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S1221 w/ 4 deg flap (s1221-flap-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S1221 w/ 4 deg flap (s1221-flap-il)
Reynolds number: 500,000
Max Cl/Cd: 104.59 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1221-flap-il-500000.txt
Download as CSV file: xf-s1221-flap-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2141   0.10117   0.09893  -0.0426   0.9873   0.0219
  -8.500  -0.2134   0.09422   0.09199  -0.0498   0.9846   0.0228
  -8.250  -0.2058   0.09006   0.08785  -0.0520   0.9817   0.0231
  -8.000  -0.1869   0.08783   0.08563  -0.0537   0.9797   0.0234
  -7.750  -0.1660   0.08505   0.08284  -0.0570   0.9780   0.0240
  -7.500  -0.1548   0.08192   0.07973  -0.0592   0.9741   0.0246
  -7.250  -0.1436   0.07767   0.07549  -0.0634   0.9701   0.0261
  -7.000  -0.1671   0.06519   0.06304  -0.0755   0.9616   0.0273
  -6.750  -0.1434   0.06476   0.06264  -0.0751   0.9585   0.0279
  -6.500  -0.1122   0.06239   0.06026  -0.0796   0.9560   0.0285
  -6.250  -0.1012   0.05882   0.05671  -0.0827   0.9487   0.0292
  -6.000  -0.0072   0.03016   0.02717  -0.1474   0.9438   0.0340
  -5.750   0.0575   0.02731   0.02387  -0.1586   0.9420   0.0381
  -5.500   0.1412   0.01704   0.01243  -0.1745   0.9416   0.0218
  -5.250   0.1792   0.01474   0.00978  -0.1768   0.9341   0.0197
  -5.000   0.2254   0.01339   0.00828  -0.1803   0.9279   0.0193
  -4.750   0.2664   0.01231   0.00715  -0.1829   0.9157   0.0195
  -4.500   0.3351   0.01101   0.00577  -0.1914   0.8926   0.0202
  -4.250   0.4087   0.01115   0.00484  -0.2008   0.6817   0.0216
  -4.000   0.4354   0.01124   0.00459  -0.2005   0.6194   0.0224
  -3.750   0.4657   0.01115   0.00420  -0.2011   0.5723   0.0237
  -3.500   0.4954   0.01114   0.00398  -0.2015   0.5390   0.0261
  -3.250   0.5270   0.01105   0.00371  -0.2023   0.5141   0.0301
  -3.000   0.5727   0.01012   0.00325  -0.2070   0.4928   0.2171
  -2.750   0.6013   0.01025   0.00332  -0.2069   0.4773   0.2615
  -2.500   0.6294   0.01040   0.00338  -0.2067   0.4638   0.2793
  -2.250   0.6572   0.01060   0.00349  -0.2065   0.4518   0.2972
  -2.000   0.6850   0.01079   0.00361  -0.2062   0.4410   0.3139
  -1.750   0.7128   0.01099   0.00374  -0.2059   0.4318   0.3258
  -1.500   0.7414   0.01108   0.00377  -0.2059   0.4230   0.3331
  -1.250   0.7699   0.01118   0.00381  -0.2057   0.4153   0.3381
  -1.000   0.7984   0.01129   0.00384  -0.2056   0.4078   0.3427
  -0.750   0.8269   0.01141   0.00387  -0.2055   0.4009   0.3466
  -0.500   0.8560   0.01144   0.00391  -0.2056   0.3944   0.3509
  -0.250   0.8844   0.01157   0.00398  -0.2055   0.3881   0.3555
   0.000   0.9127   0.01171   0.00406  -0.2054   0.3828   0.3608
   0.250   0.9418   0.01177   0.00413  -0.2054   0.3778   0.3665
   0.500   0.9702   0.01189   0.00422  -0.2053   0.3728   0.3726
   0.750   0.9981   0.01210   0.00435  -0.2052   0.3678   0.3791
   1.000   1.0273   0.01214   0.00445  -0.2052   0.3638   0.3866
   1.250   1.0557   0.01226   0.00457  -0.2051   0.3597   0.3954
   1.500   1.0843   0.01239   0.00471  -0.2051   0.3559   0.4049
   1.750   1.1122   0.01263   0.00490  -0.2050   0.3519   0.4162
   2.000   1.1409   0.01273   0.00506  -0.2050   0.3489   0.4297
   2.250   1.1696   0.01282   0.00521  -0.2050   0.3454   0.4451
   2.500   1.1980   0.01295   0.00538  -0.2049   0.3421   0.4623
   2.750   1.2262   0.01312   0.00558  -0.2048   0.3390   0.4817
   3.000   1.2544   0.01338   0.00584  -0.2048   0.3356   0.5037
