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GOE 377 AIRFOIL (goe377-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 377 AIRFOIL (goe377-il)
Reynolds number: 1,000,000
Max Cl/Cd: 105.16 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe377-il-1000000-n5.txt
Download as CSV file: xf-goe377-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 377 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2832   0.10299   0.10145  -0.0267   1.0000   0.0044
 -10.000  -0.3827   0.11234   0.11067  -0.0203   1.0000   0.0030
  -9.750  -0.3801   0.10826   0.10660  -0.0214   1.0000   0.0036
  -9.500  -0.3762   0.10542   0.10377  -0.0220   1.0000   0.0034
  -9.250  -0.3719   0.10277   0.10115  -0.0227   1.0000   0.0041
  -8.750  -0.3680   0.09642   0.09483  -0.0238   1.0000   0.0033
  -8.250  -0.2696   0.07228   0.07083  -0.0338   0.9935   0.0036
  -8.000  -0.3684   0.08755   0.08604  -0.0245   0.9999   0.0036
  -7.750  -0.3550   0.08306   0.08155  -0.0297   0.9966   0.0035
  -7.500  -0.3420   0.07875   0.07725  -0.0351   0.9890   0.0035
  -7.250  -0.3245   0.07370   0.07219  -0.0420   0.9812   0.0034
  -6.750  -0.2724   0.06253   0.06093  -0.0593   0.9672   0.0032
  -6.250  -0.2541   0.01551   0.01185  -0.0847   0.9248   0.0036
  -6.000  -0.2322   0.01343   0.00938  -0.0839   0.9162   0.0037
  -5.750  -0.2093   0.01180   0.00742  -0.0831   0.9092   0.0040
  -5.500  -0.1843   0.01100   0.00643  -0.0826   0.9023   0.0043
  -5.250  -0.1585   0.01047   0.00578  -0.0823   0.8963   0.0046
  -5.000  -0.1328   0.00997   0.00515  -0.0818   0.8894   0.0050
  -4.750  -0.1067   0.00956   0.00462  -0.0814   0.8833   0.0055
  -4.500  -0.0806   0.00919   0.00414  -0.0810   0.8765   0.0059
  -4.250  -0.0551   0.00864   0.00344  -0.0804   0.8699   0.0068
  -4.000  -0.0292   0.00830   0.00303  -0.0800   0.8625   0.0077
  -3.750  -0.0031   0.00804   0.00268  -0.0795   0.8554   0.0087
  -3.500   0.0231   0.00778   0.00234  -0.0791   0.8473   0.0102
  -3.250   0.0493   0.00759   0.00216  -0.0786   0.8390   0.0140
  -3.000   0.0758   0.00754   0.00212  -0.0783   0.8283   0.0195
  -2.750   0.1022   0.00757   0.00210  -0.0779   0.8122   0.0233
  -2.500   0.1281   0.00770   0.00213  -0.0773   0.7887   0.0254
  -2.250   0.1534   0.00780   0.00212  -0.0767   0.7613   0.0260
  -2.000   0.1786   0.00792   0.00213  -0.0760   0.7332   0.0264
  -1.750   0.2030   0.00777   0.00183  -0.0752   0.7084   0.0271
  -1.250   0.2527   0.00751   0.00134  -0.0739   0.6667   0.0292
  -1.000   0.2779   0.00746   0.00118  -0.0733   0.6464   0.0294
  -0.750   0.3033   0.00743   0.00104  -0.0727   0.6255   0.0298
  -0.500   0.3285   0.00744   0.00094  -0.0721   0.6022   0.0305
  -0.250   0.3541   0.00745   0.00087  -0.0716   0.5832   0.0322
   0.000   0.3799   0.00747   0.00083  -0.0711   0.5655   0.0351
   0.250   0.4058   0.00751   0.00081  -0.0707   0.5487   0.0372
   0.500   0.4315   0.00754   0.00080  -0.0703   0.5319   0.0437
   1.250   0.5074   0.00772   0.00088  -0.0688   0.4667   0.0994
   1.500   0.5322   0.00764   0.00095  -0.0683   0.4496   0.1910
   1.750   0.5554   0.00742   0.00105  -0.0675   0.4306   0.3628
   2.250   0.6658   0.00652   0.00139  -0.0809   0.3608   1.0000
   2.500   0.6892   0.00674   0.00149  -0.0800   0.3365   1.0000
   2.750   0.7122   0.00699   0.00161  -0.0791   0.3096   1.0000
   3.000   0.7359   0.00720   0.00173  -0.0783   0.2900   1.0000
   3.500   0.7832   0.00760   0.00198  -0.0767   0.2559   1.0000
