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SOKOLOV AIRFOIL (sokolov-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: SOKOLOV AIRFOIL (sokolov-il)
Reynolds number: 100,000
Max Cl/Cd: 69.55 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sokolov-il-100000-n5.txt
Download as CSV file: xf-sokolov-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2705   0.10239   0.09785  -0.0309   1.0000   0.0353
  -7.250  -0.2777   0.10108   0.09664  -0.0288   1.0000   0.0362
  -7.000  -0.2819   0.09959   0.09524  -0.0279   0.9980   0.0377
  -6.750  -0.2510   0.09653   0.09217  -0.0421   0.9862   0.0406
  -6.500  -0.2191   0.09225   0.08786  -0.0532   0.9774   0.0410
  -6.250  -0.1900   0.08749   0.08307  -0.0613   0.9693   0.0411
  -6.000  -0.1642   0.08180   0.07738  -0.0671   0.9639   0.0414
  -5.750  -0.1529   0.07737   0.07295  -0.0650   0.9574   0.0427
  -5.500  -0.1260   0.07331   0.06884  -0.0691   0.9523   0.0444
  -5.250  -0.0712   0.06896   0.06435  -0.0876   0.9409   0.0538
  -4.750  -0.0138   0.05772   0.05298  -0.0977   0.9256   0.0428
  -4.250   0.0589   0.04985   0.04489  -0.1103   0.9097   0.0480
  -4.000   0.1123   0.04333   0.03810  -0.1223   0.9011   0.0460
  -3.750   0.1708   0.03731   0.03168  -0.1340   0.8956   0.0503
  -3.500   0.2282   0.03088   0.02461  -0.1444   0.8882   0.0509
  -3.250   0.2818   0.02601   0.01880  -0.1521   0.8823   0.0545
  -3.000   0.3196   0.02351   0.01580  -0.1551   0.8733   0.0551
  -2.750   0.3568   0.02156   0.01337  -0.1574   0.8658   0.0557
  -2.500   0.3903   0.02021   0.01166  -0.1587   0.8563   0.0569
  -2.250   0.4226   0.01917   0.01033  -0.1595   0.8468   0.0585
  -2.000   0.4545   0.01831   0.00922  -0.1602   0.8381   0.0604
  -1.750   0.4846   0.01773   0.00842  -0.1605   0.8281   0.0645
  -1.500   0.5143   0.01727   0.00786  -0.1608   0.8184   0.0687
  -1.250   0.5440   0.01684   0.00734  -0.1610   0.8101   0.0710
  -1.000   0.5729   0.01653   0.00694  -0.1611   0.8000   0.0737
  -0.750   0.6020   0.01629   0.00658  -0.1612   0.7906   0.0778
  -0.500   0.6312   0.01612   0.00636  -0.1612   0.7820   0.0860
  -0.250   0.6598   0.01598   0.00615  -0.1613   0.7721   0.1050
   0.000   0.6885   0.01581   0.00594  -0.1613   0.7631   0.1349
   0.250   0.7167   0.01566   0.00586  -0.1613   0.7535   0.1776
   0.500   0.7442   0.01544   0.00600  -0.1614   0.7427   0.2992
   0.750   0.7713   0.01527   0.00613  -0.1611   0.7325   0.4504
   1.000   0.7974   0.01491   0.00613  -0.1606   0.7233   0.5922
   1.250   0.8191   0.01447   0.00606  -0.1590   0.7130   1.0000
   1.500   0.8467   0.01464   0.00609  -0.1588   0.7037   1.0000
   1.750   0.8742   0.01481   0.00612  -0.1586   0.6947   1.0000
   2.000   0.9012   0.01501   0.00625  -0.1583   0.6842   1.0000
   2.250   0.9282   0.01518   0.00634  -0.1580   0.6740   1.0000
   2.500   0.9553   0.01536   0.00643  -0.1577   0.6649   1.0000
   2.750   0.9821   0.01558   0.00663  -0.1575   0.6548   1.0000
   3.000   1.0089   0.01579   0.00682  -0.1572   0.6456   1.0000
   3.250   1.0357   0.01599   0.00699  -0.1569   0.6364   1.0000
