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GOE 311 (MVA H.43) AIRFOIL (goe311-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 311 (MVA H.43) AIRFOIL (goe311-il)
Reynolds number: 100,000
Max Cl/Cd: 57.54 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe311-il-100000.txt
Download as CSV file: xf-goe311-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 311 (MVA H.43) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2707   0.09939   0.09498  -0.0293   1.0000   0.0730
  -7.750  -0.2707   0.09723   0.09290  -0.0293   1.0000   0.0752
  -7.500  -0.2799   0.09597   0.09176  -0.0278   1.0000   0.0768
  -7.250  -0.2971   0.09551   0.09143  -0.0252   1.0000   0.0779
  -7.000  -0.3161   0.09540   0.09145  -0.0231   1.0000   0.0787
  -6.750  -0.3359   0.09559   0.09176  -0.0216   1.0000   0.0792
  -6.500  -0.3197   0.09211   0.08827  -0.0308   0.9941   0.0805
  -6.250  -0.2979   0.08655   0.08273  -0.0286   0.9894   0.0833
  -5.750  -0.2236   0.07684   0.07289  -0.0471   0.9719   0.0950
  -5.250  -0.1441   0.06751   0.06336  -0.0630   0.9553   0.1089
  -5.000  -0.0880   0.06389   0.05942  -0.0769   0.9439   0.1196
  -4.750  -0.0685   0.05912   0.05474  -0.0757   0.9335   0.1238
  -4.500  -0.0228   0.05555   0.05087  -0.0845   0.9208   0.1345
  -4.250   0.0022   0.05153   0.04683  -0.0851   0.9096   0.1393
  -4.000   0.0365   0.04814   0.04321  -0.0889   0.8966   0.1510
  -3.750   0.0688   0.04526   0.04004  -0.0916   0.8826   0.1639
  -3.500   0.0934   0.04262   0.03724  -0.0918   0.8684   0.1788
  -3.250   0.1171   0.04028   0.03474  -0.0916   0.8540   0.1942
  -3.000   0.1427   0.03831   0.03252  -0.0918   0.8397   0.2085
  -2.750   0.1655   0.03643   0.03049  -0.0912   0.8257   0.2243
  -2.500   0.1905   0.03478   0.02864  -0.0911   0.8121   0.2390
  -2.250   0.2407   0.02925   0.02192  -0.0951   0.8008   0.1459
  -2.000   0.2686   0.02753   0.01982  -0.0950   0.7894   0.1460
  -1.750   0.2967   0.02587   0.01778  -0.0947   0.7804   0.1452
  -1.500   0.3249   0.02447   0.01602  -0.0946   0.7692   0.1449
  -1.250   0.3536   0.02328   0.01438  -0.0945   0.7597   0.1471
  -1.000   0.3809   0.02241   0.01336  -0.0941   0.7517   0.1513
  -0.750   0.4085   0.02188   0.01264  -0.0940   0.7423   0.1589
  -0.500   0.4361   0.02140   0.01200  -0.0936   0.7358   0.1723
  -0.250   0.4630   0.02107   0.01163  -0.0936   0.7268   0.1940
   0.000   0.4904   0.02081   0.01125  -0.0932   0.7209   0.2189
   0.250   0.5170   0.02087   0.01128  -0.0933   0.7128   0.2362
   0.500   0.5442   0.02083   0.01119  -0.0930   0.7069   0.2520
   0.750   0.5707   0.02092   0.01130  -0.0931   0.6996   0.2615
   1.000   0.5978   0.02095   0.01131  -0.0929   0.6935   0.2744
   1.250   0.6244   0.02108   0.01145  -0.0928   0.6875   0.2920
   1.500   0.6507   0.02118   0.01161  -0.0927   0.6807   0.3057
   1.750   0.6788   0.02110   0.01150  -0.0924   0.6759   0.3132
   2.000   0.7045   0.02137   0.01183  -0.0924   0.6686   0.3212
   2.250   0.7310   0.02137   0.01185  -0.0920   0.6630   0.3315
   2.500   0.7565   0.02152   0.01207  -0.0917   0.6570   0.3462
   2.750   0.7817   0.02162   0.01231  -0.0914   0.6505   0.3713
   3.000   0.8187   0.02032   0.01216  -0.0926   0.6457   1.0000
   3.250   0.8426   0.02095   0.01272  -0.0923   0.6377   1.0000
   3.500   0.8695   0.02115   0.01279  -0.0918   0.6322   1.0000
   3.750   0.8932   0.02170   0.01335  -0.0914   0.6244   1.0000
   4.000   0.9200   0.02179   0.01335  -0.0907   0.6177   1.0000
   4.250   0.9436   0.02217   0.01375  -0.0901   0.6084   1.0000
