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SOKOLOV AIRFOIL (sokolov-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SOKOLOV AIRFOIL (sokolov-il)
Reynolds number: 50,000
Max Cl/Cd: 45.15 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sokolov-il-50000-n5.txt
Download as CSV file: xf-sokolov-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SOKOLOV AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2803   0.11133   0.10488  -0.0328   1.0000   0.0771
  -7.500  -0.2910   0.11099   0.10470  -0.0317   1.0000   0.0777
  -7.250  -0.2994   0.11045   0.10431  -0.0317   1.0000   0.0780
  -7.000  -0.2879   0.10488   0.09876  -0.0282   1.0000   0.0813
  -6.750  -0.2911   0.10318   0.09717  -0.0266   1.0000   0.0847
  -6.500  -0.2985   0.10232   0.09643  -0.0260   1.0000   0.0876
  -6.250  -0.3067   0.10213   0.09637  -0.0272   1.0000   0.0891
  -6.000  -0.3097   0.10171   0.09605  -0.0306   1.0000   0.0897
  -5.750  -0.3041   0.09647   0.09086  -0.0252   0.9983   0.0926
  -5.500  -0.2765   0.09230   0.08664  -0.0314   0.9904   0.0983
  -5.000  -0.2140   0.08343   0.07765  -0.0476   0.9733   0.1055
  -4.750  -0.1576   0.07962   0.07364  -0.0660   0.9639   0.1161
  -4.500  -0.1472   0.07496   0.06904  -0.0625   0.9564   0.1196
  -4.250  -0.1121   0.07064   0.06463  -0.0692   0.9489   0.1226
  -4.000  -0.0699   0.06601   0.05985  -0.0783   0.9408   0.1224
  -3.500   0.0619   0.05131   0.04435  -0.1093   0.9283   0.0768
  -3.250   0.1318   0.04490   0.03732  -0.1236   0.9246   0.0779
  -3.000   0.1645   0.04278   0.03513  -0.1264   0.9159   0.0823
  -2.750   0.2303   0.03745   0.02901  -0.1375   0.9120   0.0800
  -2.500   0.2815   0.03420   0.02513  -0.1439   0.9066   0.0802
  -2.250   0.3245   0.03198   0.02239  -0.1479   0.8992   0.0817
  -2.000   0.3692   0.03028   0.02007  -0.1517   0.8936   0.0887
  -1.750   0.4042   0.02918   0.01874  -0.1536   0.8849   0.0940
  -1.500   0.4431   0.02792   0.01705  -0.1559   0.8781   0.0966
  -1.250   0.4793   0.02695   0.01569  -0.1574   0.8704   0.1002
  -1.000   0.5137   0.02620   0.01464  -0.1585   0.8625   0.1048
  -0.750   0.5491   0.02552   0.01371  -0.1597   0.8555   0.1131
  -0.500   0.5809   0.02500   0.01307  -0.1604   0.8469   0.1263
  -0.250   0.6167   0.02434   0.01250  -0.1619   0.8406   0.1648
   0.000   0.6466   0.02396   0.01244  -0.1626   0.8314   0.2452
   0.250   0.6803   0.02336   0.01244  -0.1636   0.8255   0.4345
   0.500   0.6972   0.02240   0.01243  -0.1612   0.8152   0.9266
   0.750   0.7283   0.02264   0.01232  -0.1617   0.8075   1.0000
   1.000   0.7577   0.02293   0.01237  -0.1619   0.7992   1.0000
   1.250   0.7855   0.02331   0.01255  -0.1619   0.7907   1.0000
   1.500   0.8155   0.02355   0.01263  -0.1621   0.7833   1.0000
   1.750   0.8413   0.02398   0.01295  -0.1618   0.7735   1.0000
   2.000   0.8707   0.02415   0.01299  -0.1617   0.7647   1.0000
   2.250   0.8982   0.02433   0.01311  -0.1612   0.7539   1.0000
   2.500   0.9235   0.02459   0.01331  -0.1605   0.7416   1.0000
   2.750   0.9494   0.02484   0.01353  -0.1598   0.7302   1.0000
   3.000   0.9776   0.02501   0.01369  -0.1594   0.7212   1.0000
   3.250   1.0026   0.02544   0.01415  -0.1589   0.7114   1.0000
   3.500   1.0276   0.02589   0.01465  -0.1584   0.7020   1.0000
