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S1221 w/ 4 deg flap (s1221-flap-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S1221 w/ 4 deg flap (s1221-flap-il)
Reynolds number: 200,000
Max Cl/Cd: 69.35 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1221-flap-il-200000.txt
Download as CSV file: xf-s1221-flap-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1221  w/ 4 deg 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2226   0.09616   0.09334  -0.0175   1.0000   0.0521
  -7.500  -0.2372   0.09307   0.09030  -0.0193   1.0000   0.0539
  -7.250  -0.2512   0.08865   0.08593  -0.0250   0.9976   0.0545
  -7.000  -0.2041   0.08403   0.08129  -0.0251   0.9940   0.0567
  -6.750  -0.1811   0.08012   0.07737  -0.0290   0.9886   0.0607
  -6.500  -0.1930   0.07488   0.07217  -0.0376   0.9806   0.0642
  -6.250  -0.1731   0.06913   0.06645  -0.0406   0.9752   0.0659
  -6.000  -0.1391   0.06576   0.06306  -0.0426   0.9691   0.0685
  -5.750  -0.1249   0.06172   0.05904  -0.0463   0.9603   0.0720
  -5.500  -0.2199   0.07409   0.07127  -0.0432   0.9767   0.0669
  -5.250  -0.1868   0.07074   0.06791  -0.0479   0.9688   0.0703
  -5.000  -0.1455   0.06083   0.05799  -0.0684   0.9590   0.0784
  -4.750   0.0648   0.02638   0.02068  -0.1460   0.9676   0.0386
  -4.500   0.1219   0.02296   0.01704  -0.1525   0.9616   0.0370
  -4.250   0.1870   0.02051   0.01427  -0.1597   0.9558   0.0365
  -4.000   0.2381   0.01878   0.01239  -0.1637   0.9452   0.0371
  -3.750   0.2889   0.01722   0.01081  -0.1678   0.9335   0.0399
  -3.500   0.3394   0.01580   0.00945  -0.1716   0.9171   0.0431
  -3.250   0.3894   0.01441   0.00805  -0.1753   0.8882   0.0470
  -3.000   0.5518   0.01238   0.00544  -0.2023   0.6779   0.3105
  -2.750   0.5751   0.01334   0.00610  -0.2008   0.6192   0.3398
  -2.500   0.5993   0.01407   0.00654  -0.1996   0.5827   0.3632
  -2.250   0.6242   0.01447   0.00676  -0.1986   0.5576   0.3749
  -2.000   0.6522   0.01468   0.00674  -0.1985   0.5375   0.3830
  -1.750   0.6801   0.01489   0.00678  -0.1983   0.5213   0.3899
  -1.500   0.7099   0.01510   0.00671  -0.1985   0.5071   0.3968
  -1.250   0.7384   0.01516   0.00672  -0.1985   0.4944   0.4019
  -1.000   0.7674   0.01534   0.00676  -0.1985   0.4835   0.4078
  -0.750   0.7975   0.01552   0.00674  -0.1989   0.4736   0.4140
  -0.500   0.8266   0.01561   0.00681  -0.1990   0.4648   0.4188
  -0.250   0.8558   0.01578   0.00688  -0.1991   0.4569   0.4250
   0.000   0.8858   0.01598   0.00697  -0.1994   0.4498   0.4325
   0.250   0.9146   0.01610   0.00709  -0.1994   0.4425   0.4389
   0.500   0.9446   0.01640   0.00722  -0.1997   0.4363   0.4472
   0.750   0.9732   0.01648   0.00738  -0.1997   0.4300   0.4549
   1.000   1.0026   0.01667   0.00753  -0.1998   0.4245   0.4654
   1.250   1.0320   0.01695   0.00777  -0.2000   0.4197   0.4760
   1.500   1.0608   0.01711   0.00801  -0.2001   0.4145   0.4887
   1.750   1.0898   0.01729   0.00822  -0.2001   0.4093   0.5032
   2.000   1.1190   0.01753   0.00845  -0.2003   0.4050   0.5199
   2.250   1.1487   0.01787   0.00881  -0.2006   0.4011   0.5391
   2.500   1.1773   0.01805   0.00914  -0.2006   0.3969   0.5620
   2.750   1.2060   0.01826   0.00946  -0.2006   0.3926   0.5895
   3.000   1.2347   0.01850   0.00978  -0.2006   0.3887   0.6228
