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S1221 w/ 4 deg flap (s1221-flap-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S1221 w/ 4 deg flap (s1221-flap-il)
Reynolds number: 100,000
Max Cl/Cd: 48.32 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1221-flap-il-100000.txt
Download as CSV file: xf-s1221-flap-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.500  -0.2809   0.09918   0.09507  -0.0151   1.0000   0.1152
  -6.250  -0.3153   0.09967   0.09573  -0.0161   1.0000   0.1176
  -6.000  -0.3132   0.09591   0.09206  -0.0149   1.0000   0.1193
  -5.750  -0.2969   0.09310   0.08927  -0.0110   1.0000   0.1221
  -5.500  -0.2938   0.09111   0.08736  -0.0095   1.0000   0.1260
  -5.250  -0.3107   0.08850   0.08492  -0.0224   1.0000   0.1337
  -5.000  -0.3061   0.08611   0.08260  -0.0145   1.0000   0.1352
  -4.750  -0.2947   0.08415   0.08070  -0.0115   0.9988   0.1384
  -4.500  -0.2159   0.07614   0.07260  -0.0458   0.9820   0.1644
  -4.250  -0.1926   0.07298   0.06949  -0.0395   0.9728   0.1665
  -4.000   0.0422   0.03059   0.02390  -0.1304   0.9919   0.0647
  -3.750   0.1166   0.02764   0.02042  -0.1398   0.9847   0.0646
  -3.500   0.1831   0.02493   0.01757  -0.1470   0.9750   0.0659
  -3.250   0.2459   0.02303   0.01577  -0.1531   0.9608   0.0704
  -3.000   0.3154   0.02117   0.01400  -0.1604   0.9438   0.0845
  -2.750   0.4000   0.01935   0.01305  -0.1708   0.9159   0.3314
  -2.500   0.4278   0.01960   0.01348  -0.1680   0.8515   0.3817
  -2.250   0.5196   0.01903   0.01242  -0.1762   0.7516   0.4324
  -2.000   0.5909   0.01929   0.01179  -0.1839   0.6809   0.4506
  -1.750   0.6280   0.01961   0.01170  -0.1854   0.6450   0.4609
  -1.500   0.6631   0.01972   0.01148  -0.1869   0.6179   0.4697
  -1.250   0.6964   0.01988   0.01134  -0.1879   0.5974   0.4782
  -1.000   0.7303   0.02000   0.01120  -0.1892   0.5803   0.4860
  -0.750   0.7613   0.02018   0.01120  -0.1898   0.5660   0.4935
  -0.500   0.7955   0.02034   0.01111  -0.1913   0.5531   0.5012
  -0.250   0.8256   0.02057   0.01119  -0.1916   0.5418   0.5088
   0.000   0.8580   0.02076   0.01126  -0.1926   0.5306   0.5181
   0.250   0.8885   0.02105   0.01141  -0.1930   0.5222   0.5261
   0.500   0.9196   0.02127   0.01160  -0.1938   0.5131   0.5360
   0.750   0.9506   0.02164   0.01181  -0.1943   0.5060   0.5474
   1.000   0.9788   0.02189   0.01216  -0.1943   0.4979   0.5589
   1.250   1.0093   0.02221   0.01241  -0.1948   0.4910   0.5726
   1.500   1.0389   0.02260   0.01281  -0.1951   0.4848   0.5877
   1.750   1.0674   0.02295   0.01325  -0.1952   0.4785   0.6049
   2.000   1.0960   0.02335   0.01363  -0.1952   0.4732   0.6250
   2.250   1.1233   0.02382   0.01420  -0.1949   0.4677   0.6484
   2.500   1.1487   0.02424   0.01477  -0.1943   0.4619   0.6736
   2.750   1.1750   0.02471   0.01528  -0.1937   0.4573   0.7043
   3.000   1.2007   0.02530   0.01586  -0.1930   0.4534   0.7395
   3.250   1.2225   0.02573   0.01657  -0.1917   0.4484   0.7801
   3.500   1.2437   0.02601   0.01699  -0.1902   0.4435   0.8308
