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


Details Polar file
Airfoil: SARATOV AIRFOIL (saratov-il)
Reynolds number: 200,000
Max Cl/Cd: 161.91 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-saratov-il-200000.txt
Download as CSV file: xf-saratov-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SARATOV 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500   0.0129   0.09728   0.09271  -0.0987   0.7360   0.0622
  -9.250   0.0165   0.09570   0.09088  -0.0993   0.7039   0.0649
  -9.000   0.0023   0.09699   0.09210  -0.1023   0.6871   0.0664
  -8.750   0.0194   0.09169   0.08666  -0.1017   0.6739   0.0674
  -8.500   0.0356   0.08894   0.08376  -0.1009   0.6631   0.0687
  -8.250   0.0476   0.08696   0.08173  -0.1009   0.6551   0.0705
  -8.000   0.0569   0.08510   0.07978  -0.1013   0.6490   0.0728
  -7.750   0.0621   0.08344   0.07810  -0.1026   0.6440   0.0764
  -7.500   0.0431   0.08496   0.07969  -0.1063   0.6398   0.0780
  -7.250   0.0665   0.07942   0.07406  -0.1044   0.6355   0.0793
  -7.000   0.0846   0.07711   0.07164  -0.1039   0.6318   0.0810
  -6.750   0.0953   0.07544   0.06996  -0.1038   0.6284   0.0832
  -6.500   0.1031   0.07389   0.06841  -0.1046   0.6253   0.0869
  -6.250   0.1066   0.07286   0.06740  -0.1141   0.6227   0.0903
  -6.000   0.1218   0.06958   0.06407  -0.1107   0.6199   0.0912
  -5.750   0.1379   0.06761   0.06204  -0.1098   0.6175   0.0929
  -5.500   0.1544   0.06601   0.06037  -0.1106   0.6152   0.0964
  -5.250   0.1771   0.06403   0.05836  -0.1225   0.6132   0.1023
  -5.000   0.1904   0.06138   0.05572  -0.1199   0.6111   0.1031
  -4.750   0.2070   0.05946   0.05379  -0.1192   0.6089   0.1046
  -4.500   0.2263   0.05770   0.05201  -0.1203   0.6067   0.1069
  -4.000   0.3451   0.02222   0.01491  -0.1778   0.6034   0.0861
  -3.750   0.3790   0.01955   0.01169  -0.1813   0.6015   0.0908
  -3.500   0.4067   0.01981   0.01200  -0.1809   0.5999   0.0951
  -3.250   0.4371   0.01893   0.01088  -0.1821   0.5984   0.1023
  -3.000   0.4637   0.01980   0.01200  -0.1811   0.5970   0.1087
  -2.750   0.4914   0.02025   0.01253  -0.1807   0.5956   0.1174
  -2.500   0.5193   0.02075   0.01306  -0.1804   0.5942   0.1289
  -2.250   0.5427   0.02273   0.01528  -0.1780   0.5929   0.1301
  -2.000   0.5662   0.02444   0.01712  -0.1760   0.5917   0.1324
  -1.750   0.5926   0.02517   0.01787  -0.1754   0.5905   0.1439
  -1.500   0.6197   0.02569   0.01836  -0.1751   0.5894   0.1572
  -1.250   0.6489   0.02580   0.01835  -0.1756   0.5884   0.1712
  -1.000   0.6694   0.02692   0.01962  -0.1735   0.5875   0.1739
  -0.750   0.6976   0.02713   0.01976  -0.1738   0.5866   0.1879
  -0.500   0.7177   0.02808   0.02084  -0.1718   0.5858   0.1979
  -0.250   0.7070   0.01371   0.00709  -0.1593   0.5849   0.2355
   0.000   0.7602   0.02905   0.02197  -0.1689   0.5845   0.2413
   0.250   0.7559   0.01313   0.00648  -0.1592   0.5831   0.2548
   0.500   0.7842   0.01305   0.00635  -0.1601   0.5825   0.2669
   0.750   0.8100   0.01294   0.00626  -0.1604   0.5820   0.2746
   1.000   0.8409   0.01293   0.00620  -0.1618   0.5815   0.2797
   1.250   0.8659   0.01262   0.00594  -0.1622   0.5810   0.2819
   1.500   0.8920   0.01258   0.00593  -0.1626   0.5805   0.2868
   1.750   0.9229   0.01301   0.00631  -0.1637   0.5800   0.2929
   2.000   0.9478   0.01274   0.00610  -0.1641   0.5787   0.2940
