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SOKOLOV AIRFOIL (sokolov-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: SOKOLOV AIRFOIL (sokolov-il)
Reynolds number: 1,000,000
Max Cl/Cd: 109.71 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sokolov-il-1000000-n5.txt
Download as CSV file: xf-sokolov-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2687   0.10129   0.09965  -0.0406   0.9644   0.0040
  -8.750  -0.2631   0.09766   0.09601  -0.0422   0.9534   0.0040
  -8.500  -0.2588   0.09383   0.09217  -0.0437   0.9408   0.0040
  -7.500  -0.1777   0.01685   0.01347  -0.1469   0.8445   0.0057
  -7.250  -0.1460   0.01467   0.01083  -0.1494   0.8294   0.0059
  -7.000  -0.1157   0.01350   0.00936  -0.1506   0.8167   0.0062
  -6.750  -0.0852   0.01237   0.00796  -0.1519   0.8056   0.0071
  -6.500  -0.0554   0.01163   0.00702  -0.1527   0.7955   0.0080
  -6.250  -0.0257   0.01108   0.00628  -0.1533   0.7862   0.0088
  -6.000   0.0039   0.01062   0.00568  -0.1538   0.7780   0.0100
  -5.750   0.0333   0.01026   0.00525  -0.1542   0.7693   0.0121
  -5.500   0.0623   0.01010   0.00503  -0.1545   0.7613   0.0145
  -5.000   0.1189   0.01036   0.00527  -0.1544   0.7438   0.0190
  -4.750   0.1473   0.01043   0.00527  -0.1545   0.7336   0.0197
  -4.500   0.1758   0.01048   0.00525  -0.1545   0.7222   0.0200
  -4.250   0.2055   0.01002   0.00464  -0.1551   0.7096   0.0215
  -4.000   0.2340   0.01006   0.00462  -0.1552   0.6970   0.0225
  -3.750   0.2627   0.01005   0.00455  -0.1553   0.6848   0.0234
  -3.500   0.2916   0.00995   0.00435  -0.1556   0.6722   0.0243
  -3.250   0.3206   0.00981   0.00409  -0.1558   0.6589   0.0252
  -3.000   0.3498   0.00957   0.00374  -0.1561   0.6475   0.0259
  -2.500   0.4084   0.00914   0.00308  -0.1568   0.6248   0.0274
  -2.250   0.4374   0.00902   0.00288  -0.1570   0.6147   0.0282
  -2.000   0.4661   0.00897   0.00276  -0.1572   0.6035   0.0289
  -1.750   0.4947   0.00896   0.00266  -0.1573   0.5883   0.0293
  -1.500   0.5232   0.00897   0.00258  -0.1575   0.5742   0.0295
  -1.250   0.5522   0.00887   0.00241  -0.1577   0.5643   0.0301
  -1.000   0.5814   0.00870   0.00218  -0.1581   0.5577   0.0309
  -0.750   0.6104   0.00862   0.00203  -0.1583   0.5511   0.0316
  -0.500   0.6392   0.00856   0.00194  -0.1585   0.5447   0.0321
  -0.250   0.6679   0.00853   0.00186  -0.1587   0.5377   0.0327
   0.000   0.6965   0.00852   0.00181  -0.1588   0.5311   0.0332
   0.250   0.7251   0.00851   0.00177  -0.1590   0.5233   0.0342
   0.500   0.7536   0.00853   0.00176  -0.1591   0.5154   0.0357
   0.750   0.7820   0.00855   0.00175  -0.1592   0.5075   0.0369
   1.000   0.8104   0.00858   0.00176  -0.1594   0.5008   0.0394
   1.250   0.8388   0.00861   0.00178  -0.1595   0.4918   0.0479
   1.500   0.8672   0.00861   0.00185  -0.1597   0.4823   0.0915
   1.750   0.8952   0.00869   0.00192  -0.1598   0.4710   0.0993
   2.000   0.9231   0.00879   0.00199  -0.1598   0.4599   0.1019
   2.250   0.9510   0.00887   0.00206  -0.1599   0.4473   0.1056
   2.500   0.9787   0.00900   0.00215  -0.1599   0.4296   0.1099
   2.750   1.0057   0.00924   0.00228  -0.1599   0.3980   0.1127
   3.250   1.0588   0.00986   0.00267  -0.1597   0.3377   0.1266
   3.750   1.1124   0.01028   0.00317  -0.1599   0.2929   0.2739
