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S1221 w/ 4 deg flap (s1221-flap-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S1221 w/ 4 deg flap (s1221-flap-il)
Reynolds number: 1,000,000
Max Cl/Cd: 133.83 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1221-flap-il-1000000.txt
Download as CSV file: xf-s1221-flap-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.1843   0.10088   0.09916  -0.0587   0.9845   0.0128
  -9.500  -0.1735   0.09813   0.09641  -0.0601   0.9820   0.0130
  -9.250  -0.1613   0.09458   0.09287  -0.0630   0.9801   0.0130
  -9.000  -0.1473   0.09128   0.08957  -0.0659   0.9786   0.0132
  -8.750  -0.1307   0.08788   0.08617  -0.0695   0.9773   0.0136
  -8.500  -0.1269   0.08487   0.08318  -0.0701   0.9719   0.0137
  -8.250  -0.1155   0.08098   0.07929  -0.0734   0.9695   0.0142
  -8.000  -0.1137   0.07097   0.06929  -0.0822   0.9671   0.0155
  -7.000  -0.0192   0.01109   0.00836  -0.1587   0.9353   0.0193
  -6.750   0.0163   0.00955   0.00686  -0.1621   0.9303   0.0198
  -6.500   0.0691   0.00793   0.00507  -0.1702   0.9254   0.0206
  -6.250   0.1170   0.01344   0.00952  -0.1859   0.9292   0.0138
  -6.000   0.1684   0.01200   0.00787  -0.1914   0.9204   0.0136
  -5.750   0.2378   0.01061   0.00624  -0.2005   0.9011   0.0132
  -5.500   0.2767   0.01071   0.00552  -0.2028   0.7261   0.0131
  -5.250   0.3009   0.01073   0.00516  -0.2022   0.6522   0.0132
  -5.000   0.3297   0.01059   0.00474  -0.2025   0.5963   0.0134
  -4.750   0.3601   0.01044   0.00436  -0.2032   0.5542   0.0137
  -4.250   0.4229   0.01016   0.00374  -0.2047   0.5008   0.0148
  -4.000   0.4541   0.01005   0.00350  -0.2053   0.4826   0.0154
  -3.750   0.4866   0.00987   0.00319  -0.2062   0.4672   0.0161
  -3.500   0.5177   0.00978   0.00300  -0.2068   0.4532   0.0172
  -3.250   0.5484   0.00972   0.00285  -0.2072   0.4412   0.0184
  -3.000   0.5793   0.00965   0.00271  -0.2077   0.4303   0.0215
  -2.750   0.6199   0.00901   0.00242  -0.2109   0.4191   0.1571
  -2.500   0.6524   0.00884   0.00243  -0.2119   0.4107   0.2419
  -2.250   0.6810   0.00893   0.00247  -0.2118   0.4019   0.2592
  -2.000   0.7101   0.00897   0.00251  -0.2118   0.3951   0.2718
  -1.750   0.7385   0.00907   0.00257  -0.2117   0.3874   0.2855
  -1.500   0.7668   0.00916   0.00262  -0.2115   0.3811   0.2960
  -1.250   0.7953   0.00924   0.00269  -0.2114   0.3744   0.3049
  -1.000   0.8232   0.00938   0.00274  -0.2111   0.3676   0.3095
  -0.750   0.8525   0.00940   0.00276  -0.2112   0.3628   0.3140
  -0.500   0.8813   0.00948   0.00281  -0.2112   0.3575   0.3179
  -0.250   0.9095   0.00960   0.00288  -0.2110   0.3514   0.3218
   0.000   0.9382   0.00966   0.00292  -0.2109   0.3478   0.3256
   0.250   0.9668   0.00973   0.00298  -0.2109   0.3434   0.3304
   0.500   0.9953   0.00983   0.00306  -0.2108   0.3391   0.3361
   0.750   1.0234   0.00997   0.00316  -0.2106   0.3346   0.3417
   1.000   1.0520   0.01002   0.00323  -0.2105   0.3321   0.3476
   1.250   1.0807   0.01009   0.00332  -0.2105   0.3288   0.3552
   1.500   1.1088   0.01020   0.00341  -0.2103   0.3253   0.3624
   1.750   1.1371   0.01032   0.00353  -0.2102   0.3217   0.3724
   2.000   1.1649   0.01048   0.00368  -0.2101   0.3182   0.3825
   2.250   1.1935   0.01054   0.00379  -0.2100   0.3164   0.3947
   2.500   1.2219   0.01062   0.00391  -0.2099   0.3142   0.4085
   2.750   1.2502   0.01072   0.00405  -0.2098   0.3116   0.4244
   3.000   1.2782   0.01083   0.00419  -0.2097   0.3088   0.4418
   3.250   1.3060   0.01099   0.00436  -0.2096   0.3057   0.4602
   3.500   1.3335   0.01119   0.00458  -0.2093   0.3023   0.4801
