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GOE 702 AIRFOIL (goe702-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 702 AIRFOIL (goe702-il)
Reynolds number: 50,000
Max Cl/Cd: 20.63 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe702-il-50000-n5.txt
Download as CSV file: xf-goe702-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 702 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.2380   0.14632   0.13918  -0.0282   1.0000   0.1396
 -12.750  -0.2417   0.14476   0.13768  -0.0310   1.0000   0.1409
 -12.500  -0.2434   0.14271   0.13570  -0.0335   1.0000   0.1414
 -12.250  -0.2196   0.13753   0.13058  -0.0338   1.0000   0.1431
 -12.000  -0.2082   0.13433   0.12745  -0.0349   1.0000   0.1442
 -11.500  -0.2075   0.12532   0.11847  -0.0408   0.9881   0.1134
 -11.250  -0.1896   0.12133   0.11444  -0.0448   0.9569   0.1116
 -11.000  -0.1738   0.11714   0.11018  -0.0494   0.9423   0.1108
 -10.750  -0.1593   0.11278   0.10575  -0.0541   0.9308   0.1089
 -10.500  -0.1516   0.10806   0.10096  -0.0591   0.9204   0.1064
 -10.250  -0.1454   0.10364   0.09647  -0.0634   0.9098   0.1054
 -10.000  -0.1306   0.10049   0.09325  -0.0660   0.8998   0.1067
  -9.750  -0.1227   0.09739   0.09011  -0.0681   0.8887   0.1076
  -9.500  -0.1176   0.09417   0.08685  -0.0701   0.8782   0.1082
  -9.250  -0.1154   0.09076   0.08340  -0.0720   0.8677   0.1083
  -9.000  -0.1160   0.08745   0.08007  -0.0736   0.8559   0.1083
  -8.750  -0.1168   0.08427   0.07687  -0.0749   0.8451   0.1092
  -8.500  -0.1201   0.08096   0.07354  -0.0764   0.8344   0.1104
  -8.250  -0.1289   0.07713   0.06971  -0.0784   0.8236   0.1116
  -8.000  -0.1442   0.07266   0.06523  -0.0809   0.8143   0.1123
  -7.750  -0.1664   0.06755   0.06009  -0.0840   0.8043   0.1127
  -7.500  -0.1998   0.05973   0.05203  -0.0886   0.7963   0.1136
  -7.250  -0.2265   0.05343   0.04529  -0.0905   0.7878   0.1155
  -7.000  -0.2069   0.05309   0.04503  -0.0891   0.7789   0.1176
  -6.750  -0.1975   0.05107   0.04283  -0.0883   0.7721   0.1201
  -6.500  -0.1957   0.04823   0.03971  -0.0880   0.7626   0.1227
  -6.250  -0.1934   0.04454   0.03542  -0.0876   0.7555   0.1266
  -6.000  -0.1782   0.04312   0.03385  -0.0866   0.7476   0.1298
  -5.750  -0.1604   0.04219   0.03285  -0.0855   0.7389   0.1332
  -5.500  -0.1428   0.04043   0.03073  -0.0845   0.7327   0.1378
  -5.250  -0.1289   0.03891   0.02887  -0.0835   0.7232   0.1425
  -5.000  -0.1068   0.03825   0.02821  -0.0824   0.7154   0.1467
  -4.750  -0.0859   0.03714   0.02682  -0.0814   0.7085   0.1525
  -4.500  -0.0676   0.03627   0.02575  -0.0803   0.6986   0.1580
  -4.250  -0.0430   0.03558   0.02501  -0.0793   0.6921   0.1637
  -4.000  -0.0239   0.03486   0.02398  -0.0783   0.6822   0.1711
  -3.750  -0.0001   0.03436   0.02353  -0.0773   0.6742   0.1769
  -3.500   0.0234   0.03378   0.02276  -0.0764   0.6666   0.1854
  -3.250   0.0447   0.03346   0.02243  -0.0754   0.6566   0.1923
  -3.000   0.0719   0.03285   0.02164  -0.0746   0.6506   0.2021
  -2.750   0.0913   0.03278   0.02158  -0.0735   0.6392   0.2095
  -2.500   0.1181   0.03228   0.02094  -0.0728   0.6323   0.2202
