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S1221 w/o flap (s1221-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S1221 w/o flap (s1221-il)
Reynolds number: 200,000
Max Cl/Cd: 70.04 at α=11.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1221-il-200000.txt
Download as CSV file: xf-s1221-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.2748   0.09532   0.09210  -0.0227   1.0000   0.0522
  -6.750  -0.2920   0.09232   0.08920  -0.0255   1.0000   0.0543
  -6.500  -0.3184   0.08980   0.08681  -0.0266   1.0000   0.0547
  -6.250  -0.3138   0.08628   0.08335  -0.0244   1.0000   0.0555
  -6.000  -0.2976   0.08466   0.08174  -0.0214   1.0000   0.0567
  -5.750  -0.2974   0.08312   0.08027  -0.0192   1.0000   0.0579
  -5.500  -0.3002   0.08134   0.07857  -0.0178   1.0000   0.0594
  -5.250  -0.2793   0.06885   0.06612  -0.0446   0.9929   0.0656
  -5.000  -0.2510   0.07003   0.06731  -0.0369   0.9884   0.0680
  -4.750  -0.1977   0.05709   0.05431  -0.0662   0.9773   0.0783
  -4.500  -0.1688   0.05665   0.05390  -0.0638   0.9676   0.0804
  -4.250  -0.0391   0.02805   0.02334  -0.1204   0.9653   0.0566
  -4.000   0.0264   0.02179   0.01599  -0.1283   0.9572   0.0375
  -3.500   0.1217   0.01738   0.01107  -0.1356   0.9111   0.0362
  -3.250   0.2090   0.01518   0.00858  -0.1467   0.8514   0.0377
  -3.000   0.3131   0.01397   0.00671  -0.1621   0.7274   0.0439
  -2.750   0.3466   0.01377   0.00611  -0.1631   0.6706   0.0474
  -2.500   0.3792   0.01350   0.00554  -0.1641   0.6275   0.0562
  -2.250   0.4195   0.01268   0.00519  -0.1674   0.5930   0.2904
  -2.000   0.4466   0.01315   0.00543  -0.1669   0.5681   0.3176
  -1.750   0.4731   0.01375   0.00592  -0.1662   0.5475   0.3496
  -1.500   0.4997   0.01425   0.00631  -0.1655   0.5310   0.3727
  -1.250   0.5277   0.01445   0.00634  -0.1653   0.5171   0.3835
  -1.000   0.5567   0.01459   0.00630  -0.1653   0.5043   0.3917
  -0.750   0.5858   0.01464   0.00623  -0.1653   0.4929   0.3979
  -0.500   0.6146   0.01478   0.00622  -0.1653   0.4831   0.4038
  -0.250   0.6441   0.01485   0.00616  -0.1655   0.4730   0.4103
   0.000   0.6732   0.01496   0.00616  -0.1655   0.4650   0.4156
   0.250   0.7022   0.01502   0.00619  -0.1656   0.4569   0.4214
   0.750   0.7607   0.01528   0.00631  -0.1658   0.4434   0.4352
   1.000   0.7899   0.01542   0.00636  -0.1659   0.4370   0.4433
   1.250   0.8190   0.01559   0.00649  -0.1660   0.4313   0.4511
   1.500   0.8481   0.01570   0.00662  -0.1661   0.4254   0.4612
   1.750   0.8771   0.01584   0.00676  -0.1661   0.4204   0.4715
   2.000   0.9064   0.01612   0.00697  -0.1663   0.4160   0.4846
   2.250   0.9350   0.01621   0.00718  -0.1663   0.4110   0.4999
   2.500   0.9639   0.01634   0.00738  -0.1663   0.4061   0.5175
   2.750   0.9931   0.01654   0.00759  -0.1665   0.4020   0.5389
   3.000   1.0225   0.01681   0.00792  -0.1667   0.3984   0.5661
   3.250   1.0513   0.01692   0.00825  -0.1667   0.3943   0.6017
   3.500   1.0796   0.01703   0.00857  -0.1667   0.3901   0.6540
   3.750   1.1051   0.01713   0.00888  -0.1658   0.3865   0.7425
   4.000   1.1236   0.01725   0.00914  -0.1634   0.3835   0.8494
   4.250   1.1396   0.01727   0.00928  -0.1605   0.3806   1.0000