   3.250   1.2830   0.01352   0.00608  -0.2048   0.3332   0.5292
   3.500   1.3115   0.01363   0.00629  -0.2048   0.3305   0.5576
   3.750   1.3398   0.01375   0.00652  -0.2047   0.3275   0.5903
   4.000   1.3680   0.01390   0.00676  -0.2046   0.3246   0.6293
   4.250   1.3956   0.01410   0.00706  -0.2045   0.3219   0.6780
   4.500   1.4223   0.01447   0.00747  -0.2041   0.3185   0.7249
   4.750   1.4490   0.01459   0.00769  -0.2036   0.3162   0.7572
   5.000   1.4756   0.01474   0.00792  -0.2032   0.3133   0.7804
   5.250   1.5022   0.01491   0.00814  -0.2028   0.3101   0.8000
   5.500   1.5284   0.01508   0.00834  -0.2023   0.3067   0.8179
   5.750   1.5542   0.01542   0.00867  -0.2018   0.3027   0.8370
   6.000   1.5793   0.01548   0.00889  -0.2011   0.3001   0.8641
   6.250   1.5970   0.01543   0.00900  -0.1987   0.2974   1.0000
   6.500   1.6238   0.01564   0.00923  -0.1984   0.2942   1.0000
   6.750   1.6501   0.01589   0.00949  -0.1980   0.2908   1.0000
   7.000   1.6760   0.01633   0.00987  -0.1977   0.2867   1.0000
   7.250   1.7021   0.01644   0.01009  -0.1972   0.2833   1.0000
   7.500   1.7278   0.01660   0.01031  -0.1967   0.2790   1.0000
   7.750   1.7529   0.01682   0.01053  -0.1961   0.2741   1.0000
   8.000   1.7777   0.01712   0.01084  -0.1955   0.2690   1.0000
   8.250   1.8032   0.01724   0.01106  -0.1950   0.2637   1.0000
   8.500   1.8277   0.01750   0.01133  -0.1943   0.2587   1.0000
   8.750   1.8518   0.01782   0.01168  -0.1936   0.2538   1.0000
   9.000   1.8768   0.01802   0.01198  -0.1930   0.2483   1.0000
   9.250   1.9001   0.01834   0.01230  -0.1921   0.2418   1.0000
   9.500   1.9243   0.01861   0.01265  -0.1914   0.2350   1.0000
   9.750   1.9468   0.01899   0.01303  -0.1904   0.2269   1.0000
  10.000   1.9698   0.01935   0.01345  -0.1896   0.2181   1.0000
  10.250   1.9911   0.01985   0.01394  -0.1884   0.2070   1.0000
  10.500   2.0109   0.02047   0.01453  -0.1871   0.1939   1.0000
  10.750   2.0291   0.02122   0.01526  -0.1855   0.1789   1.0000
  11.000   2.0450   0.02215   0.01613  -0.1836   0.1626   1.0000
  11.250   2.0573   0.02328   0.01720  -0.1810   0.1464   1.0000
  11.500   2.0669   0.02447   0.01834  -0.1781   0.1325   1.0000
  11.750   2.0739   0.02580   0.01962  -0.1748   0.1187   1.0000
  12.000   2.0801   0.02719   0.02099  -0.1714   0.1067   1.0000
  12.250   2.0855   0.02864   0.02245  -0.1681   0.0961   1.0000
  12.500   2.0894   0.03021   0.02404  -0.1646   0.0872   1.0000
  12.750   2.0905   0.03203   0.02587  -0.1610   0.0791   1.0000
  13.000   2.0903   0.03398   0.02785  -0.1575   0.0720   1.0000
  13.250   2.0899   0.03602   0.02995  -0.1542   0.0663   1.0000
  13.500   2.0857   0.03847   0.03246  -0.1508   0.0619   1.0000
  13.750   2.0818   0.04103   0.03511  -0.1478   0.0581   1.0000
  14.000   2.0769   0.04384   0.03803  -0.1452   0.0555   1.0000
  14.250   2.0657   0.04752   0.04182  -0.1429   0.0530   1.0000
  14.500   2.0496   0.05221   0.04664  -0.1413   0.0509   1.0000
  14.750   2.0395   0.05680   0.05140  -0.1410   0.0497   1.0000
  15.000   2.0256   0.06255   0.05733  -0.1419   0.0485   1.0000
  15.250   2.0058   0.06980   0.06477  -0.1439   0.0478   1.0000
  15.500   1.9825   0.07805   0.07320  -0.1465   0.0468   1.0000
  15.750   1.9560   0.08694   0.08227  -0.1494   0.0462   1.0000
  16.000   1.9286   0.09601   0.09150  -0.1524   0.0455   1.0000
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