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S1221 w/ 4 deg flap (s1221-flap-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S1221 w/ 4 deg flap (s1221-flap-il)
Reynolds number: 500,000
Max Cl/Cd: 106.53 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1221-flap-il-500000-n5.txt
Download as CSV file: xf-s1221-flap-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.1580   0.08808   0.08566  -0.0638   0.9588   0.0112
  -8.500  -0.1510   0.08320   0.08079  -0.0673   0.9557   0.0108
  -8.000  -0.2552   0.03960   0.03671  -0.1062   0.9370   0.0097
  -7.750  -0.1853   0.02548   0.02181  -0.1444   0.9312   0.0099
  -7.500  -0.1345   0.02228   0.01832  -0.1541   0.9282   0.0102
  -7.250  -0.0881   0.02020   0.01601  -0.1607   0.9247   0.0104
  -7.000  -0.0485   0.01839   0.01395  -0.1650   0.9179   0.0105
  -6.750   0.0020   0.01657   0.01187  -0.1711   0.9117   0.0106
  -6.500   0.0513   0.01518   0.01027  -0.1764   0.9006   0.0107
  -6.250   0.1278   0.01375   0.00854  -0.1873   0.8725   0.0110
  -6.000   0.1775   0.01382   0.00761  -0.1921   0.6783   0.0112
  -5.750   0.2055   0.01357   0.00706  -0.1925   0.6273   0.0114
  -5.500   0.2350   0.01331   0.00653  -0.1931   0.5828   0.0117
  -5.250   0.2659   0.01305   0.00604  -0.1940   0.5484   0.0120
  -5.000   0.2974   0.01282   0.00561  -0.1949   0.5223   0.0123
  -4.750   0.3307   0.01251   0.00514  -0.1963   0.5008   0.0127
  -4.500   0.3635   0.01227   0.00475  -0.1975   0.4825   0.0133
  -4.250   0.3954   0.01210   0.00446  -0.1983   0.4671   0.0138
  -3.750   0.4582   0.01186   0.00399  -0.1997   0.4430   0.0157
  -3.500   0.4898   0.01173   0.00377  -0.2005   0.4332   0.0174
  -3.250   0.5210   0.01164   0.00359  -0.2010   0.4238   0.0194
  -3.000   0.5527   0.01153   0.00343  -0.2017   0.4156   0.0265
  -2.750   0.5868   0.01127   0.00326  -0.2032   0.4072   0.0711
  -2.500   0.6238   0.01085   0.00310  -0.2055   0.3994   0.1830
  -2.250   0.6546   0.01081   0.00318  -0.2061   0.3916   0.2495
  -2.000   0.6831   0.01093   0.00325  -0.2060   0.3846   0.2749
  -1.750   0.7120   0.01100   0.00331  -0.2059   0.3788   0.2906
  -1.500   0.7408   0.01108   0.00335  -0.2059   0.3729   0.2985
  -1.250   0.7694   0.01117   0.00338  -0.2058   0.3676   0.3032
  -1.000   0.7982   0.01124   0.00340  -0.2058   0.3629   0.3067
  -0.750   0.8268   0.01133   0.00343  -0.2057   0.3578   0.3097
  -0.500   0.8554   0.01143   0.00349  -0.2056   0.3528   0.3132
  -0.250   0.8841   0.01151   0.00355  -0.2056   0.3484   0.3177
   0.000   0.9127   0.01160   0.00361  -0.2055   0.3439   0.3222
   0.250   0.9410   0.01171   0.00369  -0.2054   0.3398   0.3263
   0.500   0.9693   0.01183   0.00378  -0.2053   0.3360   0.3308
   0.750   0.9978   0.01193   0.00388  -0.2052   0.3326   0.3361
   1.000   1.0262   0.01203   0.00397  -0.2051   0.3289   0.3418
   1.250   1.0544   0.01214   0.00408  -0.2049   0.3252   0.3476
   1.500   1.0826   0.01227   0.00421  -0.2048   0.3220   0.3546
   1.750   1.1104   0.01243   0.00435  -0.2046   0.3189   0.3623
   2.000   1.1388   0.01254   0.00450  -0.2046   0.3165   0.3714
   2.250   1.1670   0.01265   0.00464  -0.2044   0.3136   0.3809
   2.500   1.1951   0.01278   0.00479  -0.2043   0.3105   0.3914
   2.750   1.2229   0.01292   0.00496  -0.2041   0.3076   0.4023