   4.500   1.1687   0.01761   0.00965  -0.1608   0.3769   1.0000
   4.750   1.1977   0.01796   0.00998  -0.1609   0.3733   1.0000
   5.000   1.2266   0.01832   0.01029  -0.1611   0.3698   1.0000
   5.250   1.2558   0.01883   0.01070  -0.1613   0.3666   1.0000
   5.500   1.2834   0.01925   0.01120  -0.1613   0.3634   1.0000
   5.750   1.3107   0.01962   0.01167  -0.1611   0.3597   1.0000
   6.000   1.3384   0.01997   0.01205  -0.1610   0.3559   1.0000
   6.250   1.3664   0.02035   0.01238  -0.1610   0.3526   1.0000
   6.500   1.3947   0.02095   0.01292  -0.1611   0.3493   1.0000
   6.750   1.4204   0.02130   0.01345  -0.1607   0.3453   1.0000
   7.000   1.4467   0.02165   0.01389  -0.1604   0.3411   1.0000
   7.250   1.4738   0.02196   0.01420  -0.1602   0.3372   1.0000
   7.500   1.5020   0.02249   0.01462  -0.1603   0.3335   1.0000
   7.750   1.5262   0.02285   0.01521  -0.1596   0.3291   1.0000
   8.000   1.5516   0.02320   0.01567  -0.1591   0.3246   1.0000
   8.250   1.5783   0.02348   0.01595  -0.1588   0.3206   1.0000
   8.500   1.6055   0.02402   0.01642  -0.1588   0.3168   1.0000
   8.750   1.6282   0.02435   0.01702  -0.1578   0.3116   1.0000
   9.000   1.6531   0.02457   0.01730  -0.1573   0.3066   1.0000
   9.250   1.6802   0.02482   0.01745  -0.1571   0.3019   1.0000
   9.500   1.7016   0.02515   0.01804  -0.1560   0.2960   1.0000
   9.750   1.7256   0.02525   0.01821  -0.1552   0.2900   1.0000
  10.000   1.7501   0.02548   0.01840  -0.1547   0.2843   1.0000
  10.250   1.7707   0.02565   0.01881  -0.1534   0.2772   1.0000
  10.500   1.7943   0.02575   0.01888  -0.1526   0.2712   1.0000
  10.750   1.8144   0.02607   0.01942  -0.1513   0.2640   1.0000
  11.000   1.8357   0.02621   0.01963  -0.1502   0.2572   1.0000
  11.250   1.8555   0.02655   0.02014  -0.1489   0.2495   1.0000
  11.500   1.8751   0.02677   0.02044  -0.1475   0.2416   1.0000
  11.750   1.8932   0.02717   0.02103  -0.1459   0.2320   1.0000
  12.000   1.9101   0.02761   0.02154  -0.1443   0.2218   1.0000
  12.250   1.9246   0.02819   0.02219  -0.1423   0.2103   1.0000
  12.500   1.9363   0.02902   0.02306  -0.1400   0.1975   1.0000
  12.750   1.9442   0.03011   0.02421  -0.1372   0.1837   1.0000
  13.000   1.9452   0.03148   0.02562  -0.1335   0.1704   1.0000
  13.250   1.9428   0.03317   0.02735  -0.1296   0.1579   1.0000
  13.500   1.9373   0.03526   0.02948  -0.1258   0.1464   1.0000
  13.750   1.9286   0.03778   0.03206  -0.1223   0.1366   1.0000
  14.000   1.9140   0.04106   0.03536  -0.1191   0.1291   1.0000
  14.250   1.9017   0.04461   0.03905  -0.1172   0.1214   1.0000
  14.500   1.8821   0.04947   0.04396  -0.1163   0.1165   1.0000
  14.750   1.8678   0.05446   0.04913  -0.1167   0.1106   1.0000
  15.000   1.8472   0.06073   0.05547  -0.1180   0.1066   1.0000
  15.250   1.8275   0.06725   0.06210  -0.1196   0.1026   1.0000
  15.500   1.8104   0.07367   0.06868  -0.1215   0.0984   1.0000
  15.750   1.7907   0.08054   0.07561  -0.1236   0.0950   1.0000
  16.000   1.7737   0.08693   0.08202  -0.1254   0.0915   1.0000
  16.250   1.7601   0.09312   0.08838  -0.1275   0.0881   1.0000
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