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GOE 381 AIRFOIL (goe381-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 381 AIRFOIL (goe381-il)
Reynolds number: 100,000
Max Cl/Cd: 58.9 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe381-il-100000.txt
Download as CSV file: xf-goe381-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 381 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2796   0.09684   0.09250  -0.0225   1.0000   0.0408
  -7.000  -0.2821   0.09607   0.09182  -0.0234   1.0000   0.0415
  -6.750  -0.2852   0.09584   0.09167  -0.0249   1.0000   0.0420
  -6.500  -0.2857   0.09566   0.09154  -0.0272   1.0000   0.0423
  -6.250  -0.2815   0.09517   0.09105  -0.0300   1.0000   0.0425
  -6.000  -0.2828   0.09056   0.08654  -0.0277   1.0000   0.0430
  -5.750  -0.2879   0.08553   0.08159  -0.0220   1.0000   0.0440
  -5.500  -0.2877   0.08276   0.07888  -0.0202   1.0000   0.0450
  -5.250  -0.2851   0.08035   0.07651  -0.0198   1.0000   0.0462
  -5.000  -0.2801   0.07801   0.07419  -0.0201   1.0000   0.0476
  -4.750  -0.2726   0.07566   0.07186  -0.0211   1.0000   0.0493
  -4.500  -0.2614   0.07336   0.06955  -0.0230   1.0000   0.0514
  -4.250  -0.1804   0.07196   0.06771  -0.0424   0.9932   0.0550
  -4.000  -0.1685   0.06466   0.06058  -0.0420   0.9873   0.0568
  -3.750  -0.1288   0.06032   0.05618  -0.0480   0.9802   0.0612
  -3.500  -0.0614   0.05686   0.05239  -0.0604   0.9717   0.0687
  -3.250  -0.0301   0.05242   0.04797  -0.0639   0.9634   0.0742
  -3.000   0.0357   0.04925   0.04439  -0.0741   0.9563   0.0823
  -2.750   0.0699   0.04533   0.04046  -0.0777   0.9464   0.0885
  -2.500   0.1265   0.04182   0.03669  -0.0852   0.9410   0.0994
  -2.250   0.1715   0.03906   0.03369  -0.0899   0.9302   0.1114
  -2.000   0.2196   0.03628   0.03064  -0.0948   0.9216   0.1243
  -1.750   0.2687   0.03352   0.02765  -0.0997   0.9144   0.1415
  -1.500   0.3090   0.03147   0.02533  -0.1028   0.9030   0.1752
  -1.000   0.3800   0.02655   0.02026  -0.1066   0.8814   0.2650
  -0.750   0.4158   0.02484   0.01835  -0.1073   0.8691   0.3018
  -0.500   0.4458   0.02308   0.01647  -0.1069   0.8531   0.3213
  -0.250   0.4819   0.02232   0.01523  -0.1065   0.8362   0.2873
   0.000   0.5234   0.02226   0.01435  -0.1048   0.8207   0.1577
   0.250   0.5548   0.02154   0.01320  -0.1032   0.8058   0.1195
   0.500   0.5825   0.02047   0.01197  -0.1022   0.7916   0.1138
   0.750   0.6099   0.01987   0.01117  -0.1013   0.7773   0.1179
   1.000   0.6370   0.01917   0.01034  -0.1003   0.7629   0.1168
   1.250   0.6638   0.01857   0.00962  -0.0993   0.7486   0.1169
   1.500   0.6905   0.01810   0.00903  -0.0983   0.7344   0.1197
   1.750   0.7157   0.01749   0.00843  -0.0971   0.7204   0.1267
   2.000   0.7419   0.01702   0.00788  -0.0962   0.7062   0.1433
   2.250   0.7681   0.01478   0.00724  -0.0955   0.6920   1.0000
   2.500   0.7943   0.01491   0.00705  -0.0945   0.6760   1.0000
   2.750   0.8200   0.01505   0.00694  -0.0935   0.6590   1.0000
   3.000   0.8455   0.01521   0.00688  -0.0925   0.6411   1.0000
   3.250   0.8702   0.01542   0.00697  -0.0916   0.6211   1.0000
   3.500   0.8953   0.01565   0.00705  -0.0907   0.6017   1.0000
   3.750   0.9200   0.01593   0.00720  -0.0899   0.5812   1.0000
   4.000   0.9445   0.01623   0.00737  -0.0890   0.5595   1.0000
   4.250   0.9685   0.01656   0.00758  -0.0880   0.5362   1.0000
