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SOKOLOV AIRFOIL (sokolov-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: SOKOLOV AIRFOIL (sokolov-il)
Reynolds number: 500,000
Max Cl/Cd: 118.23 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sokolov-il-500000-n5.txt
Download as CSV file: xf-sokolov-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2182   0.08857   0.08635  -0.0500   0.9636   0.0068
  -7.500  -0.2085   0.08522   0.08299  -0.0524   0.9515   0.0069
  -7.250  -0.2005   0.08206   0.07982  -0.0543   0.9369   0.0071
  -7.000  -0.1890   0.07850   0.07624  -0.0574   0.9206   0.0073
  -6.000  -0.0029   0.01621   0.01203  -0.1505   0.8528   0.0127
  -5.750   0.0262   0.01554   0.01114  -0.1512   0.8381   0.0143
  -5.500   0.0517   0.01639   0.01202  -0.1502   0.8244   0.0154
  -5.250   0.0811   0.01585   0.01125  -0.1508   0.8125   0.0174
  -5.000   0.1123   0.01467   0.00966  -0.1520   0.8022   0.0198
  -4.750   0.1414   0.01433   0.00917  -0.1525   0.7927   0.0212
  -4.500   0.1690   0.01458   0.00940  -0.1525   0.7831   0.0224
  -4.250   0.1978   0.01445   0.00915  -0.1528   0.7740   0.0239
  -4.000   0.2270   0.01415   0.00867  -0.1532   0.7653   0.0259
  -3.750   0.2569   0.01361   0.00792  -0.1537   0.7559   0.0273
  -3.500   0.2862   0.01331   0.00743  -0.1541   0.7457   0.0285
  -3.250   0.3156   0.01291   0.00683  -0.1545   0.7345   0.0290
  -3.000   0.3449   0.01254   0.00627  -0.1548   0.7222   0.0294
  -2.750   0.3744   0.01209   0.00565  -0.1552   0.7100   0.0299
  -2.500   0.4048   0.01121   0.00456  -0.1559   0.6991   0.0307
  -2.250   0.4345   0.01070   0.00392  -0.1564   0.6884   0.0318
  -2.000   0.4636   0.01044   0.00355  -0.1567   0.6774   0.0330
  -1.750   0.4925   0.01025   0.00328  -0.1569   0.6658   0.0342
  -1.500   0.5214   0.01010   0.00305  -0.1572   0.6548   0.0353
  -1.250   0.5502   0.00998   0.00286  -0.1574   0.6448   0.0363
  -1.000   0.5789   0.00990   0.00268  -0.1575   0.6329   0.0371
  -0.750   0.6074   0.00985   0.00253  -0.1577   0.6191   0.0378
  -0.500   0.6358   0.00982   0.00241  -0.1578   0.6059   0.0384
  -0.250   0.6643   0.00980   0.00233  -0.1579   0.5959   0.0395
   0.000   0.6928   0.00979   0.00227  -0.1581   0.5878   0.0405
   0.250   0.7212   0.00979   0.00222  -0.1582   0.5795   0.0410
   0.500   0.7497   0.00977   0.00215  -0.1583   0.5721   0.0429
   0.750   0.7782   0.00976   0.00211  -0.1584   0.5644   0.0487
   1.000   0.8066   0.00972   0.00217  -0.1586   0.5569   0.0902
   1.250   0.8346   0.00980   0.00223  -0.1586   0.5491   0.1031
   1.500   0.8627   0.00984   0.00229  -0.1587   0.5406   0.1113
   1.750   0.8905   0.00994   0.00234  -0.1587   0.5315   0.1158
   2.000   0.9184   0.00999   0.00242  -0.1588   0.5226   0.1227
   2.250   0.9463   0.01005   0.00250  -0.1589   0.5148   0.1336
   2.500   0.9749   0.00993   0.00266  -0.1593   0.5075   0.2567
   2.750   1.0031   0.00987   0.00287  -0.1595   0.5003   0.3761
   3.000   1.0308   0.00993   0.00301  -0.1596   0.4917   0.4172
   3.250   1.0585   0.00999   0.00315  -0.1596   0.4827   0.4560
   3.500   1.0861   0.01005   0.00332  -0.1597   0.4720   0.5062
   3.750   1.1082   0.00938   0.00344  -0.1586   0.4601   1.0000
   4.000   1.1350   0.00960   0.00360  -0.1584   0.4383   1.0000
