0.3309   0.11176   0.11013  -0.0171   1.0000   0.0124
  -9.000  -0.3323   0.10741   0.10581  -0.0179   1.0000   0.0126
  -8.750  -0.3277   0.10497   0.10338  -0.0180   1.0000   0.0127
  -8.500  -0.3238   0.10231   0.10074  -0.0183   1.0000   0.0128
  -8.250  -0.3084   0.09859   0.09702  -0.0221   0.9990   0.0129
  -8.000  -0.2891   0.09512   0.09355  -0.0263   0.9975   0.0131
  -7.750  -0.2712   0.09097   0.08940  -0.0313   0.9958   0.0133
  -7.500  -0.2527   0.08663   0.08506  -0.0367   0.9943   0.0136
  -7.250  -0.2400   0.08227   0.08071  -0.0409   0.9917   0.0139
  -7.000  -0.2281   0.07703   0.07549  -0.0463   0.9886   0.0146
  -6.500  -0.2342   0.03228   0.03010  -0.1121   0.9650   0.0159
  -6.250  -0.2035   0.02945   0.02716  -0.1170   0.9552   0.0161
  -6.000  -0.1683   0.02702   0.02460  -0.1219   0.9431   0.0166
  -5.500   0.0524   0.01331   0.00835  -0.1662   0.7539   0.0128
  -5.250   0.0776   0.01289   0.00757  -0.1658   0.6931   0.0128
  -5.000   0.1059   0.01237   0.00684  -0.1661   0.6537   0.0131
  -4.750   0.1350   0.01195   0.00621  -0.1664   0.6100   0.0132
  -4.500   0.1651   0.01153   0.00556  -0.1670   0.5698   0.0131
  -4.250   0.1961   0.01115   0.00499  -0.1677   0.5387   0.0132
  -4.000   0.2277   0.01081   0.00450  -0.1685   0.5153   0.0133
  -3.750   0.2592   0.01052   0.00409  -0.1693   0.4960   0.0136
  -3.500   0.2907   0.01028   0.00373  -0.1700   0.4799   0.0140
  -3.250   0.3219   0.01008   0.00342  -0.1706   0.4658   0.0146
  -3.000   0.3528   0.00992   0.00316  -0.1710   0.4534   0.0152
  -2.750   0.3843   0.00971   0.00286  -0.1717   0.4425   0.0160
  -2.500   0.4150   0.00959   0.00265  -0.1721   0.4317   0.0170
  -2.250   0.4453   0.00950   0.00250  -0.1724   0.4219   0.0183
  -2.000   0.4758   0.00941   0.00235  -0.1727   0.4131   0.0215
  -1.750   0.5140   0.00863   0.00202  -0.1754   0.4044   0.1755
  -1.500   0.5450   0.00851   0.00205  -0.1760   0.3969   0.2460
  -1.250   0.5741   0.00855   0.00207  -0.1760   0.3899   0.2629
  -1.000   0.6027   0.00864   0.00210  -0.1758   0.3825   0.2740
  -0.750   0.6318   0.00867   0.00215  -0.1758   0.3770   0.2887
  -0.500   0.6606   0.00874   0.00220  -0.1758   0.3705   0.3008
  -0.250   0.6889   0.00886   0.00225  -0.1755   0.3646   0.3084
   0.000   0.7183   0.00887   0.00226  -0.1756   0.3598   0.3142
   0.250   0.7472   0.00893   0.00229  -0.1756   0.3547   0.3180
   0.500   0.7758   0.00903   0.00234  -0.1755   0.3492   0.3218
   0.750   0.8047   0.00908   0.00237  -0.1754   0.3456   0.3253
   1.000   0.8338   0.00912   0.00241  -0.1754   0.3414   0.3310
   1.250   0.8625   0.00921   0.00247  -0.1754   0.3373   0.3367
   1.500   0.8908   0.00932   0.00255  -0.1753   0.3330   0.3420
   1.750   0.9199   0.00936   0.00261  -0.1753   0.3306   0.3491
   2.000   0.9487   0.00941   0.00268  -0.1753   0.3275   0.3569
   2.250   0.9774   0.00949   0.00276  -0.1752   0.3241   0.3655
   2.500   1.0058   0.00960   0.00286  -0.1751   0.3206   0.3756
   2.750   1.0342   0.00973   0.00300  -0.1751   0.3171   0.3873
   3.000   1.0630   0.00978   0.00309  -0.1751   0.3153   0.4006
   3.250   1.0918   0.00984   0.00320  -0.1751   0.3132   0.4162
   3.500   1.1205   0.00991   0.00332  -0.1750   0.3108   0.4344
   3.750   1.1490   0.01000   0.00345  -0.1750   0.3080   0.4548
   4.000   1.1774   0.01012   0.00359  -0.1750   0.3050   0.4769
   4.250   1.2054   0.01029   0.00379  -0.1749   0.3016   0.5015
