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GOE 410 AIRFOIL (goe410-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 410 AIRFOIL (goe410-il)
Reynolds number: 50,000
Max Cl/Cd: 20.94 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe410-il-50000.txt
Download as CSV file: xf-goe410-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 410 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5363   0.10226   0.09367   0.0064   1.0000   0.3058
  -9.500  -0.5677   0.09212   0.08356   0.0008   1.0000   0.2887
  -9.250  -0.5609   0.08808   0.07952   0.0001   1.0000   0.2899
  -9.000  -0.5541   0.08435   0.07579  -0.0006   1.0000   0.2918
  -8.750  -0.6377   0.06875   0.06029  -0.0094   1.0000   0.2858
  -8.500  -0.7727   0.05145   0.04289  -0.0138   1.0000   0.2819
  -8.250  -0.8048   0.04553   0.03664  -0.0125   1.0000   0.2854
  -8.000  -0.8076   0.04204   0.03292  -0.0112   1.0000   0.2905
  -7.750  -0.7821   0.04123   0.03221  -0.0104   1.0000   0.2981
  -7.500  -0.7851   0.03802   0.02866  -0.0088   1.0000   0.3063
  -7.250  -0.7557   0.03770   0.02857  -0.0079   1.0000   0.3156
  -7.000  -0.7458   0.03568   0.02642  -0.0065   1.0000   0.3257
  -6.750  -0.7270   0.03472   0.02551  -0.0052   1.0000   0.3377
  -6.500  -0.7049   0.03420   0.02514  -0.0038   1.0000   0.3504
  -6.250  -0.6877   0.03340   0.02441  -0.0020   1.0000   0.3651
  -6.000  -0.6713   0.03280   0.02390  -0.0001   1.0000   0.3817
  -5.750  -0.6548   0.03252   0.02376   0.0022   1.0000   0.4001
  -5.500  -0.6394   0.03245   0.02384   0.0049   1.0000   0.4202
  -5.250  -0.6277   0.03249   0.02403   0.0081   1.0000   0.4421
  -5.000  -0.6225   0.03240   0.02402   0.0118   1.0000   0.4649
  -4.750  -0.6230   0.03211   0.02375   0.0157   1.0000   0.4880
  -4.500  -0.6175   0.03241   0.02416   0.0194   1.0000   0.5081
  -4.250  -0.6134   0.03258   0.02438   0.0229   1.0000   0.5274
  -4.000  -0.6055   0.03309   0.02499   0.0263   1.0000   0.5443
  -3.750  -0.5977   0.03352   0.02549   0.0295   1.0000   0.5604
  -3.500  -0.5712   0.03402   0.02600   0.0294   0.9930   0.5811
  -3.250  -0.5202   0.03438   0.02625   0.0248   0.9744   0.6063
  -3.000  -0.4689   0.03502   0.02688   0.0213   0.9574   0.6263
  -2.750  -0.4187   0.03556   0.02737   0.0181   0.9410   0.6449
  -2.500  -0.3692   0.03623   0.02804   0.0156   0.9257   0.6641
  -2.250  -0.3193   0.03680   0.02859   0.0131   0.9113   0.6854
  -2.000  -0.2447   0.03756   0.02935   0.0078   0.8993   0.7063
  -1.750  -0.1957   0.03779   0.02956   0.0053   0.8847   0.7207
  -1.500  -0.1539   0.03755   0.02928   0.0028   0.8706   0.7321
  -1.250  -0.1344   0.03681   0.02847   0.0022   0.8577   0.7441
  -1.000  -0.0818   0.03677   0.02842  -0.0012   0.8446   0.7533
  -0.750  -0.0886   0.03629   0.02790   0.0020   0.8310   0.7646
  -0.500  -0.0297   0.03627   0.02787  -0.0021   0.8203   0.7741
  -0.250  -0.0291   0.03606   0.02765   0.0006   0.8075   0.7857
   0.000   0.0000   0.03619   0.02778   0.0000   0.7959   0.7959
   0.250   0.0296   0.03606   0.02764  -0.0006   0.7856   0.8075
   0.500   0.0302   0.03627   0.02787   0.0020   0.7740   0.8202
   0.750   0.0887   0.03629   0.02790  -0.0020   0.7646   0.8309
   1.000   0.0820   0.03677   0.02842   0.0012   0.7533   0.8447
   1.250   0.1341   0.03681   0.02847  -0.0021   0.7441   0.8576
   1.500   0.1541   0.03755   0.02928  -0.0028   0.7320   0.8706
   1.750   0.1957   0.03778   0.02955  -0.0053   0.7207   0.8847
   2.000   0.2454   0.03753   0.02932  -0.0078   0.7062   0.8993
   2.250   0.3190   0.03680   0.02860  -0.0131   0.6855   0.9113
   2.500   0.3691   0.03622   0.02803  -0.0156   0.6640   0.9257
   2.750   0.4189   0.03554   0.02736  -0.0181   0.6450   0.9410
   3.000   0.4690   0.03502   0.02687  -0.0213   0.6263   0.9575
   3.250   0.5202   0.03437   0.02624  -0.0248   0.6063   0.9745
   3.500   0.5712   0.03400   0.02598  -0.0294   0.5809   0.9930
   3.750   0.5977   0.03352   0.02549  -0.0295   0.5605   1.0000
   4.000   0.6055   0.03308   0.02498  -0.0263   0.5444   1.0000
   4.250   0.6133   0.03258   0.02438  -0.0229   0.5274   1.0000
   4.500   0.6174   0.03241   0.02416  -0.0194   0.5081   1.0000
   4.750   0.6228   0.03212   0.02377  -0.0157   0.4881   1.0000
   5.000   0.6225   0.03239   0.02402  -0.0118   0.4649   1.0000
   5.250   0.6277   0.03249   0.02403  -0.0081   0.4422   1.0000
   5.500   0.6393   0.03246   0.02385  -0.0049   0.4203   1.0000
   5.750   0.6548   0.03251   0.02375  -0.0022   0.4001   1.0000
   6.000   0.6713   0.03281   0.02391   0.0001   0.3817   1.0000
   6.250   0.6877   0.03341   0.02441   0.0020   0.3651   1.0000
   6.500   0.7050   0.03420   0.02514   0.0038   0.3505   1.0000
   6.750   0.7271   0.03472   0.02550   0.0052   0.3378   1.0000
   7.000   0.7456   0.03569   0.02644   0.0065   0.3258   1.0000
   7.250   0.7557   0.03770   0.02857   0.0079   0.3156   1.0000
   7.500   0.7850   0.03803   0.02868   0.0088   0.3063   1.0000
   7.750   0.7822   0.04122   0.03221   0.0104   0.2981   1.0000
   8.000   0.8074   0.04207   0.03295   0.0112   0.2905   1.0000
   8.250   0.8050   0.04551   0.03662   0.0125   0.2854   1.0000
   8.500   0.7730   0.05143   0.04287   0.0138   0.2818   1.0000
   8.750   0.6391   0.06861   0.06015   0.0094   0.2858   1.0000
   9.000   0.5496   0.08495   0.07637   0.0001   0.2924   1.0000
   9.250   0.5731   0.08662   0.07806   0.0010   0.2878   1.0000
   9.500   0.5669   0.09225   0.08368  -0.0011   0.2888   1.0000
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