   4.500   0.9926   0.01691   0.00781  -0.0871   0.5131   1.0000
   4.750   1.0161   0.01728   0.00813  -0.0862   0.4879   1.0000
   5.000   1.0396   0.01767   0.00845  -0.0854   0.4640   1.0000
   5.250   1.0632   0.01805   0.00874  -0.0846   0.4420   1.0000
   5.500   1.0868   0.01849   0.00917  -0.0838   0.4210   1.0000
   5.750   1.1106   0.01897   0.00964  -0.0832   0.4031   1.0000
   6.000   1.1342   0.01946   0.01008  -0.0825   0.3866   1.0000
   6.250   1.1560   0.01987   0.01045  -0.0815   0.3652   1.0000
   6.500   1.1775   0.02034   0.01087  -0.0806   0.3452   1.0000
   6.750   1.1977   0.02082   0.01136  -0.0795   0.3222   1.0000
   7.000   1.2174   0.02138   0.01184  -0.0785   0.3008   1.0000
   7.250   1.2384   0.02199   0.01250  -0.0775   0.2846   1.0000
   7.500   1.2591   0.02260   0.01321  -0.0766   0.2686   1.0000
   7.750   1.2762   0.02319   0.01379  -0.0752   0.2427   1.0000
   8.000   1.2944   0.02378   0.01446  -0.0740   0.2163   1.0000
   8.250   1.3135   0.02439   0.01514  -0.0729   0.1762   1.0000
   8.500   1.3245   0.02598   0.01615  -0.0710   0.1127   1.0000
   8.750   1.3292   0.02842   0.01810  -0.0683   0.0517   1.0000
   9.000   1.3374   0.03037   0.02018  -0.0659   0.0445   1.0000
   9.250   1.3451   0.03220   0.02222  -0.0635   0.0411   1.0000
   9.500   1.3523   0.03381   0.02408  -0.0610   0.0397   1.0000
   9.750   1.3554   0.03558   0.02609  -0.0582   0.0387   1.0000
  10.000   1.3558   0.03759   0.02832  -0.0555   0.0380   1.0000
  10.250   1.3541   0.03986   0.03085  -0.0531   0.0375   1.0000
  10.500   1.3511   0.04238   0.03355  -0.0511   0.0371   1.0000
  10.750   1.3476   0.04511   0.03646  -0.0494   0.0369   1.0000
  11.000   1.3445   0.04797   0.03946  -0.0479   0.0367   1.0000
  11.250   1.3432   0.05078   0.04239  -0.0466   0.0364   1.0000
  11.500   1.3443   0.05346   0.04514  -0.0453   0.0359   1.0000
  11.750   1.3483   0.05596   0.04769  -0.0437   0.0349   1.0000
  12.000   1.3592   0.05804   0.04974  -0.0417   0.0338   1.0000
  12.250   1.3832   0.05961   0.05134  -0.0393   0.0336   1.0000
  12.500   1.4055   0.06167   0.05361  -0.0375   0.0344   1.0000
  12.750   1.4188   0.06455   0.05686  -0.0359   0.0356   1.0000
  13.000   1.4230   0.06807   0.06072  -0.0347   0.0367   1.0000
  13.250   1.4216   0.07207   0.06503  -0.0338   0.0378   1.0000
  13.500   1.4160   0.07648   0.06974  -0.0333   0.0388   1.0000
  13.750   1.4075   0.08130   0.07483  -0.0332   0.0397   1.0000
  14.000   1.3978   0.08661   0.08039  -0.0335   0.0406   1.0000
  14.250   1.4065   0.09134   0.08532  -0.0327   0.0425   1.0000
  14.500   1.3868   0.09586   0.09010  -0.0344   0.0429   1.0000
  14.750   1.3650   0.10140   0.09590  -0.0371   0.0432   1.0000
  15.000   1.3422   0.10773   0.10247  -0.0406   0.0434   1.0000
  15.250   1.3187   0.11482   0.10978  -0.0450   0.0436   1.0000
  15.500   1.2951   0.12268   0.11784  -0.0503   0.0437   1.0000
  15.750   1.2713   0.13136   0.12670  -0.0565   0.0437   1.0000
  16.000   1.2470   0.14104   0.13653  -0.0636   0.0437   1.0000
  16.250   1.2217   0.15207   0.14769  -0.0719   0.0436   1.0000
  16.500   1.1928   0.16550   0.16117  -0.0819   0.0437   1.0000
  16.750   1.1343   0.19487   0.19043  -0.1017   0.0473   1.0000
  17.000   1.1336   0.20239   0.19791  -0.1052   0.0510   1.0000
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