   3.500   1.0622   0.01623   0.00726  -0.1566   0.6264   1.0000
   3.750   1.0887   0.01646   0.00752  -0.1562   0.6168   1.0000
   4.000   1.1151   0.01669   0.00776  -0.1558   0.6072   1.0000
   4.250   1.1411   0.01695   0.00810  -0.1555   0.5968   1.0000
   4.500   1.1674   0.01721   0.00845  -0.1551   0.5879   1.0000
   4.750   1.1934   0.01748   0.00879  -0.1547   0.5786   1.0000
   5.000   1.2191   0.01777   0.00920  -0.1543   0.5680   1.0000
   5.250   1.2447   0.01807   0.00960  -0.1538   0.5575   1.0000
   5.500   1.2701   0.01836   0.01003  -0.1532   0.5468   1.0000
   5.750   1.2942   0.01865   0.01044  -0.1524   0.5297   1.0000
   6.000   1.3151   0.01891   0.01070  -0.1509   0.4955   1.0000
   6.250   1.3340   0.01930   0.01099  -0.1491   0.4454   1.0000
   6.500   1.3514   0.01995   0.01142  -0.1471   0.3831   1.0000
   6.750   1.3654   0.02106   0.01223  -0.1448   0.3267   1.0000
   7.250   1.3681   0.02600   0.01555  -0.1376   0.0890   1.0000
   7.500   1.3685   0.02853   0.01754  -0.1338   0.0347   1.0000
   7.750   1.3790   0.02998   0.01908  -0.1311   0.0288   1.0000
   8.000   1.3871   0.03153   0.02074  -0.1282   0.0255   1.0000
   8.250   1.3952   0.03294   0.02235  -0.1253   0.0232   1.0000
   8.500   1.3991   0.03447   0.02409  -0.1219   0.0219   1.0000
   8.750   1.4016   0.03622   0.02603  -0.1185   0.0210   1.0000
   9.000   1.4027   0.03818   0.02818  -0.1153   0.0203   1.0000
   9.250   1.4025   0.04036   0.03054  -0.1123   0.0196   1.0000
   9.500   1.4012   0.04277   0.03317  -0.1095   0.0188   1.0000
   9.750   1.3987   0.04546   0.03599  -0.1069   0.0180   1.0000
  10.000   1.3957   0.04844   0.03909  -0.1043   0.0171   1.0000
  10.250   1.3991   0.05106   0.04179  -0.1020   0.0164   1.0000
  10.500   1.4076   0.05324   0.04412  -0.1001   0.0160   1.0000
  10.750   1.4184   0.05547   0.04651  -0.0981   0.0157   1.0000
  11.000   1.4302   0.05783   0.04906  -0.0963   0.0154   1.0000
  11.250   1.4421   0.06040   0.05185  -0.0945   0.0151   1.0000
  11.500   1.4519   0.06327   0.05497  -0.0927   0.0149   1.0000
  11.750   1.4574   0.06640   0.05839  -0.0911   0.0147   1.0000
  12.000   1.4583   0.06976   0.06204  -0.0895   0.0143   1.0000
  12.250   1.4556   0.07336   0.06593  -0.0882   0.0140   1.0000
  12.500   1.4500   0.07722   0.07007  -0.0872   0.0136   1.0000
  12.750   1.4420   0.08138   0.07451  -0.0865   0.0134   1.0000
  13.000   1.4321   0.08587   0.07928  -0.0862   0.0132   1.0000
  13.250   1.4203   0.09069   0.08437  -0.0863   0.0130   1.0000
  13.500   1.4071   0.09587   0.08982  -0.0870   0.0130   1.0000
  13.750   1.3927   0.10145   0.09566  -0.0882   0.0129   1.0000
  14.000   1.3772   0.10742   0.10189  -0.0901   0.0129   1.0000
  14.250   1.3613   0.11387   0.10858  -0.0927   0.0130   1.0000
  14.500   1.3449   0.12088   0.11583  -0.0962   0.0130   1.0000
  14.750   1.3283   0.12846   0.12362  -0.1004   0.0131   1.0000
  15.000   1.3117   0.13670   0.13207  -0.1055   0.0133   1.0000
  15.250   1.2951   0.14570   0.14126  -0.1115   0.0134   1.0000
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