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SOKOLOV AIRFOIL (sokolov-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: SOKOLOV AIRFOIL (sokolov-il)
Reynolds number: 200,000
Max Cl/Cd: 92.88 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sokolov-il-200000.txt
Download as CSV file: xf-sokolov-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2858   0.09736   0.09416  -0.0273   1.0000   0.0329
  -7.000  -0.2999   0.09673   0.09363  -0.0235   1.0000   0.0333
  -6.750  -0.3142   0.09617   0.09316  -0.0202   0.9994   0.0338
  -6.500  -0.2817   0.09142   0.08839  -0.0298   0.9938   0.0361
  -6.250  -0.2310   0.08716   0.08408  -0.0495   0.9851   0.0378
  -6.000  -0.1897   0.08213   0.07899  -0.0616   0.9791   0.0380
  -5.750  -0.1731   0.07520   0.07207  -0.0644   0.9744   0.0390
  -5.500  -0.1509   0.07143   0.06829  -0.0651   0.9715   0.0406
  -5.250  -0.1192   0.06767   0.06450  -0.0706   0.9662   0.0434
  -5.000  -0.0339   0.06151   0.05812  -0.0974   0.9598   0.0503
  -4.750  -0.0104   0.05556   0.05217  -0.1004   0.9569   0.0520
  -4.500   0.0143   0.05290   0.04950  -0.1016   0.9498   0.0547
  -4.250   0.0861   0.04584   0.04218  -0.1206   0.9449   0.0645
  -4.000   0.1061   0.04444   0.04082  -0.1191   0.9386   0.0690
  -3.750   0.1581   0.03959   0.03575  -0.1295   0.9310   0.0784
  -3.500   0.2094   0.03532   0.03120  -0.1383   0.9247   0.0900
  -2.500   0.3804   0.01957   0.01351  -0.1562   0.8884   0.0734
  -2.250   0.4147   0.01721   0.01068  -0.1575   0.8780   0.0692
  -2.000   0.4467   0.01562   0.00864  -0.1579   0.8677   0.0679
  -1.750   0.4759   0.01479   0.00757  -0.1578   0.8565   0.0693
  -1.500   0.5041   0.01425   0.00684  -0.1575   0.8435   0.0722
  -1.250   0.5325   0.01363   0.00605  -0.1572   0.8305   0.0733
  -1.000   0.5606   0.01318   0.00546  -0.1569   0.8176   0.0752
  -0.750   0.5888   0.01283   0.00510  -0.1568   0.8054   0.0790
  -0.500   0.6170   0.01268   0.00488  -0.1565   0.7941   0.0855
  -0.250   0.6452   0.01256   0.00472  -0.1564   0.7836   0.0975
   0.000   0.6742   0.01224   0.00449  -0.1566   0.7721   0.1362
   0.250   0.7027   0.01201   0.00444  -0.1567   0.7614   0.2022
   0.500   0.7308   0.01181   0.00456  -0.1569   0.7519   0.3318
   0.750   0.7584   0.01171   0.00467  -0.1568   0.7419   0.4527
   1.000   0.7825   0.01103   0.00471  -0.1559   0.7313   0.7272
   1.250   0.8066   0.01082   0.00457  -0.1547   0.7209   1.0000
   1.500   0.8343   0.01096   0.00456  -0.1544   0.7112   1.0000
   1.750   0.8619   0.01109   0.00460  -0.1542   0.7004   1.0000
   2.000   0.8896   0.01124   0.00467  -0.1541   0.6912   1.0000
   2.250   0.9173   0.01141   0.00473  -0.1539   0.6832   1.0000
   2.500   0.9448   0.01156   0.00488  -0.1538   0.6737   1.0000
   2.750   0.9723   0.01173   0.00498  -0.1537   0.6653   1.0000
   3.000   0.9998   0.01190   0.00512  -0.1535   0.6567   1.0000
   3.250   1.0273   0.01208   0.00530  -0.1534   0.6485   1.0000
   3.500   1.0546   0.01226   0.00546  -0.1532   0.6404   1.0000
   3.750   1.0817   0.01244   0.00567  -0.1530   0.6308   1.0000
   4.000   1.1088   0.01263   0.00585  -0.1528   0.6220   1.0000
   4.250   1.1358   0.01282   0.00606  -0.1526   0.6128   1.0000
   4.500   1.1627   0.01302   0.00634  -0.1524   0.6033   1.0000
   4.750   1.1893   0.01321   0.00655  -0.1520   0.5927   1.0000
   5.000   1.2148   0.01335   0.00671  -0.1514   0.5759   1.0000
   5.250   1.2397   0.01349   0.00684  -0.1507   0.5562   1.0000
   5.500   1.2645   0.01367   0.00705  -0.1499   0.5350   1.0000
   5.750   1.2888   0.01388   0.00726  -0.1491   0.5115   1.0000
   6.000   1.3124   0.01413   0.00751  -0.1482   0.4814   1.0000
   6.250   1.3335   0.01452   0.00776  -0.1469   0.4237   1.0000
   6.500   1.3471   0.01577   0.00842  -0.1446   0.3297   1.0000
   6.750   1.3514   0.01827   0.00985  -0.1413   0.1702   1.0000
   7.000   1.3525   0.02123   0.01190  -0.1376   0.0471   1.0000
   7.250   1.3672   0.02255   0.01321  -0.1354   0.0358   1.0000
   7.500   1.3819   0.02379   0.01459  -0.1332   0.0323   1.0000
   7.750   1.3961   0.02496   0.01593  -0.1309   0.0305   1.0000
   8.000   1.4073   0.02629   0.01739  -0.1282   0.0291   1.0000
   8.250   1.4154   0.02773   0.01895  -0.1251   0.0276   1.0000
   8.500   1.4183   0.02938   0.02067  -0.1214   0.0261   1.0000
   8.750   1.4151   0.03157   0.02292  -0.1169   0.0250   1.0000
   9.000   1.4180   0.03381   0.02522  -0.1134   0.0244   1.0000
   9.250   1.4287   0.03555   0.02705  -0.1109   0.0241   1.0000
   9.500   1.4432   0.03743   0.02903  -0.1089   0.0238   1.0000
   9.750   1.4638   0.03956   0.03126  -0.1075   0.0237   1.0000
  10.000   1.4951   0.04241   0.03429  -0.1077   0.0238   1.0000
  10.250   1.5281   0.04597   0.03809  -0.1085   0.0239   1.0000
  10.500   1.5395   0.04825   0.04064  -0.1061   0.0235   1.0000
  10.750   1.5484   0.05091   0.04359  -0.1036   0.0232   1.0000
  11.000   1.5843   0.05708   0.05001  -0.1052   0.0250   1.0000
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