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SOKOLOV AIRFOIL (sokolov-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: SOKOLOV AIRFOIL (sokolov-il)
Reynolds number: 1,000,000
Max Cl/Cd: 146.07 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sokolov-il-1000000.txt
Download as CSV file: xf-sokolov-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2900   0.10755   0.10595  -0.0321   1.0000   0.0114
  -8.750  -0.2864   0.10473   0.10315  -0.0332   1.0000   0.0115
  -8.500  -0.2856   0.10231   0.10076  -0.0330   1.0000   0.0115
  -8.250  -0.2750   0.09875   0.09721  -0.0358   0.9981   0.0116
  -8.000  -0.2595   0.09465   0.09310  -0.0401   0.9955   0.0116
  -7.750  -0.2442   0.09055   0.08901  -0.0443   0.9914   0.0116
  -7.500  -0.2334   0.08577   0.08423  -0.0474   0.9857   0.0120
  -7.250  -0.2178   0.08307   0.08153  -0.0501   0.9783   0.0123
  -7.000  -0.2013   0.08022   0.07866  -0.0532   0.9698   0.0127
  -6.750  -0.1875   0.07745   0.07588  -0.0558   0.9577   0.0135
  -6.500  -0.1662   0.07305   0.07144  -0.0634   0.9428   0.0155
  -6.250  -0.1472   0.06910   0.06745  -0.0682   0.9276   0.0156
  -6.000  -0.0320   0.01777   0.01491  -0.1427   0.9162   0.0155
  -5.750   0.0012   0.01490   0.01153  -0.1457   0.9002   0.0168
  -5.500   0.0263   0.01562   0.01226  -0.1447   0.8787   0.0172
  -5.250  -0.0425   0.04828   0.04620  -0.0967   0.8465   0.0147
  -4.500   0.1432   0.01313   0.00886  -0.1470   0.8153   0.0222
  -4.250   0.1715   0.01312   0.00878  -0.1471   0.8026   0.0230
  -4.000   0.1997   0.01312   0.00871  -0.1473   0.7906   0.0242
  -3.750   0.2289   0.01284   0.00831  -0.1476   0.7796   0.0257
  -3.500   0.2586   0.01240   0.00769  -0.1480   0.7690   0.0269
  -3.250   0.2876   0.01232   0.00749  -0.1482   0.7583   0.0277
  -3.000   0.3195   0.01084   0.00569  -0.1494   0.7482   0.0293
  -2.750   0.3496   0.01013   0.00484  -0.1500   0.7373   0.0302
  -2.250   0.4083   0.00949   0.00401  -0.1507   0.7152   0.0325
  -2.000   0.4376   0.00922   0.00366  -0.1510   0.7037   0.0337
  -1.750   0.4668   0.00897   0.00331  -0.1512   0.6906   0.0345
  -1.500   0.4959   0.00876   0.00300  -0.1515   0.6758   0.0351
  -1.250   0.5250   0.00858   0.00272  -0.1517   0.6617   0.0356
  -1.000   0.5541   0.00843   0.00249  -0.1519   0.6495   0.0362
  -0.750   0.5831   0.00833   0.00231  -0.1521   0.6380   0.0368
  -0.500   0.6118   0.00828   0.00221  -0.1523   0.6270   0.0377
  -0.250   0.6410   0.00816   0.00202  -0.1525   0.6173   0.0388
   0.000   0.6701   0.00803   0.00181  -0.1527   0.6077   0.0421
   0.250   0.6989   0.00801   0.00174  -0.1529   0.5978   0.0450
   0.500   0.7275   0.00799   0.00169  -0.1530   0.5889   0.0482
   0.750   0.7563   0.00795   0.00170  -0.1532   0.5798   0.0842
   1.000   0.7846   0.00800   0.00176  -0.1533   0.5699   0.1079
   1.250   0.8128   0.00805   0.00180  -0.1534   0.5606   0.1153
   1.500   0.8412   0.00809   0.00184  -0.1535   0.5533   0.1232
   1.750   0.8696   0.00812   0.00187  -0.1536   0.5468   0.1280
   2.000   0.8978   0.00816   0.00192  -0.1537   0.5399   0.1367
   2.500   0.9554   0.00793   0.00218  -0.1544   0.5263   0.3728
   2.750   0.9837   0.00791   0.00231  -0.1546   0.5194   0.4459
   3.000   1.0119   0.00791   0.00243  -0.1548   0.5115   0.5099