   4.000   1.1396   0.01040   0.00341  -0.1600   0.2791   0.3660
   4.250   1.1662   0.01063   0.00366  -0.1599   0.2591   0.4194
   4.500   1.1886   0.01149   0.00420  -0.1594   0.1738   0.4705
   4.750   1.2145   0.01154   0.00471  -0.1595   0.1502   0.7667
   5.000   1.2354   0.01152   0.00495  -0.1581   0.1336   1.0000
   5.250   1.2530   0.01302   0.00585  -0.1567   0.0241   1.0000
   5.500   1.2778   0.01342   0.00623  -0.1563   0.0141   1.0000
   5.750   1.3028   0.01379   0.00660  -0.1559   0.0107   1.0000
   6.000   1.3278   0.01411   0.00695  -0.1555   0.0093   1.0000
   6.250   1.3524   0.01447   0.00732  -0.1550   0.0081   1.0000
   6.500   1.3763   0.01490   0.00778  -0.1544   0.0070   1.0000
   6.750   1.3998   0.01536   0.00828  -0.1537   0.0063   1.0000
   7.000   1.4234   0.01578   0.00873  -0.1531   0.0059   1.0000
   7.250   1.4465   0.01621   0.00918  -0.1524   0.0053   1.0000
   7.500   1.4691   0.01667   0.00966  -0.1517   0.0048   1.0000
   7.750   1.4895   0.01736   0.01039  -0.1505   0.0042   1.0000
   8.000   1.5111   0.01787   0.01097  -0.1495   0.0041   1.0000
   8.250   1.5317   0.01845   0.01160  -0.1484   0.0039   1.0000
   8.500   1.5514   0.01907   0.01228  -0.1472   0.0036   1.0000
   8.750   1.5702   0.01972   0.01299  -0.1458   0.0034   1.0000
   9.000   1.5881   0.02040   0.01373  -0.1443   0.0032   1.0000
   9.250   1.6051   0.02110   0.01447  -0.1426   0.0031   1.0000
   9.500   1.6201   0.02186   0.01528  -0.1406   0.0029   1.0000
   9.750   1.6316   0.02278   0.01627  -0.1380   0.0028   1.0000
  10.000   1.6345   0.02410   0.01770  -0.1340   0.0026   1.0000
  10.250   1.6432   0.02499   0.01867  -0.1310   0.0026   1.0000
  10.500   1.6512   0.02602   0.01981  -0.1282   0.0025   1.0000
  10.750   1.6588   0.02715   0.02104  -0.1254   0.0024   1.0000
  11.000   1.6652   0.02845   0.02243  -0.1228   0.0023   1.0000
  11.250   1.6706   0.02991   0.02398  -0.1202   0.0022   1.0000
  11.500   1.6748   0.03156   0.02574  -0.1176   0.0022   1.0000
  11.750   1.6784   0.03335   0.02764  -0.1153   0.0021   1.0000
  12.000   1.6812   0.03531   0.02970  -0.1131   0.0020   1.0000
  12.250   1.6836   0.03743   0.03194  -0.1112   0.0020   1.0000
  12.500   1.6860   0.03964   0.03425  -0.1095   0.0019   1.0000
  12.750   1.6883   0.04192   0.03663  -0.1080   0.0019   1.0000
  13.000   1.6893   0.04443   0.03925  -0.1066   0.0019   1.0000
  13.250   1.6894   0.04711   0.04204  -0.1053   0.0018   1.0000
  13.500   1.6890   0.04990   0.04494  -0.1042   0.0018   1.0000
  13.750   1.6885   0.05277   0.04791  -0.1032   0.0018   1.0000
  14.000   1.6861   0.05595   0.05123  -0.1024   0.0017   1.0000
  14.250   1.6836   0.05923   0.05463  -0.1017   0.0017   1.0000
  14.500   1.6796   0.06279   0.05830  -0.1012   0.0017   1.0000
  14.750   1.6749   0.06658   0.06221  -0.1009   0.0016   1.0000
  15.000   1.6684   0.07072   0.06648  -0.1008   0.0016   1.0000
  15.250   1.6605   0.07514   0.07103  -0.1009   0.0016   1.0000
  15.500   1.6513   0.07989   0.07592  -0.1012   0.0016   1.0000
  15.750   1.6396   0.08514   0.08133  -0.1017   0.0015   1.0000
  16.000   1.6253   0.09098   0.08733  -0.1026   0.0015   1.0000
  16.250   1.6097   0.09712   0.09364  -0.1037   0.0015   1.0000
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