   3.250   1.2782   0.01328   0.00534  -0.2038   0.3025   0.4285
   3.500   1.3062   0.01340   0.00553  -0.2036   0.3007   0.4435
   3.750   1.3341   0.01354   0.00574  -0.2035   0.2983   0.4598
   4.000   1.3619   0.01368   0.00594  -0.2033   0.2956   0.4785
   4.250   1.3895   0.01384   0.00616  -0.2032   0.2930   0.4997
   4.500   1.4170   0.01402   0.00641  -0.2030   0.2906   0.5230
   4.750   1.4442   0.01423   0.00666  -0.2028   0.2879   0.5475
   5.000   1.4716   0.01440   0.00692  -0.2026   0.2852   0.5742
   5.250   1.4993   0.01454   0.00717  -0.2024   0.2824   0.6049
   5.500   1.5267   0.01469   0.00744  -0.2022   0.2789   0.6409
   5.750   1.5535   0.01488   0.00773  -0.2019   0.2750   0.6874
   6.000   1.5793   0.01513   0.00804  -0.2014   0.2714   0.7275
   6.250   1.6056   0.01532   0.00831  -0.2009   0.2687   0.7541
   6.500   1.6319   0.01551   0.00857  -0.2005   0.2655   0.7715
   6.750   1.6579   0.01573   0.00884  -0.2000   0.2617   0.7853
   7.000   1.6835   0.01598   0.00912  -0.1995   0.2575   0.7985
   7.250   1.7091   0.01620   0.00940  -0.1990   0.2531   0.8116
   7.500   1.7348   0.01639   0.00968  -0.1985   0.2474   0.8264
   8.000   1.7758   0.01667   0.01014  -0.1953   0.2334   1.0000
   8.250   1.8001   0.01704   0.01049  -0.1946   0.2243   1.0000
   8.500   1.8245   0.01740   0.01085  -0.1940   0.2154   1.0000
   8.750   1.8482   0.01781   0.01126  -0.1932   0.2066   1.0000
   9.000   1.8709   0.01831   0.01174  -0.1923   0.1963   1.0000
   9.250   1.8927   0.01890   0.01229  -0.1913   0.1831   1.0000
   9.500   1.9135   0.01958   0.01292  -0.1902   0.1683   1.0000
   9.750   1.9331   0.02036   0.01364  -0.1888   0.1535   1.0000
  10.000   1.9517   0.02121   0.01444  -0.1873   0.1400   1.0000
  10.250   1.9690   0.02212   0.01532  -0.1856   0.1270   1.0000
  10.500   1.9848   0.02311   0.01627  -0.1837   0.1148   1.0000
  10.750   1.9988   0.02416   0.01729  -0.1814   0.1041   1.0000
  11.000   2.0115   0.02511   0.01827  -0.1789   0.0954   1.0000
  11.250   2.0222   0.02614   0.01931  -0.1761   0.0878   1.0000
  11.500   2.0310   0.02731   0.02049  -0.1731   0.0803   1.0000
  11.750   2.0393   0.02852   0.02172  -0.1701   0.0728   1.0000
  12.000   2.0461   0.02985   0.02308  -0.1670   0.0664   1.0000
  12.500   2.0565   0.03282   0.02615  -0.1608   0.0563   1.0000
  12.750   2.0590   0.03457   0.02795  -0.1576   0.0523   1.0000
  13.000   2.0615   0.03637   0.02984  -0.1547   0.0492   1.0000
  13.250   2.0616   0.03844   0.03198  -0.1517   0.0458   1.0000
  13.500   2.0588   0.04089   0.03452  -0.1488   0.0433   1.0000
  13.750   2.0569   0.04338   0.03712  -0.1464   0.0411   1.0000
  14.000   2.0531   0.04623   0.04009  -0.1442   0.0396   1.0000
  14.250   2.0449   0.04981   0.04378  -0.1424   0.0380   1.0000
  14.500   2.0316   0.05446   0.04856  -0.1415   0.0364   1.0000
  14.750   2.0193   0.05967   0.05395  -0.1419   0.0357   1.0000
  15.000   2.0054   0.06571   0.06018  -0.1432   0.0350   1.0000
  15.250   1.9879   0.07279   0.06745  -0.1453   0.0349   1.0000
  15.500   1.9658   0.08091   0.07576  -0.1479   0.0340   1.0000
  15.750   1.9414   0.08948   0.08451  -0.1507   0.0336   1.0000
  16.000   1.9160   0.09822   0.09342  -0.1537   0.0331   1.0000
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