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GOE 495 AIRFOIL (goe495-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 495 AIRFOIL (goe495-il)
Reynolds number: 100,000
Max Cl/Cd: 69.29 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe495-il-100000-n5.txt
Download as CSV file: xf-goe495-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 495 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3261   0.09977   0.09500  -0.0324   1.0000   0.0449
  -7.750  -0.3330   0.09808   0.09340  -0.0311   1.0000   0.0457
  -7.500  -0.3406   0.09643   0.09184  -0.0290   1.0000   0.0455
  -7.250  -0.2592   0.07709   0.07285  -0.0370   0.9883   0.0343
  -7.000  -0.2509   0.07283   0.06860  -0.0395   0.9830   0.0334
  -6.750  -0.3500   0.08800   0.08359  -0.0302   0.9944   0.0338
  -6.500  -0.3300   0.08327   0.07885  -0.0357   0.9884   0.0318
  -6.250  -0.3086   0.07828   0.07383  -0.0426   0.9817   0.0306
  -6.000  -0.2827   0.07320   0.06872  -0.0509   0.9756   0.0320
  -5.750  -0.2552   0.06770   0.06318  -0.0597   0.9687   0.0328
  -5.500  -0.2252   0.06190   0.05728  -0.0685   0.9624   0.0323
  -5.250  -0.1879   0.05492   0.05017  -0.0797   0.9565   0.0319
  -5.000  -0.1354   0.04516   0.04009  -0.0954   0.9531   0.0323
  -4.750  -0.0841   0.03433   0.02839  -0.1094   0.9480   0.0349
  -4.500  -0.0390   0.02819   0.02117  -0.1167   0.9448   0.0368
  -4.250  -0.0028   0.02606   0.01876  -0.1198   0.9416   0.0410
  -4.000   0.0369   0.02381   0.01593  -0.1228   0.9391   0.0457
  -3.750   0.0667   0.02216   0.01374  -0.1235   0.9328   0.0496
  -3.500   0.1011   0.02104   0.01249  -0.1253   0.9288   0.0547
  -3.250   0.1387   0.01987   0.01104  -0.1272   0.9260   0.0585
  -3.000   0.1678   0.01916   0.01015  -0.1275   0.9198   0.0637
  -2.750   0.2014   0.01848   0.00939  -0.1287   0.9152   0.0689
  -2.500   0.2382   0.01781   0.00857  -0.1304   0.9120   0.0743
  -2.250   0.2677   0.01731   0.00807  -0.1307   0.9058   0.0830
  -2.000   0.3005   0.01681   0.00758  -0.1317   0.9008   0.1057
  -1.750   0.3363   0.01637   0.00723  -0.1332   0.8972   0.1515
  -1.500   0.3637   0.01617   0.00713  -0.1333   0.8900   0.1981
  -1.250   0.3964   0.01587   0.00701  -0.1343   0.8851   0.2656
  -1.000   0.4285   0.01562   0.00692  -0.1351   0.8799   0.3288
  -0.750   0.4580   0.01544   0.00683  -0.1353   0.8732   0.3855
  -0.500   0.4923   0.01513   0.00666  -0.1364   0.8689   0.4546
  -0.250   0.5184   0.01494   0.00668  -0.1359   0.8609   0.5321
   0.000   0.5482   0.01440   0.00654  -0.1358   0.8558   0.6731
   0.250   0.5752   0.01396   0.00640  -0.1352   0.8478   1.0000
   0.500   0.6079   0.01396   0.00627  -0.1359   0.8419   1.0000
   0.750   0.6353   0.01408   0.00630  -0.1356   0.8334   1.0000
   1.000   0.6676   0.01408   0.00622  -0.1362   0.8272   1.0000
   1.250   0.6941   0.01421   0.00631  -0.1358   0.8178   1.0000
   1.500   0.7255   0.01423   0.00628  -0.1362   0.8108   1.0000
   1.750   0.7522   0.01435   0.00638  -0.1357   0.8008   1.0000
   2.000   0.7796   0.01444   0.00646  -0.1354   0.7906   1.0000
   2.250   0.8091   0.01446   0.00648  -0.1353   0.7810   1.0000
