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SOKOLOV AIRFOIL (sokolov-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: SOKOLOV AIRFOIL (sokolov-il)
Reynolds number: 200,000
Max Cl/Cd: 91.97 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sokolov-il-200000-n5.txt
Download as CSV file: xf-sokolov-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2783   0.11256   0.10915  -0.0361   1.0000   0.0198
  -8.500  -0.2773   0.11000   0.10664  -0.0358   1.0000   0.0198
  -8.250  -0.2781   0.10761   0.10428  -0.0349   1.0000   0.0198
  -8.000  -0.2751   0.10495   0.10167  -0.0355   0.9982   0.0198
  -7.750  -0.1322   0.07830   0.07513  -0.0543   0.9701   0.0190
  -7.500  -0.1212   0.07412   0.07095  -0.0566   0.9642   0.0183
  -7.250  -0.2254   0.09151   0.08822  -0.0450   0.9831   0.0191
  -7.000  -0.2079   0.08744   0.08415  -0.0486   0.9768   0.0180
  -6.750  -0.1896   0.08338   0.08009  -0.0534   0.9678   0.0174
  -6.500  -0.1699   0.07924   0.07594  -0.0586   0.9583   0.0170
  -6.250  -0.1475   0.07494   0.07162  -0.0646   0.9491   0.0169
  -6.000  -0.1237   0.07062   0.06728  -0.0710   0.9385   0.0173
  -5.750  -0.0961   0.06567   0.06229  -0.0792   0.9258   0.0187
  -5.500  -0.0644   0.06005   0.05660  -0.0885   0.9131   0.0192
  -5.250  -0.0275   0.05385   0.05031  -0.0986   0.9011   0.0197
  -5.000   0.0104   0.04835   0.04469  -0.1079   0.8900   0.0208
  -4.750   0.0341   0.04778   0.04407  -0.1086   0.8786   0.0230
  -4.500   0.0789   0.04249   0.03859  -0.1184   0.8682   0.0251
  -4.250   0.1739   0.02605   0.02116  -0.1454   0.8625   0.0303
  -4.000   0.2083   0.02374   0.01855  -0.1486   0.8519   0.0322
  -3.750   0.2390   0.02271   0.01730  -0.1500   0.8405   0.0352
  -3.500   0.2776   0.01968   0.01358  -0.1534   0.8300   0.0378
  -3.250   0.3112   0.01800   0.01136  -0.1550   0.8196   0.0394
  -3.000   0.3420   0.01725   0.01020  -0.1556   0.8095   0.0409
  -2.750   0.3728   0.01625   0.00886  -0.1563   0.7994   0.0411
  -2.500   0.4036   0.01507   0.00737  -0.1571   0.7899   0.0418
  -2.250   0.4333   0.01422   0.00631  -0.1576   0.7808   0.0430
  -2.000   0.4626   0.01368   0.00565  -0.1579   0.7707   0.0444
  -1.750   0.4915   0.01330   0.00514  -0.1581   0.7607   0.0459
  -1.500   0.5202   0.01301   0.00473  -0.1582   0.7502   0.0473
  -1.250   0.5487   0.01278   0.00440  -0.1583   0.7390   0.0490
  -1.000   0.5772   0.01262   0.00414  -0.1584   0.7275   0.0519
  -0.750   0.6056   0.01249   0.00391  -0.1584   0.7164   0.0535
  -0.500   0.6341   0.01237   0.00370  -0.1585   0.7064   0.0546
  -0.250   0.6627   0.01226   0.00352  -0.1586   0.6964   0.0573
   0.000   0.6912   0.01218   0.00342  -0.1587   0.6867   0.0625
   0.250   0.7194   0.01214   0.00344  -0.1587   0.6776   0.0925
   0.500   0.7475   0.01217   0.00343  -0.1587   0.6681   0.1153
   0.750   0.7754   0.01217   0.00342  -0.1587   0.6582   0.1296
   1.000   0.8030   0.01216   0.00344  -0.1587   0.6474   0.1506
   1.250   0.8310   0.01203   0.00354  -0.1589   0.6361   0.2473
   1.500   0.8587   0.01186   0.00377  -0.1591   0.6251   0.4190
   1.750   0.8860   0.01182   0.00386  -0.1590   0.6151   0.4936
   2.000   0.9117   0.01148   0.00395  -0.1585   0.6058   0.6969
   2.250   0.9347   0.01121   0.00392  -0.1572   0.5973   1.0000
   2.500   0.9622   0.01138   0.00403  -0.1571   0.5902   1.0000
   2.750   0.9897   0.01155   0.00417  -0.1571   0.5821   1.0000
   3.000   1.0170   0.01173   0.00431  -0.1570   0.5738   1.0000
