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GOE 143 (MVA H.20) AIRFOIL (goe143-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 143 (MVA H.20) AIRFOIL (goe143-il)
Reynolds number: 1,000,000
Max Cl/Cd: 98.18 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe143-il-1000000-n5.txt
Download as CSV file: xf-goe143-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 143 (MVA H.20) 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5216   0.09788   0.09628  -0.0042   1.0000   0.0083
  -9.750  -0.5205   0.09359   0.09201  -0.0066   1.0000   0.0087
  -9.250  -0.6443   0.01741   0.01370  -0.0739   1.0000   0.0112
  -9.000  -0.6219   0.01521   0.01125  -0.0740   1.0000   0.0125
  -8.750  -0.5978   0.01413   0.01003  -0.0737   1.0000   0.0138
  -8.500  -0.5697   0.01337   0.00921  -0.0741   0.9986   0.0159
  -8.250  -0.5380   0.01278   0.00852  -0.0751   0.9961   0.0177
  -8.000  -0.5059   0.01259   0.00834  -0.0760   0.9928   0.0193
  -7.750  -0.4739   0.01252   0.00829  -0.0768   0.9884   0.0208
  -7.500  -0.4420   0.01226   0.00797  -0.0776   0.9835   0.0220
  -7.250  -0.4105   0.01193   0.00756  -0.0784   0.9753   0.0227
  -7.000  -0.3812   0.01169   0.00723  -0.0786   0.9612   0.0232
  -6.750  -0.3552   0.01133   0.00677  -0.0780   0.9407   0.0240
  -6.500  -0.3297   0.01128   0.00666  -0.0772   0.9178   0.0248
  -6.250  -0.3034   0.01128   0.00659  -0.0766   0.8942   0.0254
  -6.000  -0.2770   0.01129   0.00651  -0.0761   0.8713   0.0261
  -5.750  -0.2499   0.01130   0.00643  -0.0757   0.8514   0.0268
  -5.500  -0.2224   0.01127   0.00630  -0.0755   0.8348   0.0276
  -5.250  -0.1948   0.01108   0.00600  -0.0753   0.8211   0.0283
  -5.000  -0.1670   0.01083   0.00564  -0.0752   0.8090   0.0288
  -4.750  -0.1391   0.01050   0.00519  -0.0751   0.7977   0.0291
  -4.500  -0.1112   0.01019   0.00476  -0.0750   0.7861   0.0293
  -4.250  -0.0831   0.00989   0.00437  -0.0749   0.7746   0.0295
  -4.000  -0.0550   0.00963   0.00401  -0.0748   0.7626   0.0296
  -3.750  -0.0271   0.00918   0.00346  -0.0748   0.7504   0.0301
  -3.500   0.0010   0.00882   0.00299  -0.0748   0.7357   0.0309
  -3.250   0.0292   0.00863   0.00274  -0.0747   0.7194   0.0316
  -3.000   0.0573   0.00855   0.00259  -0.0746   0.6992   0.0324
  -2.750   0.0855   0.00850   0.00244  -0.0746   0.6763   0.0331
  -2.500   0.1136   0.00844   0.00227  -0.0745   0.6517   0.0338
  -2.250   0.1417   0.00839   0.00212  -0.0744   0.6257   0.0345
  -2.000   0.1698   0.00837   0.00197  -0.0744   0.5989   0.0352
  -1.750   0.1979   0.00835   0.00185  -0.0743   0.5738   0.0359
  -1.500   0.2261   0.00834   0.00174  -0.0743   0.5492   0.0365
  -1.250   0.2542   0.00836   0.00165  -0.0743   0.5248   0.0370
  -1.000   0.2824   0.00837   0.00158  -0.0743   0.5033   0.0374
  -0.750   0.3107   0.00833   0.00145  -0.0743   0.4840   0.0386
  -0.500   0.3388   0.00834   0.00137  -0.0743   0.4603   0.0404
  -0.250   0.3669   0.00841   0.00135  -0.0743   0.4356   0.0420
   0.000   0.3950   0.00848   0.00134  -0.0743   0.4145   0.0436
   0.250   0.4231   0.00853   0.00133  -0.0743   0.3985   0.0455
   0.500   0.4514   0.00857   0.00133  -0.0742   0.3865   0.0468
   0.750   0.4796   0.00862   0.00133  -0.0742   0.3760   0.0476
   1.000   0.5078   0.00864   0.00131  -0.0742   0.3634   0.0507
   1.250   0.5359   0.00868   0.00133  -0.0742   0.3500   0.0541
   1.500   0.5641   0.00873   0.00135  -0.0742   0.3386   0.0572
   1.750   0.5920   0.00882   0.00139  -0.0742   0.3233   0.0602
   2.000   0.6198   0.00893   0.00146  -0.0742   0.3051   0.0726
   2.250   0.6476   0.00902   0.00155  -0.0742   0.2882   0.0959
   2.500   0.6754   0.00913   0.00163  -0.0742   0.2739   0.1073
   2.750   0.7032   0.00923   0.00171  -0.0741   0.2594   0.1251