  -2.250   0.1396   0.03219   0.02086  -0.0718   0.6225   0.2288
  -1.750   0.1923   0.03154   0.02005  -0.0705   0.6077   0.2524
  -1.500   0.2142   0.03159   0.02007  -0.0698   0.5971   0.2651
  -1.250   0.2441   0.03115   0.01949  -0.0694   0.5915   0.2823
  -1.000   0.2635   0.03144   0.01981  -0.0685   0.5809   0.2974
  -0.750   0.2911   0.03117   0.01949  -0.0679   0.5744   0.3174
  -0.500   0.3144   0.03123   0.01953  -0.0672   0.5666   0.3378
  -0.250   0.3370   0.03133   0.01963  -0.0664   0.5583   0.3592
   0.000   0.3665   0.03096   0.01920  -0.0659   0.5535   0.3848
   0.250   0.3828   0.03153   0.01986  -0.0648   0.5439   0.4059
   0.500   0.4084   0.03138   0.01974  -0.0641   0.5380   0.4327
   0.750   0.4385   0.03091   0.01925  -0.0637   0.5340   0.4658
   1.000   0.4494   0.03173   0.02030  -0.0622   0.5240   0.4933
   1.250   0.4747   0.03135   0.02013  -0.0613   0.5192   0.5404
   1.500   0.5011   0.03054   0.01991  -0.0602   0.5152   0.6448
   2.000   0.5967   0.03125   0.02075  -0.0682   0.5010   1.0000
   2.250   0.6194   0.03163   0.02091  -0.0673   0.4963   1.0000
   2.500   0.6259   0.03307   0.02230  -0.0653   0.4886   1.0000
   2.750   0.6488   0.03344   0.02249  -0.0644   0.4842   1.0000
   3.000   0.6781   0.03342   0.02226  -0.0640   0.4811   1.0000
   3.250   0.6747   0.03552   0.02438  -0.0614   0.4732   1.0000
   3.500   0.6902   0.03637   0.02514  -0.0601   0.4680   1.0000
   3.750   0.7174   0.03650   0.02510  -0.0595   0.4647   1.0000
   4.000   0.7500   0.03636   0.02479  -0.0593   0.4623   1.0000
   4.250   0.7124   0.04073   0.02933  -0.0548   0.4520   1.0000
   4.500   0.7324   0.04137   0.02987  -0.0538   0.4482   1.0000
   4.750   0.7631   0.04132   0.02969  -0.0535   0.4457   1.0000
   5.250   0.7120   0.04924   0.03769  -0.0477   0.4295   1.0000
   5.500   0.7380   0.04949   0.03785  -0.0470   0.4273   1.0000
   5.750   0.7701   0.04925   0.03751  -0.0465   0.4257   1.0000
   6.750   0.6760   0.07050   0.05893  -0.0445   0.3926   1.0000
   7.000   0.6975   0.07123   0.05962  -0.0438   0.3901   1.0000
   7.250   0.7233   0.07154   0.05987  -0.0430   0.3883   1.0000
   7.750   0.6845   0.08221   0.07063  -0.0438   0.3742   1.0000
   8.000   0.7036   0.08332   0.07170  -0.0433   0.3715   1.0000
   8.250   0.7276   0.08392   0.07228  -0.0426   0.3695   1.0000
   8.500   0.6896   0.09143   0.07987  -0.0440   0.3610   1.0000
   8.750   0.6960   0.09402   0.08247  -0.0440   0.3571   1.0000
   9.000   0.7123   0.09552   0.08396  -0.0436   0.3540   1.0000
   9.250   0.7345   0.09642   0.08484  -0.0431   0.3519   1.0000
   9.500   0.7146   0.10199   0.09048  -0.0441   0.3457   1.0000
   9.750   0.7135   0.10549   0.09400  -0.0446   0.3411   1.0000
  10.000   0.7255   0.10752   0.09605  -0.0445   0.3376   1.0000
  10.250   0.7442   0.10884   0.09738  -0.0442   0.3350   1.0000
  10.500   0.7675   0.10973   0.09826  -0.0436   0.3331   1.0000
  10.750   0.7368   0.11653   0.10515  -0.0456   0.3260   1.0000
  11.000   0.7433   0.11918   0.10784  -0.0459   0.3220   1.0000
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