   3.250   1.0441   0.01191   0.00447  -0.1568   0.5648   1.0000
   3.500   1.0713   0.01210   0.00465  -0.1567   0.5561   1.0000
   3.750   1.0981   0.01231   0.00485  -0.1565   0.5476   1.0000
   4.000   1.1251   0.01249   0.00508  -0.1564   0.5386   1.0000
   4.250   1.1519   0.01270   0.00531  -0.1562   0.5304   1.0000
   4.500   1.1786   0.01291   0.00558  -0.1560   0.5213   1.0000
   4.750   1.2052   0.01312   0.00586  -0.1557   0.5120   1.0000
   5.000   1.2306   0.01338   0.00611  -0.1553   0.4930   1.0000
   5.250   1.2545   0.01370   0.00636  -0.1546   0.4597   1.0000
   5.500   1.2760   0.01424   0.00669  -0.1535   0.3990   1.0000
   5.750   1.2921   0.01539   0.00733  -0.1517   0.3242   1.0000
   6.000   1.3113   0.01631   0.00803  -0.1505   0.2787   1.0000
   6.500   1.3325   0.02007   0.01049  -0.1459   0.0686   1.0000
   6.750   1.3430   0.02181   0.01192  -0.1433   0.0225   1.0000
   7.000   1.3599   0.02283   0.01307  -0.1415   0.0175   1.0000
   7.250   1.3771   0.02376   0.01416  -0.1397   0.0160   1.0000
   7.500   1.3932   0.02472   0.01531  -0.1378   0.0150   1.0000
   7.750   1.4072   0.02579   0.01654  -0.1356   0.0139   1.0000
   8.000   1.4190   0.02693   0.01781  -0.1332   0.0126   1.0000
   8.250   1.4271   0.02823   0.01924  -0.1302   0.0117   1.0000
   8.500   1.4295   0.02973   0.02087  -0.1264   0.0112   1.0000
   8.750   1.4297   0.03153   0.02280  -0.1226   0.0108   1.0000
   9.000   1.4283   0.03366   0.02509  -0.1189   0.0105   1.0000
   9.250   1.4256   0.03613   0.02767  -0.1154   0.0101   1.0000
   9.500   1.4264   0.03857   0.03019  -0.1123   0.0099   1.0000
   9.750   1.4337   0.04041   0.03216  -0.1101   0.0097   1.0000
  10.000   1.4421   0.04217   0.03405  -0.1082   0.0093   1.0000
  10.250   1.4504   0.04398   0.03600  -0.1063   0.0088   1.0000
  10.500   1.4580   0.04592   0.03806  -0.1045   0.0083   1.0000
  10.750   1.4654   0.04804   0.04032  -0.1027   0.0079   1.0000
  11.000   1.4729   0.05030   0.04272  -0.1008   0.0077   1.0000
  11.250   1.4799   0.05266   0.04524  -0.0990   0.0075   1.0000
  11.500   1.4861   0.05516   0.04790  -0.0973   0.0074   1.0000
  11.750   1.4905   0.05788   0.05080  -0.0956   0.0072   1.0000
  12.000   1.4929   0.06081   0.05392  -0.0940   0.0071   1.0000
  12.250   1.4933   0.06397   0.05735  -0.0925   0.0070   1.0000
  12.500   1.4916   0.06741   0.06100  -0.0912   0.0069   1.0000
  12.750   1.4876   0.07113   0.06494  -0.0900   0.0069   1.0000
  13.000   1.4814   0.07514   0.06918  -0.0891   0.0068   1.0000
  13.250   1.4731   0.07946   0.07373  -0.0885   0.0068   1.0000
  13.500   1.4628   0.08408   0.07858  -0.0883   0.0068   1.0000
  13.750   1.4509   0.08901   0.08375  -0.0885   0.0068   1.0000
  14.000   1.4379   0.09426   0.08923  -0.0893   0.0068   1.0000
  14.250   1.4242   0.09985   0.09506  -0.0906   0.0068   1.0000
  14.500   1.4097   0.10583   0.10127  -0.0924   0.0068   1.0000
  14.750   1.3952   0.11216   0.10781  -0.0949   0.0068   1.0000
  15.000   1.3803   0.11894   0.11480  -0.0980   0.0068   1.0000
  15.250   1.3652   0.12623   0.12232  -0.1019   0.0069   1.0000
  15.500   1.3496   0.13415   0.13044  -0.1065   0.0069   1.0000
  15.750   1.3327   0.14313   0.13964  -0.1123   0.0070   1.0000
  16.000   1.3085   0.15554   0.15234  -0.1210   0.0072   1.0000
  16.250   1.2855   0.16924   0.16627  -0.1307   0.0074   1.0000
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