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S1221 w/ 4 deg flap (s1221-flap-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S1221 w/ 4 deg flap (s1221-flap-il)
Reynolds number: 1,000,000
Max Cl/Cd: 129.46 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1221-flap-il-1000000-n5.txt
Download as CSV file: xf-s1221-flap-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.1910   0.10068   0.09886  -0.0614   0.9655   0.0071
 -10.000  -0.1857   0.09728   0.09546  -0.0627   0.9593   0.0070
  -9.250  -0.3235   0.04158   0.03923  -0.1076   0.9417   0.0073
  -8.750  -0.2213   0.02048   0.01717  -0.1623   0.9275   0.0074
  -8.500  -0.1686   0.01763   0.01403  -0.1722   0.9230   0.0075
  -8.250  -0.1185   0.01586   0.01205  -0.1792   0.9163   0.0076
  -8.000  -0.0606   0.01458   0.01059  -0.1872   0.9067   0.0077
  -7.750  -0.0053   0.01369   0.00952  -0.1940   0.8871   0.0079
  -7.500   0.0171   0.01394   0.00897  -0.1932   0.7098   0.0080
  -7.250   0.0436   0.01365   0.00837  -0.1936   0.6548   0.0081
  -7.000   0.0730   0.01325   0.00769  -0.1944   0.6072   0.0082
  -6.750   0.1036   0.01287   0.00707  -0.1954   0.5661   0.0083
  -6.500   0.1350   0.01251   0.00651  -0.1965   0.5345   0.0084
  -6.250   0.1671   0.01217   0.00600  -0.1977   0.5098   0.0085
  -6.000   0.1994   0.01185   0.00553  -0.1988   0.4900   0.0087
  -5.750   0.2317   0.01157   0.00511  -0.1999   0.4727   0.0089
  -5.500   0.2640   0.01132   0.00474  -0.2009   0.4575   0.0091
  -5.250   0.2960   0.01110   0.00441  -0.2018   0.4447   0.0093
  -5.000   0.3277   0.01092   0.00413  -0.2026   0.4340   0.0096
  -4.750   0.3590   0.01077   0.00390  -0.2033   0.4241   0.0097
  -4.500   0.3919   0.01052   0.00356  -0.2043   0.4154   0.0102
  -4.250   0.4233   0.01038   0.00334  -0.2050   0.4068   0.0106
  -4.000   0.4541   0.01028   0.00318  -0.2055   0.3994   0.0110
  -3.750   0.4847   0.01020   0.00303  -0.2059   0.3921   0.0115
  -3.500   0.5150   0.01015   0.00291  -0.2063   0.3846   0.0120
  -3.250   0.5454   0.01009   0.00280  -0.2066   0.3781   0.0128
  -3.000   0.5757   0.01005   0.00271  -0.2070   0.3706   0.0146
  -2.750   0.6063   0.00999   0.00262  -0.2074   0.3651   0.0197
  -2.500   0.6385   0.00983   0.00253  -0.2082   0.3596   0.0514
  -2.250   0.6729   0.00956   0.00242  -0.2097   0.3537   0.1260
  -2.000   0.7069   0.00931   0.00240  -0.2112   0.3491   0.2203
  -1.750   0.7366   0.00932   0.00245  -0.2114   0.3446   0.2512
  -1.500   0.7656   0.00937   0.00250  -0.2114   0.3396   0.2678
  -1.250   0.7941   0.00946   0.00255  -0.2113   0.3346   0.2781
  -1.000   0.8230   0.00950   0.00259  -0.2112   0.3307   0.2846
  -0.750   0.8517   0.00957   0.00262  -0.2112   0.3268   0.2874
  -0.500   0.8802   0.00966   0.00267  -0.2110   0.3229   0.2900
   0.000   0.9372   0.00982   0.00277  -0.2108   0.3159   0.2964
   0.250   0.9658   0.00989   0.00284  -0.2107   0.3126   0.3007
   0.500   0.9942   0.00997   0.00291  -0.2106   0.3094   0.3046
   0.750   1.0224   0.01008   0.00298  -0.2105   0.3063   0.3082
   1.000   1.0506   0.01018   0.00307  -0.2103   0.3032   0.3122
   1.250   1.0790   0.01026   0.00316  -0.2102   0.3010   0.3175
   1.500   1.1073   0.01034   0.00325  -0.2101   0.2987   0.3228
   2.000   1.1636   0.01053   0.00346  -0.2098   0.2937   0.3345
   2.250   1.1915   0.01065   0.00357  -0.2096   0.2913   0.3414
   2.500   1.2195   0.01077   0.00370  -0.2094   0.2889   0.3489
   2.750   1.2473   0.01090   0.00384  -0.2092   0.2864   0.3585
   3.000   1.2754   0.01098   0.00396  -0.2091   0.2849   0.3679
   3.250   1.3033   0.01108   0.00409  -0.2089   0.2830   0.3779