   3.750   1.3618   0.01126   0.00473  -0.2093   0.3009   0.5019
   4.000   1.3901   0.01134   0.00488  -0.2092   0.2988   0.5262
   4.250   1.4183   0.01143   0.00504  -0.2091   0.2962   0.5525
   4.500   1.4462   0.01155   0.00522  -0.2090   0.2933   0.5828
   4.750   1.4739   0.01172   0.00543  -0.2089   0.2896   0.6171
   5.000   1.5016   0.01190   0.00570  -0.2087   0.2859   0.6624
   5.250   1.5295   0.01196   0.00591  -0.2086   0.2839   0.7154
   5.500   1.5566   0.01209   0.00610  -0.2083   0.2815   0.7464
   5.750   1.5833   0.01224   0.00629  -0.2079   0.2789   0.7656
   6.000   1.6098   0.01242   0.00649  -0.2075   0.2757   0.7797
   6.250   1.6356   0.01268   0.00674  -0.2069   0.2717   0.7915
   6.500   1.6624   0.01280   0.00692  -0.2066   0.2688   0.8024
   6.750   1.6893   0.01290   0.00707  -0.2063   0.2653   0.8133
   7.000   1.7157   0.01305   0.00724  -0.2059   0.2604   0.8247
   7.250   1.7413   0.01327   0.00748  -0.2054   0.2547   0.8378
   7.500   1.7678   0.01336   0.00766  -0.2050   0.2507   0.8549
   7.750   1.7879   0.01336   0.00781  -0.2033   0.2464   1.0000
   8.000   1.8134   0.01365   0.00808  -0.2028   0.2409   1.0000
   8.250   1.8395   0.01384   0.00830  -0.2024   0.2360   1.0000
   8.500   1.8648   0.01411   0.00857  -0.2018   0.2290   1.0000
   8.750   1.8899   0.01440   0.00886  -0.2013   0.2223   1.0000
   9.000   1.9143   0.01476   0.00919  -0.2006   0.2131   1.0000
   9.250   1.9385   0.01514   0.00954  -0.1999   0.2031   1.0000
   9.500   1.9615   0.01563   0.00998  -0.1991   0.1901   1.0000
   9.750   1.9837   0.01622   0.01050  -0.1981   0.1757   1.0000
  10.000   2.0043   0.01696   0.01114  -0.1969   0.1590   1.0000
  10.250   2.0237   0.01781   0.01189  -0.1955   0.1418   1.0000
  10.500   2.0420   0.01873   0.01271  -0.1940   0.1241   1.0000
  10.750   2.0595   0.01967   0.01357  -0.1923   0.1092   1.0000
  11.000   2.0765   0.02058   0.01442  -0.1905   0.0972   1.0000
  11.250   2.0923   0.02155   0.01534  -0.1885   0.0861   1.0000
  11.500   2.1067   0.02255   0.01630  -0.1863   0.0767   1.0000
  11.750   2.1180   0.02362   0.01735  -0.1835   0.0682   1.0000
  12.000   2.1264   0.02470   0.01842  -0.1802   0.0613   1.0000
  12.250   2.1359   0.02571   0.01946  -0.1772   0.0560   1.0000
  12.500   2.1427   0.02694   0.02069  -0.1738   0.0508   1.0000
  12.750   2.1520   0.02801   0.02181  -0.1710   0.0476   1.0000
  13.000   2.1567   0.02944   0.02326  -0.1676   0.0438   1.0000
  13.250   2.1639   0.03069   0.02458  -0.1646   0.0415   1.0000
  13.500   2.1681   0.03222   0.02616  -0.1615   0.0390   1.0000
  13.750   2.1699   0.03398   0.02797  -0.1582   0.0369   1.0000
  14.000   2.1733   0.03567   0.02974  -0.1554   0.0352   1.0000
  14.250   2.1757   0.03752   0.03168  -0.1526   0.0340   1.0000
  14.500   2.1751   0.03973   0.03397  -0.1499   0.0328   1.0000
  14.750   2.1702   0.04245   0.03677  -0.1471   0.0314   1.0000
  15.000   2.1628   0.04564   0.04006  -0.1447   0.0301   1.0000
  15.250   2.1583   0.04876   0.04331  -0.1431   0.0296   1.0000
  15.500   2.1507   0.05258   0.04726  -0.1420   0.0290   1.0000
  15.750   2.1400   0.05737   0.05219  -0.1420   0.0284   1.0000
  16.000   2.1253   0.06332   0.05830  -0.1430   0.0278   1.0000
  16.250   2.1059   0.07055   0.06569  -0.1450   0.0274   1.0000
  16.500   2.0817   0.07896   0.07428  -0.1476   0.0271   1.0000
  16.750   2.0532   0.08822   0.08373  -0.1506   0.0269   1.0000
  17.000   2.0216   0.09806   0.09375  -0.1539   0.0268   1.0000
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