   4.250   1.1584   0.01027   0.00391  -0.1579   0.3691   1.0000
   4.500   1.1824   0.01089   0.00430  -0.1574   0.3293   1.0000
   4.750   1.2071   0.01139   0.00466  -0.1570   0.3022   1.0000
   5.000   1.2316   0.01189   0.00503  -0.1566   0.2729   1.0000
   5.250   1.2499   0.01322   0.00576  -0.1555   0.1661   1.0000
   5.500   1.2729   0.01386   0.00631  -0.1548   0.1410   1.0000
   5.750   1.2864   0.01569   0.00746  -0.1529   0.0250   1.0000
   6.000   1.3096   0.01623   0.00799  -0.1521   0.0152   1.0000
   6.250   1.3328   0.01673   0.00854  -0.1514   0.0128   1.0000
   6.500   1.3548   0.01736   0.00925  -0.1504   0.0105   1.0000
   6.750   1.3769   0.01791   0.00990  -0.1495   0.0094   1.0000
   7.000   1.3986   0.01848   0.01053  -0.1485   0.0085   1.0000
   7.250   1.4192   0.01914   0.01125  -0.1473   0.0078   1.0000
   7.500   1.4385   0.01987   0.01205  -0.1460   0.0072   1.0000
   7.750   1.4541   0.02092   0.01319  -0.1441   0.0066   1.0000
   8.000   1.4701   0.02185   0.01421  -0.1422   0.0063   1.0000
   8.250   1.4869   0.02262   0.01509  -0.1404   0.0058   1.0000
   8.500   1.5020   0.02345   0.01599  -0.1385   0.0054   1.0000
   8.750   1.5139   0.02443   0.01705  -0.1360   0.0051   1.0000
   9.000   1.5234   0.02545   0.01815  -0.1331   0.0049   1.0000
   9.250   1.5298   0.02655   0.01933  -0.1298   0.0047   1.0000
   9.500   1.5352   0.02784   0.02069  -0.1266   0.0045   1.0000
   9.750   1.5374   0.02947   0.02242  -0.1232   0.0044   1.0000
  10.000   1.5352   0.03161   0.02467  -0.1195   0.0042   1.0000
  10.250   1.5397   0.03332   0.02651  -0.1169   0.0042   1.0000
  10.500   1.5433   0.03523   0.02854  -0.1144   0.0041   1.0000
  10.750   1.5460   0.03731   0.03076  -0.1120   0.0040   1.0000
  11.000   1.5483   0.03955   0.03314  -0.1097   0.0039   1.0000
  11.250   1.5504   0.04191   0.03563  -0.1076   0.0038   1.0000
  11.500   1.5531   0.04427   0.03818  -0.1056   0.0036   1.0000
  11.750   1.5559   0.04667   0.04071  -0.1039   0.0035   1.0000
  12.000   1.5586   0.04908   0.04326  -0.1024   0.0033   1.0000
  12.250   1.5605   0.05162   0.04594  -0.1010   0.0032   1.0000
  12.500   1.5624   0.05419   0.04864  -0.0999   0.0031   1.0000
  12.750   1.5637   0.05684   0.05141  -0.0990   0.0030   1.0000
  13.000   1.5632   0.05978   0.05448  -0.0981   0.0029   1.0000
  13.250   1.5612   0.06298   0.05782  -0.0973   0.0029   1.0000
  13.500   1.5578   0.06646   0.06143  -0.0966   0.0028   1.0000
  13.750   1.5535   0.07013   0.06525  -0.0962   0.0028   1.0000
  14.000   1.5472   0.07420   0.06948  -0.0959   0.0028   1.0000
  14.250   1.5392   0.07866   0.07410  -0.0959   0.0027   1.0000
  14.500   1.5285   0.08367   0.07930  -0.0961   0.0027   1.0000
  14.750   1.5153   0.08923   0.08506  -0.0966   0.0026   1.0000
  15.000   1.5027   0.09496   0.09099  -0.0977   0.0026   1.0000
  15.250   1.4902   0.10091   0.09715  -0.0992   0.0026   1.0000
  15.500   1.4764   0.10732   0.10376  -0.1012   0.0026   1.0000
  15.750   1.4617   0.11414   0.11078  -0.1038   0.0026   1.0000
  16.000   1.4465   0.12137   0.11821  -0.1069   0.0026   1.0000
  16.250   1.4312   0.12902   0.12605  -0.1106   0.0026   1.0000
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