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GOE 310 (MVA H.42) AIRFOIL (goe310-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 310 (MVA H.42) AIRFOIL (goe310-il)
Reynolds number: 500,000
Max Cl/Cd: 99.91 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe310-il-500000.txt
Download as CSV file: xf-goe310-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 310 (MVA H.42) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3479   0.09320   0.09103  -0.0348   1.0000   0.0210
  -8.500  -0.3577   0.09099   0.08888  -0.0334   1.0000   0.0210
  -8.250  -0.3708   0.08919   0.08712  -0.0313   0.9998   0.0210
  -8.000  -0.3564   0.08370   0.08163  -0.0391   0.9954   0.0211
  -7.750  -0.3466   0.07700   0.07493  -0.0448   0.9905   0.0215
  -7.500  -0.3268   0.07298   0.07089  -0.0496   0.9866   0.0218
  -7.250  -0.3037   0.06988   0.06776  -0.0537   0.9839   0.0223
  -7.000  -0.2842   0.06627   0.06413  -0.0580   0.9785   0.0232
  -6.750  -0.2599   0.06164   0.05945  -0.0643   0.9738   0.0244
  -6.500  -0.1894   0.02927   0.02696  -0.0831   0.9592   0.0278
  -6.250  -0.1641   0.02826   0.02594  -0.0841   0.9552   0.0285
  -6.000  -0.1463   0.02573   0.02333  -0.0852   0.9464   0.0295
  -5.750  -0.1262   0.02153   0.01898  -0.0878   0.9398   0.0313
  -5.500  -0.1148   0.01455   0.01120  -0.0900   0.9300   0.0348
  -5.250  -0.1124   0.00934   0.00562  -0.0888   0.9210   0.0371
  -5.000  -0.0903   0.00845   0.00468  -0.0884   0.9130   0.0394
  -3.750   0.0184   0.01383   0.00822  -0.0857   0.8841   0.0411
  -3.500   0.0436   0.01268   0.00677  -0.0845   0.8733   0.0381
  -3.250   0.0697   0.01199   0.00592  -0.0837   0.8619   0.0374
  -3.000   0.0954   0.01137   0.00520  -0.0830   0.8492   0.0376
  -2.750   0.1203   0.01083   0.00457  -0.0821   0.8348   0.0386
  -2.500   0.1452   0.01038   0.00403  -0.0812   0.8184   0.0387
  -2.250   0.1699   0.01002   0.00358  -0.0803   0.7995   0.0390
  -2.000   0.1944   0.00975   0.00319  -0.0793   0.7793   0.0393
  -1.750   0.2188   0.00954   0.00286  -0.0784   0.7591   0.0397
  -1.500   0.2432   0.00939   0.00260  -0.0775   0.7398   0.0404
  -1.250   0.2676   0.00927   0.00237  -0.0766   0.7224   0.0416
  -1.000   0.2924   0.00920   0.00218  -0.0757   0.7069   0.0423
  -0.750   0.3173   0.00914   0.00203  -0.0750   0.6932   0.0431
  -0.500   0.3425   0.00912   0.00191  -0.0743   0.6807   0.0440
  -0.250   0.3677   0.00911   0.00182  -0.0736   0.6696   0.0459
   0.000   0.3927   0.00910   0.00176  -0.0728   0.6586   0.0519
   0.250   0.4158   0.00888   0.00173  -0.0718   0.6464   0.1173
   0.500   0.4399   0.00885   0.00180  -0.0710   0.6333   0.1652
   0.750   0.4648   0.00890   0.00186  -0.0703   0.6216   0.1860
   1.000   0.4898   0.00897   0.00189  -0.0697   0.6107   0.1985
   1.250   0.5151   0.00901   0.00194  -0.0691   0.6009   0.2116
   1.500   0.5399   0.00905   0.00197  -0.0684   0.5893   0.2236
   1.750   0.5640   0.00908   0.00199  -0.0676   0.5755   0.2359
   2.000   0.5879   0.00910   0.00202  -0.0667   0.5622   0.2471
   2.250   0.6119   0.00913   0.00206  -0.0659   0.5509   0.2637
   2.500   0.6359   0.00909   0.00212  -0.0651   0.5400   0.2935
   2.750   0.6584   0.00897   0.00224  -0.0641   0.5289   0.3886
   3.000   0.7907   0.00818   0.00270  -0.0877   0.4957   0.9959
   3.250   0.8329   0.00835   0.00275  -0.0911   0.4667   1.0000
   3.500   0.8542   0.00855   0.00283  -0.0898   0.4401   1.0000
   3.750   0.8737   0.00885   0.00295  -0.0881   0.4001   1.0000
   4.000   0.8902   0.00938   0.00317  -0.0860   0.3390   1.0000