   3.250   1.2634   0.01892   0.01024  -0.2006   0.3851   0.6617
   3.500   1.2895   0.01916   0.01070  -0.2000   0.3817   0.7054
   3.750   1.3153   0.01946   0.01115  -0.1993   0.3781   0.7485
   4.000   1.3416   0.01975   0.01149  -0.1988   0.3745   0.7898
   4.250   1.3664   0.01997   0.01174  -0.1979   0.3712   0.8280
   4.500   1.3869   0.02025   0.01204  -0.1961   0.3683   0.8761
   4.750   1.4059   0.02034   0.01234  -0.1941   0.3653   1.0000
   5.000   1.4345   0.02075   0.01280  -0.1943   0.3615   1.0000
   5.250   1.4630   0.02113   0.01319  -0.1944   0.3577   1.0000
   5.500   1.4917   0.02155   0.01357  -0.1946   0.3543   1.0000
   5.750   1.5207   0.02217   0.01413  -0.1948   0.3509   1.0000
   6.000   1.5461   0.02253   0.01465  -0.1943   0.3469   1.0000
   6.250   1.5724   0.02290   0.01511  -0.1940   0.3426   1.0000
   6.500   1.5995   0.02325   0.01544  -0.1938   0.3386   1.0000
   6.750   1.6281   0.02385   0.01593  -0.1940   0.3348   1.0000
   7.000   1.6513   0.02419   0.01651  -0.1930   0.3305   1.0000
   7.250   1.6762   0.02455   0.01697  -0.1924   0.3259   1.0000
   7.500   1.7025   0.02487   0.01728  -0.1921   0.3219   1.0000
   7.750   1.7294   0.02542   0.01780  -0.1920   0.3179   1.0000
   8.000   1.7510   0.02576   0.01839  -0.1907   0.3127   1.0000
   8.250   1.7750   0.02599   0.01866  -0.1899   0.3075   1.0000
   8.500   1.8016   0.02633   0.01890  -0.1897   0.3027   1.0000
   8.750   1.8210   0.02664   0.01949  -0.1881   0.2967   1.0000
   9.000   1.8433   0.02676   0.01965  -0.1870   0.2906   1.0000
   9.250   1.8660   0.02706   0.01996  -0.1860   0.2848   1.0000
   9.500   1.8847   0.02729   0.02040  -0.1843   0.2779   1.0000
   9.750   1.9063   0.02749   0.02058  -0.1831   0.2720   1.0000
  10.000   1.9244   0.02789   0.02119  -0.1814   0.2654   1.0000
  10.250   1.9427   0.02813   0.02154  -0.1796   0.2585   1.0000
  10.500   1.9599   0.02852   0.02206  -0.1777   0.2513   1.0000
  10.750   1.9755   0.02885   0.02252  -0.1755   0.2432   1.0000
  11.000   1.9899   0.02934   0.02316  -0.1732   0.2344   1.0000
  11.250   2.0013   0.02988   0.02374  -0.1704   0.2254   1.0000
  11.500   2.0100   0.03057   0.02459  -0.1672   0.2145   1.0000
  11.750   2.0167   0.03143   0.02556  -0.1638   0.2031   1.0000
  12.000   2.0211   0.03256   0.02674  -0.1602   0.1907   1.0000
  12.250   2.0227   0.03402   0.02823  -0.1566   0.1774   1.0000
  12.500   2.0210   0.03586   0.03009  -0.1528   0.1640   1.0000
  12.750   2.0157   0.03813   0.03240  -0.1489   0.1517   1.0000
  13.000   2.0063   0.04091   0.03520  -0.1451   0.1410   1.0000
  13.250   1.9954   0.04409   0.03843  -0.1417   0.1314   1.0000
  13.500   1.9833   0.04766   0.04211  -0.1389   0.1230   1.0000
  13.750   1.9645   0.05226   0.04675  -0.1367   0.1172   1.0000
  14.000   1.9503   0.05692   0.05158  -0.1357   0.1108   1.0000
  14.250   1.9293   0.06309   0.05784  -0.1360   0.1064   1.0000
  14.500   1.9085   0.06985   0.06472  -0.1372   0.1023   1.0000
  14.750   1.8911   0.07653   0.07158  -0.1389   0.0979   1.0000
  15.000   1.8708   0.08380   0.07893  -0.1410   0.0946   1.0000
  15.250   1.8510   0.09095   0.08611  -0.1429   0.0912   1.0000
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