   3.500   1.3313   0.01118   0.00424  -0.2088   0.2809   0.3890
   3.750   1.3590   0.01130   0.00438  -0.2086   0.2788   0.4006
   4.000   1.3867   0.01143   0.00454  -0.2084   0.2764   0.4137
   4.250   1.4142   0.01158   0.00471  -0.2082   0.2732   0.4282
   4.500   1.4416   0.01173   0.00490  -0.2080   0.2702   0.4434
   4.750   1.4694   0.01183   0.00505  -0.2078   0.2677   0.4597
   5.000   1.4970   0.01195   0.00522  -0.2077   0.2641   0.4786
   5.250   1.5244   0.01209   0.00541  -0.2075   0.2604   0.5005
   5.500   1.5517   0.01226   0.00562  -0.2073   0.2571   0.5236
   5.750   1.5790   0.01241   0.00583  -0.2070   0.2544   0.5471
   6.000   1.6065   0.01253   0.00603  -0.2069   0.2513   0.5727
   6.250   1.6338   0.01268   0.00625  -0.2067   0.2474   0.6023
   6.500   1.6608   0.01289   0.00650  -0.2064   0.2414   0.6363
   6.750   1.6881   0.01304   0.00676  -0.2063   0.2360   0.6857
   7.000   1.7141   0.01331   0.00705  -0.2059   0.2270   0.7268
   7.250   1.7396   0.01359   0.00733  -0.2053   0.2168   0.7496
   7.500   1.7646   0.01393   0.00764  -0.2048   0.2068   0.7627
   7.750   1.7893   0.01430   0.00798  -0.2041   0.1970   0.7736
   8.000   1.8138   0.01467   0.00833  -0.2035   0.1869   0.7838
   8.250   1.8374   0.01517   0.00877  -0.2027   0.1727   0.7936
   8.500   1.8601   0.01576   0.00929  -0.2018   0.1574   0.8027
   8.750   1.8827   0.01636   0.00984  -0.2008   0.1435   0.8115
   9.000   1.9049   0.01696   0.01040  -0.1999   0.1309   0.8201
   9.250   1.9266   0.01760   0.01101  -0.1988   0.1185   0.8300
   9.500   1.9478   0.01828   0.01167  -0.1977   0.1064   0.8455
   9.750   1.9637   0.01870   0.01220  -0.1954   0.0980   1.0000
  10.000   1.9841   0.01939   0.01285  -0.1941   0.0892   1.0000
  10.250   2.0033   0.02016   0.01358  -0.1926   0.0798   1.0000
  10.500   2.0207   0.02106   0.01442  -0.1909   0.0690   1.0000
  10.750   2.0372   0.02198   0.01530  -0.1891   0.0600   1.0000
  11.000   2.0534   0.02284   0.01616  -0.1871   0.0535   1.0000
  11.250   2.0683   0.02373   0.01705  -0.1849   0.0482   1.0000
  11.500   2.0801   0.02466   0.01799  -0.1822   0.0442   1.0000
  11.750   2.0913   0.02551   0.01888  -0.1794   0.0411   1.0000
  12.000   2.1015   0.02648   0.01988  -0.1765   0.0380   1.0000
  12.250   2.1107   0.02753   0.02096  -0.1735   0.0354   1.0000
  12.500   2.1210   0.02853   0.02201  -0.1708   0.0337   1.0000
  12.750   2.1292   0.02970   0.02323  -0.1679   0.0319   1.0000
  13.000   2.1350   0.03107   0.02465  -0.1648   0.0299   1.0000
  13.250   2.1425   0.03233   0.02599  -0.1620   0.0288   1.0000
  13.500   2.1476   0.03382   0.02755  -0.1592   0.0274   1.0000
  13.750   2.1511   0.03549   0.02929  -0.1563   0.0264   1.0000
  14.000   2.1510   0.03755   0.03141  -0.1533   0.0248   1.0000
  14.250   2.1536   0.03946   0.03341  -0.1508   0.0242   1.0000
  14.500   2.1541   0.04166   0.03571  -0.1484   0.0235   1.0000
  14.750   2.1511   0.04432   0.03847  -0.1461   0.0225   1.0000
  15.000   2.1449   0.04753   0.04177  -0.1441   0.0217   1.0000
  15.250   2.1364   0.05132   0.04568  -0.1427   0.0211   1.0000
  15.500   2.1238   0.05619   0.05069  -0.1424   0.0204   1.0000
  15.750   2.1116   0.06167   0.05632  -0.1432   0.0200   1.0000
  16.000   2.0956   0.06824   0.06305  -0.1448   0.0195   1.0000
  16.250   2.0756   0.07583   0.07082  -0.1471   0.0193   1.0000
  16.500   2.0507   0.08448   0.07965  -0.1499   0.0191   1.0000
  16.750   2.0229   0.09364   0.08898  -0.1529   0.0190   1.0000
  17.000   1.9941   0.10299   0.09850  -0.1561   0.0188   1.0000
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