   2.500   0.8361   0.01455   0.00658  -0.1349   0.7697   1.0000
   2.750   0.8621   0.01466   0.00672  -0.1342   0.7574   1.0000
   3.000   0.8885   0.01475   0.00687  -0.1336   0.7445   1.0000
   3.250   0.9149   0.01482   0.00697  -0.1329   0.7302   1.0000
   3.500   0.9410   0.01489   0.00709  -0.1322   0.7150   1.0000
   3.750   0.9671   0.01498   0.00723  -0.1315   0.6993   1.0000
   4.000   0.9932   0.01508   0.00740  -0.1307   0.6830   1.0000
   4.250   1.0187   0.01520   0.00757  -0.1299   0.6647   1.0000
   4.500   1.0434   0.01536   0.00778  -0.1289   0.6436   1.0000
   4.750   1.0684   0.01553   0.00801  -0.1279   0.6217   1.0000
   5.000   1.0913   0.01575   0.00822  -0.1265   0.5900   1.0000
   5.250   1.1121   0.01608   0.00842  -0.1246   0.5446   1.0000
   5.500   1.1312   0.01658   0.00872  -0.1226   0.4921   1.0000
   5.750   1.1489   0.01722   0.00917  -0.1205   0.4300   1.0000
   6.000   1.1627   0.01821   0.00978  -0.1180   0.3503   1.0000
   6.250   1.1739   0.01954   0.01064  -0.1154   0.2641   1.0000
   6.500   1.1854   0.02099   0.01166  -0.1130   0.1919   1.0000
   6.750   1.1983   0.02238   0.01281  -0.1109   0.1468   1.0000
   7.000   1.2116   0.02375   0.01398  -0.1087   0.1008   1.0000
   7.250   1.2235   0.02522   0.01524  -0.1065   0.0739   1.0000
   7.500   1.2362   0.02656   0.01662  -0.1043   0.0596   1.0000
   7.750   1.2479   0.02797   0.01805  -0.1019   0.0505   1.0000
   8.000   1.2578   0.02949   0.01960  -0.0994   0.0434   1.0000
   8.250   1.2674   0.03098   0.02125  -0.0967   0.0383   1.0000
   8.500   1.2760   0.03254   0.02287  -0.0941   0.0338   1.0000
   8.750   1.2841   0.03448   0.02490  -0.0914   0.0311   1.0000
   9.000   1.2968   0.03621   0.02684  -0.0893   0.0281   1.0000
   9.250   1.3083   0.03790   0.02864  -0.0874   0.0254   1.0000
   9.500   1.3188   0.04012   0.03091  -0.0855   0.0234   1.0000
   9.750   1.3363   0.04273   0.03373  -0.0842   0.0222   1.0000
  10.000   1.3530   0.04527   0.03668  -0.0828   0.0209   1.0000
  10.250   1.3646   0.04781   0.03956  -0.0810   0.0195   1.0000
  10.500   1.3714   0.05034   0.04240  -0.0788   0.0182   1.0000
  10.750   1.3750   0.05312   0.04549  -0.0766   0.0174   1.0000
  11.000   1.3753   0.05628   0.04897  -0.0743   0.0169   1.0000
  11.250   1.3717   0.05963   0.05263  -0.0720   0.0166   1.0000
  11.500   1.3647   0.06323   0.05654  -0.0699   0.0163   1.0000
  11.750   1.3549   0.06713   0.06074  -0.0682   0.0162   1.0000
  12.000   1.3425   0.07141   0.06532  -0.0670   0.0160   1.0000
  12.250   1.3277   0.07613   0.07032  -0.0665   0.0160   1.0000
  12.500   1.3107   0.08138   0.07585  -0.0667   0.0159   1.0000
  12.750   1.2918   0.08723   0.08198  -0.0678   0.0160   1.0000
  13.000   1.2709   0.09386   0.08887  -0.0700   0.0160   1.0000
  13.250   1.2481   0.10143   0.09670  -0.0735   0.0162   1.0000
  13.500   1.2233   0.11029   0.10580  -0.0785   0.0164   1.0000
  13.750   1.1963   0.12098   0.11670  -0.0854   0.0167   1.0000
  14.000   1.1632   0.13581   0.13171  -0.0958   0.0174   1.0000
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