   3.750   1.0559   0.02610   0.01490  -0.1581   0.6943   1.0000
   4.000   1.0789   0.02668   0.01563  -0.1574   0.6840   1.0000
   4.250   1.1044   0.02706   0.01610  -0.1568   0.6746   1.0000
   4.500   1.1316   0.02728   0.01641  -0.1563   0.6655   1.0000
   4.750   1.1544   0.02781   0.01713  -0.1554   0.6542   1.0000
   5.000   1.1784   0.02819   0.01766  -0.1545   0.6427   1.0000
   5.250   1.2034   0.02845   0.01807  -0.1535   0.6309   1.0000
   5.500   1.2289   0.02864   0.01841  -0.1525   0.6188   1.0000
   5.750   1.2542   0.02886   0.01887  -0.1516   0.6068   1.0000
   6.000   1.2764   0.02938   0.01962  -0.1504   0.5940   1.0000
   6.250   1.2987   0.02989   0.02039  -0.1493   0.5813   1.0000
   6.500   1.3214   0.03033   0.02109  -0.1481   0.5678   1.0000
   6.750   1.3438   0.03074   0.02178  -0.1467   0.5535   1.0000
   7.000   1.3619   0.03046   0.02170  -0.1437   0.5235   1.0000
   7.250   1.3722   0.03039   0.02165  -0.1396   0.4795   1.0000
   7.500   1.3856   0.03088   0.02234  -0.1368   0.4465   1.0000
   7.750   1.3899   0.03154   0.02280  -0.1323   0.3800   1.0000
   8.000   1.3846   0.03331   0.02378  -0.1271   0.2935   1.0000
   8.250   1.3717   0.03615   0.02591  -0.1222   0.1841   1.0000
   8.500   1.3565   0.03950   0.02872  -0.1176   0.1332   1.0000
   8.750   1.3444   0.04310   0.03186  -0.1141   0.0735   1.0000
   9.000   1.3369   0.04647   0.03509  -0.1113   0.0584   1.0000
   9.250   1.3321   0.04973   0.03838  -0.1090   0.0509   1.0000
   9.500   1.3284   0.05299   0.04177  -0.1072   0.0458   1.0000
   9.750   1.3229   0.05656   0.04541  -0.1056   0.0428   1.0000
  10.000   1.3212   0.05981   0.04891  -0.1042   0.0407   1.0000
  10.250   1.3190   0.06316   0.05248  -0.1029   0.0390   1.0000
  10.500   1.3170   0.06654   0.05613  -0.1016   0.0375   1.0000
  10.750   1.3149   0.06994   0.05966  -0.1005   0.0359   1.0000
  11.000   1.3122   0.07340   0.06320  -0.0993   0.0344   1.0000
  11.250   1.3168   0.07605   0.06608  -0.0978   0.0327   1.0000
  11.500   1.3230   0.07851   0.06878  -0.0961   0.0310   1.0000
  11.750   1.3336   0.08052   0.07099  -0.0939   0.0297   1.0000
  12.000   1.3505   0.08206   0.07275  -0.0913   0.0287   1.0000
  12.250   1.3674   0.08406   0.07496  -0.0889   0.0279   1.0000
  12.500   1.3803   0.08682   0.07790  -0.0872   0.0270   1.0000
  12.750   1.3880   0.09048   0.08175  -0.0859   0.0263   1.0000
  13.000   1.3830   0.09493   0.08659  -0.0858   0.0260   1.0000
  13.250   1.3754   0.09978   0.09178  -0.0862   0.0257   1.0000
  13.500   1.3657   0.10499   0.09732  -0.0871   0.0255   1.0000
  13.750   1.3542   0.11057   0.10321  -0.0886   0.0254   1.0000
  14.000   1.3414   0.11654   0.10946  -0.0908   0.0254   1.0000
  14.250   1.3282   0.12290   0.11608  -0.0936   0.0254   1.0000
  14.500   1.3144   0.12978   0.12318  -0.0972   0.0255   1.0000
  14.750   1.3007   0.13708   0.13069  -0.1014   0.0256   1.0000
  15.000   1.2873   0.14485   0.13864  -0.1063   0.0257   1.0000
  15.250   1.2752   0.15294   0.14688  -0.1116   0.0259   1.0000
  15.500   1.2646   0.16131   0.15536  -0.1172   0.0261   1.0000
  15.750   1.2556   0.16986   0.16401  -0.1229   0.0263   1.0000
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