   4.500   0.9719   0.02205   0.01352  -0.0894   0.6016   1.0000
   4.750   0.9947   0.02248   0.01403  -0.0887   0.5913   1.0000
   5.000   1.0201   0.02264   0.01419  -0.0880   0.5825   1.0000
   5.250   1.0471   0.02259   0.01408  -0.0872   0.5736   1.0000
   5.500   1.0705   0.02290   0.01449  -0.0864   0.5627   1.0000
   5.750   1.0960   0.02305   0.01464  -0.0857   0.5530   1.0000
   6.000   1.1226   0.02315   0.01471  -0.0851   0.5439   1.0000
   6.250   1.1452   0.02363   0.01533  -0.0843   0.5334   1.0000
   6.500   1.1711   0.02389   0.01563  -0.0837   0.5245   1.0000
   6.750   1.1958   0.02420   0.01602  -0.0831   0.5146   1.0000
   7.000   1.2180   0.02469   0.01666  -0.0822   0.5036   1.0000
   7.250   1.2432   0.02496   0.01703  -0.0816   0.4938   1.0000
   7.500   1.2683   0.02517   0.01731  -0.0809   0.4832   1.0000
   7.750   1.2907   0.02516   0.01741  -0.0797   0.4688   1.0000
   8.000   1.3140   0.02461   0.01688  -0.0783   0.4514   1.0000
   8.250   1.3327   0.02444   0.01691  -0.0766   0.4330   1.0000
   8.500   1.3519   0.02421   0.01687  -0.0749   0.4140   1.0000
   8.750   1.3713   0.02397   0.01670  -0.0732   0.3941   1.0000
   9.000   1.3874   0.02411   0.01699  -0.0713   0.3701   1.0000
   9.250   1.4000   0.02437   0.01719  -0.0688   0.3384   1.0000
   9.500   1.4097   0.02511   0.01786  -0.0662   0.3068   1.0000
   9.750   1.4120   0.02635   0.01896  -0.0628   0.2661   1.0000
  10.000   1.4056   0.02810   0.02048  -0.0586   0.2224   1.0000
  10.250   1.3922   0.03045   0.02257  -0.0541   0.1761   1.0000
  10.500   1.3734   0.03370   0.02543  -0.0503   0.1128   1.0000
  10.750   1.3528   0.03760   0.02896  -0.0475   0.0882   1.0000
  11.000   1.3358   0.04167   0.03293  -0.0456   0.0762   1.0000
  11.250   1.3254   0.04540   0.03676  -0.0443   0.0660   1.0000
  11.500   1.3180   0.04899   0.04046  -0.0434   0.0596   1.0000
  11.750   1.3116   0.05258   0.04416  -0.0428   0.0553   1.0000
  12.000   1.3031   0.05648   0.04810  -0.0424   0.0527   1.0000
  12.250   1.2992   0.05990   0.05166  -0.0419   0.0503   1.0000
  12.500   1.2958   0.06325   0.05512  -0.0415   0.0483   1.0000
  12.750   1.2933   0.06648   0.05842  -0.0410   0.0464   1.0000
  13.000   1.2912   0.06961   0.06157  -0.0404   0.0446   1.0000
  13.250   1.2937   0.07191   0.06385  -0.0390   0.0427   1.0000
  13.500   1.3007   0.07388   0.06594  -0.0377   0.0408   1.0000
  13.750   1.3114   0.07536   0.06752  -0.0358   0.0393   1.0000
  14.000   1.3275   0.07634   0.06855  -0.0333   0.0381   1.0000
  14.250   1.3455   0.07752   0.06982  -0.0309   0.0373   1.0000
  14.500   1.3621   0.07939   0.07185  -0.0288   0.0368   1.0000
  14.750   1.3729   0.08222   0.07491  -0.0274   0.0366   1.0000
  15.000   1.3756   0.08585   0.07876  -0.0268   0.0364   1.0000
  15.250   1.3721   0.09003   0.08317  -0.0269   0.0361   1.0000
  15.500   1.3646   0.09464   0.08802  -0.0275   0.0358   1.0000
  15.750   1.3529   0.09980   0.09343  -0.0286   0.0358   1.0000
  16.000   1.3387   0.10541   0.09930  -0.0304   0.0358   1.0000
  16.250   1.3195   0.11200   0.10619  -0.0333   0.0361   1.0000
  16.500   1.2962   0.11967   0.11418  -0.0371   0.0367   1.0000
  16.750   1.2558   0.13138   0.12629  -0.0445   0.0382   1.0000
  17.000   1.2235   0.14272   0.13790  -0.0519   0.0394   1.0000
  17.250   1.1929   0.15488   0.15024  -0.0601   0.0407   1.0000
  17.500   1.1657   0.16751   0.16297  -0.0686   0.0418   1.0000
  17.750   1.1483   0.17834   0.17382  -0.0752   0.0428   1.0000
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