   2.250   0.9733   0.01263   0.00602  -0.1644   0.5767   0.2955
   2.500   0.9999   0.01255   0.00594  -0.1647   0.5744   0.2971
   2.750   1.0274   0.01251   0.00590  -0.1652   0.5727   0.2978
   3.000   1.0782   0.01055   0.00324  -0.1713   0.5714   0.2348
   3.250   1.1041   0.01058   0.00329  -0.1711   0.5696   0.2360
   3.500   1.1312   0.01056   0.00325  -0.1711   0.5674   0.2376
   3.750   1.1564   0.01072   0.00343  -0.1709   0.5656   0.2396
   4.000   1.1797   0.01099   0.00378  -0.1706   0.5642   0.2422
   4.250   1.2047   0.01085   0.00361  -0.1708   0.5624   0.2495
   4.500   1.2261   0.01142   0.00435  -0.1699   0.5602   0.2513
   4.750   1.2491   0.01181   0.00486  -0.1692   0.5577   0.2539
   5.000   1.2741   0.01198   0.00509  -0.1689   0.5555   0.2578
   5.250   1.3013   0.01185   0.00495  -0.1689   0.5533   0.2650
   5.500   1.3299   0.01186   0.00497  -0.1688   0.5504   0.2681
   5.750   1.3500   0.01244   0.00571  -0.1677   0.5476   0.2733
   6.000   1.3693   0.01296   0.00639  -0.1666   0.5441   0.2800
   6.250   1.3920   0.01330   0.00687  -0.1658   0.5408   0.2850
   6.500   1.4196   0.01322   0.00684  -0.1656   0.5373   0.2949
   6.750   1.4526   0.01276   0.00630  -0.1659   0.5325   0.3072
   7.000   1.4699   0.01306   0.00681  -0.1641   0.5246   0.3136
   7.250   1.5050   0.01202   0.00565  -0.1644   0.5146   0.3272
   7.500   1.5286   0.01153   0.00519  -0.1630   0.5030   0.3403
   7.750   1.5486   0.01127   0.00502  -0.1613   0.4917   0.3543
   8.000   1.5668   0.01066   0.00444  -0.1590   0.4763   0.3702
   8.250   1.5791   0.01016   0.00406  -0.1559   0.4586   0.3844
   8.500   1.5867   0.00980   0.00388  -0.1522   0.4325   0.3960
   8.750   1.5641   0.00970   0.00329  -0.1433   0.3319   0.3997
   9.000   1.5237   0.01166   0.00493  -0.1336   0.2741   0.3992
   9.250   1.5679   0.02550   0.01809  -0.1365   0.2361   0.4021
   9.500   1.5412   0.02849   0.02094  -0.1303   0.2055   0.4039
   9.750   1.5218   0.03154   0.02393  -0.1258   0.1902   0.4071
  10.000   1.5069   0.03465   0.02707  -0.1226   0.1800   0.4108
  10.250   1.4923   0.03822   0.03068  -0.1201   0.1725   0.4149
  10.500   1.4842   0.04149   0.03402  -0.1184   0.1644   0.4201
  10.750   1.4739   0.04522   0.03777  -0.1170   0.1574   0.4243
  11.000   1.4716   0.04821   0.04084  -0.1159   0.1491   0.4298
  11.250   1.4663   0.05162   0.04427  -0.1151   0.1408   0.4345
  11.500   1.4679   0.05441   0.04713  -0.1144   0.1272   0.4401
  11.750   1.4672   0.05752   0.05021  -0.1139   0.1025   0.4450
  12.000   1.4558   0.06182   0.05421  -0.1131   0.0694   0.4478
  12.250   1.4483   0.06565   0.05787  -0.1121   0.0544   0.4512
  12.500   1.4456   0.06899   0.06115  -0.1113   0.0475   0.4546
  12.750   1.4462   0.07195   0.06412  -0.1106   0.0435   0.4590
  13.000   1.4459   0.07508   0.06727  -0.1099   0.0408   0.4635
  13.250   1.4506   0.07762   0.06989  -0.1092   0.0387   0.4683
  13.500   1.4555   0.08012   0.07244  -0.1086   0.0366   0.4725
  13.750   1.4594   0.08271   0.07504  -0.1079   0.0349   0.4757
  14.000   1.4658   0.08487   0.07719  -0.1069   0.0334   0.4781
  14.250   1.4754   0.08676   0.07918  -0.1062   0.0320   0.4803
  14.500   1.4858   0.08848   0.08095  -0.1053   0.0309   0.4817
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