   3.750   0.8076   0.00775   0.00211  -0.0760   0.2462   1.0000
   4.000   0.8318   0.00791   0.00224  -0.0753   0.2360   1.0000
   4.250   0.8546   0.00819   0.00242  -0.0744   0.2140   1.0000
   4.500   0.8776   0.00845   0.00260  -0.0736   0.1930   1.0000
   4.750   0.8983   0.00892   0.00286  -0.0723   0.1508   1.0000
   5.000   0.9168   0.00959   0.00326  -0.0707   0.0998   1.0000
   5.250   0.9355   0.01026   0.00370  -0.0691   0.0513   1.0000
   5.500   0.9559   0.01080   0.00410  -0.0678   0.0229   1.0000
   5.750   0.9780   0.01117   0.00444  -0.0668   0.0119   1.0000
   6.000   1.0003   0.01152   0.00483  -0.0657   0.0084   1.0000
   6.250   1.0232   0.01180   0.00514  -0.0649   0.0074   1.0000
   6.500   1.0453   0.01215   0.00550  -0.0639   0.0062   1.0000
   6.750   1.0667   0.01258   0.00598  -0.0628   0.0052   1.0000
   7.000   1.0887   0.01293   0.00638  -0.0617   0.0048   1.0000
   7.250   1.1102   0.01333   0.00684  -0.0607   0.0043   1.0000
   7.500   1.1314   0.01375   0.00730  -0.0595   0.0040   1.0000
   7.750   1.1511   0.01431   0.00790  -0.0582   0.0036   1.0000
   8.000   1.1708   0.01484   0.00850  -0.0569   0.0032   1.0000
   8.250   1.1907   0.01535   0.00907  -0.0555   0.0029   1.0000
   8.500   1.2102   0.01587   0.00966  -0.0542   0.0028   1.0000
   8.750   1.2284   0.01649   0.01035  -0.0527   0.0026   1.0000
   9.000   1.2460   0.01713   0.01107  -0.0511   0.0024   1.0000
   9.250   1.2641   0.01770   0.01171  -0.0496   0.0023   1.0000
   9.500   1.2797   0.01845   0.01253  -0.0478   0.0021   1.0000
   9.750   1.2913   0.01948   0.01367  -0.0452   0.0020   1.0000
  10.000   1.3020   0.02050   0.01481  -0.0426   0.0019   1.0000
  10.250   1.3118   0.02144   0.01585  -0.0399   0.0019   1.0000
  10.500   1.3208   0.02227   0.01679  -0.0369   0.0018   1.0000
  10.750   1.3278   0.02327   0.01791  -0.0338   0.0017   1.0000
  11.000   1.3303   0.02464   0.01941  -0.0303   0.0017   1.0000
  11.250   1.3351   0.02590   0.02081  -0.0274   0.0017   1.0000
  11.500   1.3380   0.02739   0.02245  -0.0245   0.0016   1.0000
  11.750   1.3401   0.02901   0.02421  -0.0218   0.0016   1.0000
  12.000   1.3396   0.03096   0.02631  -0.0191   0.0014   1.0000
  12.250   1.3399   0.03290   0.02840  -0.0169   0.0015   1.0000
  12.500   1.3502   0.03387   0.02943  -0.0159   0.0013   1.0000
  12.750   1.3478   0.03624   0.03196  -0.0141   0.0013   1.0000
  13.000   1.3392   0.03943   0.03535  -0.0123   0.0013   1.0000
  13.250   1.3405   0.04168   0.03771  -0.0117   0.0013   1.0000
  13.500   1.3358   0.04478   0.04096  -0.0112   0.0013   1.0000
  13.750   1.3355   0.04752   0.04380  -0.0112   0.0012   1.0000
  14.000   1.3223   0.05215   0.04862  -0.0117   0.0012   1.0000
  14.250   1.3001   0.05847   0.05519  -0.0130   0.0012   1.0000
  14.500   1.3048   0.06108   0.05789  -0.0142   0.0012   1.0000
  14.750   1.3048   0.06457   0.06145  -0.0157   0.0012   1.0000
  15.000   1.3002   0.06897   0.06595  -0.0177   0.0011   1.0000
  15.250   1.2711   0.07770   0.07490  -0.0214   0.0011   1.0000
  15.500   1.2609   0.08349   0.08081  -0.0241   0.0012   1.0000
  15.750   1.2307   0.09332   0.09085  -0.0287   0.0012   1.0000
  16.000   1.2175   0.10021   0.09784  -0.0322   0.0012   1.0000
  16.250   1.1886   0.11062   0.10844  -0.0374   0.0012   1.0000
  16.500   1.1721   0.11868   0.11660  -0.0416   0.0012   1.0000
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