   4.750   1.2631   0.01039   0.00408  -0.1750   0.2981   0.5642
   5.000   1.2923   0.01043   0.00423  -0.1752   0.2955   0.6079
   5.250   1.3218   0.01047   0.00443  -0.1755   0.2926   0.6809
   5.500   1.3502   0.01055   0.00466  -0.1755   0.2892   0.7657
   5.750   1.3771   0.01072   0.00491  -0.1751   0.2853   0.8172
   6.000   1.4037   0.01071   0.00504  -0.1747   0.2834   0.8681
   6.250   1.4228   0.01061   0.00510  -0.1725   0.2813   1.0000
   6.500   1.4506   0.01075   0.00525  -0.1724   0.2787   1.0000
   6.750   1.4781   0.01091   0.00541  -0.1722   0.2757   1.0000
   7.000   1.5051   0.01114   0.00562  -0.1719   0.2721   1.0000
   7.250   1.5323   0.01132   0.00581  -0.1717   0.2688   1.0000
   7.500   1.5601   0.01141   0.00594  -0.1716   0.2656   1.0000
   7.750   1.5874   0.01156   0.00610  -0.1714   0.2615   1.0000
   8.000   1.6139   0.01180   0.00630  -0.1711   0.2557   1.0000
   8.250   1.6412   0.01193   0.00647  -0.1710   0.2513   1.0000
   8.500   1.6681   0.01210   0.00665  -0.1707   0.2462   1.0000
   8.750   1.6943   0.01235   0.00689  -0.1704   0.2409   1.0000
   9.000   1.7210   0.01253   0.00710  -0.1701   0.2365   1.0000
   9.250   1.7472   0.01277   0.00734  -0.1698   0.2298   1.0000
   9.500   1.7729   0.01304   0.00760  -0.1694   0.2225   1.0000
   9.750   1.7983   0.01336   0.00790  -0.1689   0.2137   1.0000
  10.000   1.8234   0.01369   0.00823  -0.1685   0.2045   1.0000
  10.250   1.8476   0.01414   0.00862  -0.1679   0.1923   1.0000
  10.500   1.8708   0.01467   0.00909  -0.1672   0.1779   1.0000
  10.750   1.8931   0.01532   0.00966  -0.1663   0.1617   1.0000
  11.000   1.9140   0.01611   0.01034  -0.1653   0.1447   1.0000
  11.250   1.9344   0.01692   0.01107  -0.1642   0.1290   1.0000
  11.500   1.9542   0.01777   0.01184  -0.1630   0.1138   1.0000
  11.750   1.9736   0.01862   0.01263  -0.1618   0.1009   1.0000
  12.000   1.9923   0.01950   0.01345  -0.1605   0.0893   1.0000
  12.250   2.0102   0.02040   0.01431  -0.1590   0.0790   1.0000
  12.500   2.0269   0.02138   0.01524  -0.1574   0.0695   1.0000
  12.750   2.0430   0.02235   0.01619  -0.1557   0.0619   1.0000
  13.000   2.0583   0.02331   0.01716  -0.1539   0.0554   1.0000
  13.250   2.0719   0.02434   0.01819  -0.1519   0.0503   1.0000
  13.500   2.0839   0.02537   0.01926  -0.1496   0.0466   1.0000
  13.750   2.0895   0.02656   0.02048  -0.1462   0.0432   1.0000
  14.000   2.0967   0.02756   0.02154  -0.1431   0.0412   1.0000
  14.250   2.1008   0.02882   0.02286  -0.1398   0.0393   1.0000
  14.500   2.1016   0.03039   0.02449  -0.1363   0.0370   1.0000
  14.750   2.1045   0.03189   0.02607  -0.1333   0.0357   1.0000
  15.000   2.1061   0.03358   0.02785  -0.1306   0.0344   1.0000
  15.250   2.1040   0.03569   0.03005  -0.1279   0.0333   1.0000
  15.500   2.0982   0.03833   0.03278  -0.1255   0.0322   1.0000
  15.750   2.0884   0.04173   0.03629  -0.1239   0.0311   1.0000
  16.000   2.0754   0.04609   0.04078  -0.1233   0.0304   1.0000
  16.250   2.0661   0.05061   0.04544  -0.1238   0.0298   1.0000
  16.500   2.0530   0.05614   0.05113  -0.1251   0.0294   1.0000
  16.750   2.0342   0.06294   0.05809  -0.1271   0.0291   1.0000
  17.000   2.0109   0.07075   0.06608  -0.1296   0.0287   1.0000
  17.250   1.9825   0.07953   0.07504  -0.1325   0.0288   1.0000
  17.500   1.9532   0.08850   0.08417  -0.1355   0.0284   1.0000
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