   3.250   0.7535   0.00779   0.00210  -0.0736   0.2247   1.0000
   3.500   0.7805   0.00809   0.00226  -0.0735   0.1997   1.0000
   3.750   0.8072   0.00845   0.00246  -0.0734   0.1701   1.0000
   4.000   0.8338   0.00881   0.00268  -0.0732   0.1432   1.0000
   4.250   0.8607   0.00910   0.00288  -0.0731   0.1273   1.0000
   4.500   0.8878   0.00935   0.00308  -0.0730   0.1173   1.0000
   4.750   0.9151   0.00955   0.00325  -0.0729   0.1123   1.0000
   5.000   0.9419   0.00982   0.00346  -0.0727   0.1040   1.0000
   5.250   0.9690   0.01003   0.00366  -0.0726   0.0982   1.0000
   5.500   0.9958   0.01027   0.00387  -0.0725   0.0934   1.0000
   5.750   1.0227   0.01050   0.00408  -0.0723   0.0889   1.0000
   6.000   1.0497   0.01070   0.00428  -0.0722   0.0861   1.0000
   6.250   1.0761   0.01098   0.00453  -0.0720   0.0798   1.0000
   6.500   1.1026   0.01123   0.00476  -0.0718   0.0748   1.0000
   6.750   1.1265   0.01187   0.00520  -0.0714   0.0425   1.0000
   7.000   1.1504   0.01253   0.00579  -0.0709   0.0230   1.0000
   7.250   1.1759   0.01290   0.00617  -0.0706   0.0185   1.0000
   7.500   1.2009   0.01332   0.00659  -0.0702   0.0148   1.0000
   7.750   1.2262   0.01368   0.00697  -0.0699   0.0131   1.0000
   8.000   1.2511   0.01409   0.00739  -0.0695   0.0116   1.0000
   8.250   1.2754   0.01456   0.00788  -0.0690   0.0101   1.0000
   8.500   1.3000   0.01494   0.00831  -0.0686   0.0095   1.0000
   8.750   1.3244   0.01536   0.00875  -0.0682   0.0088   1.0000
   9.000   1.3482   0.01582   0.00923  -0.0677   0.0080   1.0000
   9.250   1.3712   0.01637   0.00981  -0.0671   0.0072   1.0000
   9.500   1.3943   0.01687   0.01036  -0.0665   0.0068   1.0000
   9.750   1.4173   0.01737   0.01092  -0.0659   0.0065   1.0000
  10.000   1.4397   0.01790   0.01150  -0.0653   0.0061   1.0000
  10.250   1.4616   0.01846   0.01210  -0.0646   0.0058   1.0000
  10.500   1.4829   0.01907   0.01275  -0.0638   0.0055   1.0000
  10.750   1.5030   0.01977   0.01350  -0.0629   0.0052   1.0000
  11.000   1.5215   0.02061   0.01443  -0.0617   0.0049   1.0000
  11.250   1.5412   0.02126   0.01514  -0.0607   0.0047   1.0000
  11.500   1.5599   0.02195   0.01590  -0.0597   0.0046   1.0000
  11.750   1.5775   0.02269   0.01671  -0.0585   0.0044   1.0000
  12.000   1.5940   0.02348   0.01757  -0.0572   0.0042   1.0000
  12.250   1.6090   0.02433   0.01849  -0.0557   0.0040   1.0000
  12.500   1.6221   0.02522   0.01946  -0.0539   0.0039   1.0000
  12.750   1.6309   0.02616   0.02049  -0.0515   0.0038   1.0000
  13.000   1.6379   0.02725   0.02165  -0.0491   0.0037   1.0000
  13.250   1.6432   0.02854   0.02303  -0.0468   0.0036   1.0000
  13.500   1.6463   0.03012   0.02470  -0.0447   0.0035   1.0000
  13.750   1.6466   0.03209   0.02678  -0.0429   0.0034   1.0000
  14.000   1.6431   0.03464   0.02947  -0.0414   0.0033   1.0000
  14.250   1.6430   0.03712   0.03206  -0.0406   0.0033   1.0000
  14.500   1.6422   0.03986   0.03492  -0.0403   0.0032   1.0000
  14.750   1.6396   0.04303   0.03822  -0.0403   0.0032   1.0000
  15.000   1.6347   0.04670   0.04202  -0.0408   0.0032   1.0000
  15.250   1.6271   0.05103   0.04648  -0.0419   0.0031   1.0000
  15.500   1.6167   0.05600   0.05159  -0.0435   0.0031   1.0000
  15.750   1.6039   0.06158   0.05732  -0.0456   0.0031   1.0000
  16.000   1.5878   0.06782   0.06371  -0.0480   0.0031   1.0000
  16.250   1.5685   0.07469   0.07072  -0.0507   0.0031   1.0000
  16.500   1.5477   0.08187   0.07805  -0.0536   0.0031   1.0000
  16.750   1.5237   0.08970   0.08602  -0.0567   0.0031   1.0000
  17.000   1.5008   0.09750   0.09394  -0.0599   0.0031   1.0000
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