   4.000   1.2881   0.02666   0.01768  -0.1879   0.4361   1.0000
   4.250   1.3175   0.02757   0.01875  -0.1887   0.4312   1.0000
   4.500   1.3468   0.02837   0.01958  -0.1893   0.4262   1.0000
   4.750   1.3765   0.02911   0.02025  -0.1898   0.4219   1.0000
   5.000   1.4051   0.03007   0.02121  -0.1901   0.4182   1.0000
   5.250   1.4281   0.03114   0.02251  -0.1896   0.4132   1.0000
   5.500   1.4541   0.03200   0.02344  -0.1894   0.4084   1.0000
   5.750   1.4822   0.03273   0.02415  -0.1894   0.4043   1.0000
   6.000   1.5068   0.03385   0.02536  -0.1891   0.4001   1.0000
   6.250   1.5269   0.03507   0.02683  -0.1881   0.3945   1.0000
   6.500   1.5527   0.03586   0.02768  -0.1878   0.3898   1.0000
   6.750   1.5817   0.03652   0.02826  -0.1879   0.3857   1.0000
   7.000   1.5971   0.03813   0.03022  -0.1863   0.3798   1.0000
   7.250   1.6195   0.03905   0.03127  -0.1855   0.3742   1.0000
   7.500   1.6489   0.03943   0.03158  -0.1855   0.3697   1.0000
   7.750   1.6636   0.04110   0.03355  -0.1838   0.3637   1.0000
   8.000   1.6836   0.04210   0.03473  -0.1827   0.3576   1.0000
   8.250   1.7147   0.04217   0.03470  -0.1828   0.3528   1.0000
   8.500   1.7250   0.04408   0.03696  -0.1806   0.3462   1.0000
   8.750   1.7475   0.04465   0.03763  -0.1796   0.3398   1.0000
   9.000   1.7843   0.04414   0.03691  -0.1804   0.3349   1.0000
   9.250   1.7844   0.04640   0.03969  -0.1768   0.3266   1.0000
   9.500   1.8196   0.04543   0.03856  -0.1771   0.3203   1.0000
   9.750   1.8274   0.04698   0.04045  -0.1743   0.3124   1.0000
  10.000   1.8576   0.04614   0.03954  -0.1740   0.3052   1.0000
  10.250   1.8707   0.04695   0.04056  -0.1717   0.2973   1.0000
  10.500   1.8976   0.04611   0.03970  -0.1709   0.2892   1.0000
  10.750   1.9090   0.04678   0.04057  -0.1683   0.2809   1.0000
  11.000   1.9365   0.04568   0.03939  -0.1675   0.2725   1.0000
  11.250   1.9391   0.04681   0.04082  -0.1638   0.2636   1.0000
  11.500   1.9690   0.04542   0.03925  -0.1632   0.2549   1.0000
  11.750   1.9600   0.04706   0.04130  -0.1580   0.2458   1.0000
  12.000   1.9689   0.04718   0.04146  -0.1549   0.2371   1.0000
  12.250   1.9666   0.04785   0.04224  -0.1503   0.2284   1.0000
  12.500   1.9566   0.04945   0.04404  -0.1454   0.2201   1.0000
  12.750   1.9589   0.05009   0.04462  -0.1420   0.2107   1.0000
  13.000   1.9418   0.05286   0.04765  -0.1375   0.2019   1.0000
  13.250   1.9316   0.05541   0.05026  -0.1343   0.1930   1.0000
  13.500   1.9263   0.05766   0.05240  -0.1318   0.1834   1.0000
  13.750   1.9015   0.06265   0.05770  -0.1296   0.1759   1.0000
  14.000   1.8901   0.06647   0.06149  -0.1284   0.1677   1.0000
  14.250   1.8681   0.07223   0.06741  -0.1283   0.1607   1.0000
  14.500   1.8550   0.07720   0.07239  -0.1285   0.1533   1.0000
  14.750   1.8358   0.08345   0.07877  -0.1298   0.1468   1.0000
  15.000   1.8273   0.08827   0.08357  -0.1305   0.1401   1.0000
  15.250   1.8081   0.09512   0.09058  -0.1326   0.1346   1.0000
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