   3.250   1.0358   0.00713   0.00255  -0.1541   0.5043   1.0000
   3.500   1.0634   0.00728   0.00264  -0.1541   0.4898   1.0000
   3.750   1.0907   0.00749   0.00275  -0.1540   0.4670   1.0000
   4.000   1.1180   0.00768   0.00287  -0.1540   0.4450   1.0000
   4.250   1.1436   0.00817   0.00310  -0.1537   0.3891   1.0000
   4.500   1.1677   0.00889   0.00348  -0.1533   0.3284   1.0000
   4.750   1.1935   0.00929   0.00375  -0.1531   0.3025   1.0000
   5.000   1.2188   0.00976   0.00405  -0.1528   0.2700   1.0000
   5.250   1.2387   0.01105   0.00475  -0.1519   0.1619   1.0000
   5.500   1.2624   0.01171   0.00523  -0.1513   0.1257   1.0000
   5.750   1.2787   0.01341   0.00629  -0.1497   0.0185   1.0000
   6.000   1.3037   0.01379   0.00671  -0.1492   0.0160   1.0000
   6.250   1.3280   0.01425   0.00720  -0.1487   0.0142   1.0000
   6.500   1.3507   0.01491   0.00795  -0.1477   0.0121   1.0000
   6.750   1.3743   0.01539   0.00847  -0.1471   0.0115   1.0000
   7.000   1.3975   0.01589   0.00902  -0.1463   0.0109   1.0000
   7.250   1.4199   0.01647   0.00964  -0.1454   0.0102   1.0000
   7.500   1.4415   0.01709   0.01031  -0.1444   0.0097   1.0000
   7.750   1.4620   0.01779   0.01108  -0.1432   0.0091   1.0000
   8.000   1.4787   0.01884   0.01220  -0.1414   0.0085   1.0000
   8.250   1.4889   0.02042   0.01391  -0.1385   0.0080   1.0000
   8.500   1.5099   0.02089   0.01442  -0.1375   0.0077   1.0000
   8.750   1.5263   0.02172   0.01531  -0.1356   0.0074   1.0000
   9.000   1.5402   0.02268   0.01634  -0.1334   0.0071   1.0000
   9.250   1.5519   0.02370   0.01745  -0.1308   0.0069   1.0000
   9.500   1.5615   0.02479   0.01862  -0.1279   0.0067   1.0000
   9.750   1.5679   0.02588   0.01978  -0.1245   0.0065   1.0000
  10.000   1.5744   0.02705   0.02102  -0.1213   0.0063   1.0000
  10.250   1.5809   0.02832   0.02237  -0.1183   0.0061   1.0000
  10.500   1.5874   0.02968   0.02380  -0.1156   0.0060   1.0000
  10.750   1.5933   0.03117   0.02535  -0.1130   0.0058   1.0000
  11.000   1.5968   0.03299   0.02725  -0.1103   0.0057   1.0000
  11.250   1.5962   0.03552   0.02988  -0.1071   0.0055   1.0000
  11.500   1.5944   0.03927   0.03383  -0.1035   0.0053   1.0000
  11.750   1.5996   0.04096   0.03565  -0.1015   0.0052   1.0000
  12.000   1.6039   0.04289   0.03771  -0.0996   0.0051   1.0000
  12.250   1.6070   0.04509   0.04006  -0.0976   0.0050   1.0000
  12.500   1.6090   0.04745   0.04257  -0.0959   0.0049   1.0000
  12.750   1.6095   0.05005   0.04532  -0.0942   0.0047   1.0000
  13.000   1.6077   0.05306   0.04850  -0.0925   0.0046   1.0000
  13.250   1.6037   0.05643   0.05205  -0.0909   0.0045   1.0000
  13.500   1.5958   0.06039   0.05621  -0.0894   0.0045   1.0000
  13.750   1.5857   0.06470   0.06071  -0.0882   0.0045   1.0000
  14.000   1.5735   0.06936   0.06558  -0.0874   0.0045   1.0000
  14.250   1.5587   0.07447   0.07089  -0.0871   0.0045   1.0000
  14.500   1.5424   0.08005   0.07667  -0.0873   0.0045   1.0000
  14.750   1.5246   0.08613   0.08296  -0.0882   0.0045   1.0000
  15.000   1.5063   0.09256   0.08957  -0.0896   0.0046   1.0000
  15.250   1.4872   0.09950   0.09669  -0.0917   0.0046   1.0000
  15.500   1.4681   0.10681   0.10419  -0.0945   0.0046   1.0000
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