   4.250   0.9046   0.01010   0.00352  -0.0836   0.2694   1.0000
   4.500   0.9204   0.01074   0.00387  -0.0814   0.2160   1.0000
   4.750   0.9384   0.01122   0.00417  -0.0796   0.1834   1.0000
   5.000   0.9574   0.01160   0.00445  -0.0780   0.1600   1.0000
   5.250   0.9768   0.01196   0.00474  -0.0764   0.1424   1.0000
   5.500   0.9941   0.01245   0.00509  -0.0745   0.1129   1.0000
   5.750   1.0072   0.01321   0.00561  -0.0718   0.0681   1.0000
   6.000   1.0248   0.01366   0.00605  -0.0699   0.0633   1.0000
   6.250   1.0429   0.01405   0.00648  -0.0681   0.0592   1.0000
   6.500   1.0614   0.01442   0.00689  -0.0663   0.0573   1.0000
   6.750   1.0791   0.01481   0.00735  -0.0645   0.0554   1.0000
   7.000   1.0956   0.01527   0.00787  -0.0624   0.0535   1.0000
   7.250   1.1102   0.01582   0.00848  -0.0600   0.0513   1.0000
   7.500   1.1204   0.01659   0.00932  -0.0569   0.0483   1.0000
   7.750   1.1348   0.01710   0.00989  -0.0546   0.0461   1.0000
   8.000   1.1534   0.01736   0.01021  -0.0530   0.0430   1.0000
   8.250   1.1679   0.01783   0.01071  -0.0507   0.0393   1.0000
   8.500   1.1810   0.01824   0.01116  -0.0481   0.0348   1.0000
   8.750   1.2003   0.01837   0.01124  -0.0466   0.0289   1.0000
   9.000   1.2147   0.01871   0.01159  -0.0442   0.0251   1.0000
   9.250   1.2257   0.01925   0.01210  -0.0414   0.0223   1.0000
   9.500   1.2336   0.01998   0.01291  -0.0381   0.0207   1.0000
   9.750   1.2435   0.02068   0.01367  -0.0354   0.0193   1.0000
  10.000   1.2521   0.02149   0.01453  -0.0326   0.0183   1.0000
  10.250   1.2563   0.02262   0.01572  -0.0294   0.0172   1.0000
  10.500   1.2550   0.02417   0.01738  -0.0258   0.0163   1.0000
  10.750   1.2634   0.02518   0.01849  -0.0236   0.0157   1.0000
  11.000   1.2687   0.02648   0.01987  -0.0212   0.0152   1.0000
  11.250   1.2739   0.02785   0.02133  -0.0190   0.0145   1.0000
  11.500   1.2792   0.02928   0.02285  -0.0170   0.0142   1.0000
  11.750   1.2821   0.03099   0.02463  -0.0151   0.0136   1.0000
  12.000   1.2845   0.03283   0.02656  -0.0133   0.0133   1.0000
  12.250   1.2845   0.03499   0.02880  -0.0115   0.0129   1.0000
  12.500   1.2810   0.03762   0.03155  -0.0095   0.0125   1.0000
  12.750   1.2799   0.04022   0.03428  -0.0076   0.0123   1.0000
  13.000   1.2844   0.04225   0.03643  -0.0064   0.0121   1.0000
  13.250   1.2883   0.04440   0.03872  -0.0052   0.0120   1.0000
  13.500   1.2918   0.04661   0.04107  -0.0042   0.0117   1.0000
  13.750   1.2946   0.04892   0.04352  -0.0034   0.0115   1.0000
  14.000   1.2953   0.05156   0.04631  -0.0025   0.0113   1.0000
  14.250   1.2951   0.05433   0.04922  -0.0020   0.0110   1.0000
  14.500   1.2941   0.05720   0.05224  -0.0017   0.0107   1.0000
  14.750   1.2910   0.06047   0.05567  -0.0014   0.0106   1.0000
  15.000   1.2896   0.06345   0.05875  -0.0017   0.0103   1.0000
  15.250   1.2830   0.06738   0.06285  -0.0018   0.0102   1.0000
  15.500   1.2776   0.07110   0.06670  -0.0025   0.0100   1.0000
  15.750   1.2669   0.07585   0.07164  -0.0031   0.0100   1.0000
  16.000   1.2559   0.08077   0.07673  -0.0043   0.0099   1.0000
  16.250   1.2470   0.08543   0.08152  -0.0059   0.0098   1.0000
  16.500   1.2288   0.09191   0.08823  -0.0079   0.0099   1.0000
  16.750   1.2160   0.09766   0.09411  -0.0103   0.0098   1.0000
  17.000   1.1782   0.10862   0.10544  -0.0149   0.0102   1.0000
  17.250   1.1768   0.11263   0.10947  -0.0171   0.0099   1.0000
  17.500   1.1242   0.12839   0.12563  -0.0254   0.0103   1.0000
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