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GOE 143 (MVA H.20) AIRFOIL (goe143-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 143 (MVA H.20) AIRFOIL (goe143-il)
Reynolds number: 100,000
Max Cl/Cd: 55.39 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe143-il-100000-n5.txt
Download as CSV file: xf-goe143-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4260   0.11780   0.11276  -0.0057   1.0000   0.0466
  -9.250  -0.4255   0.11540   0.11041  -0.0092   1.0000   0.0471
  -9.000  -0.4232   0.11241   0.10748  -0.0121   1.0000   0.0473
  -8.750  -0.4201   0.10914   0.10425  -0.0146   1.0000   0.0474
  -8.500  -0.4166   0.10572   0.10087  -0.0171   1.0000   0.0475
  -8.250  -0.4116   0.10204   0.09724  -0.0199   1.0000   0.0475
  -8.000  -0.4038   0.09803   0.09325  -0.0238   1.0000   0.0476
  -7.750  -0.3904   0.09300   0.08821  -0.0151   1.0000   0.0505
  -7.500  -0.3837   0.09016   0.08540  -0.0156   1.0000   0.0529
  -7.250  -0.3771   0.08695   0.08223  -0.0181   1.0000   0.0550
  -7.000  -0.3689   0.08349   0.07881  -0.0226   1.0000   0.0576
  -6.750  -0.3538   0.07947   0.07475  -0.0344   1.0000   0.0598
  -6.500  -0.3395   0.07518   0.07039  -0.0397   1.0000   0.0601
  -6.250  -0.3241   0.07090   0.06598  -0.0443   1.0000   0.0603
  -6.000  -0.3264   0.06785   0.06319  -0.0368   1.0000   0.0627
  -5.750  -0.3163   0.06511   0.06047  -0.0366   1.0000   0.0647
  -5.500  -0.2976   0.05992   0.05511  -0.0416   1.0000   0.0580
  -5.250  -0.2845   0.05622   0.05135  -0.0428   1.0000   0.0563
  -5.000  -0.2637   0.05207   0.04698  -0.0464   1.0000   0.0584
  -4.750  -0.2479   0.04861   0.04340  -0.0473   1.0000   0.0576
  -4.500  -0.2223   0.04465   0.03923  -0.0501   0.9980   0.0564
  -4.250  -0.1746   0.03969   0.03375  -0.0571   0.9909   0.0584
  -4.000  -0.1302   0.03555   0.02913  -0.0623   0.9838   0.0587
  -3.750  -0.0886   0.03210   0.02523  -0.0664   0.9763   0.0586
  -3.500  -0.0487   0.02931   0.02196  -0.0695   0.9686   0.0592
  -3.250  -0.0084   0.02702   0.01933  -0.0729   0.9625   0.0620
  -3.000   0.0270   0.02526   0.01729  -0.0748   0.9527   0.0628
  -2.750   0.0633   0.02355   0.01525  -0.0765   0.9432   0.0631
  -2.500   0.1002   0.02211   0.01354  -0.0783   0.9339   0.0639
  -2.250   0.1332   0.02096   0.01214  -0.0792   0.9213   0.0649
  -2.000   0.1659   0.01994   0.01093  -0.0799   0.9082   0.0662
  -1.750   0.1981   0.01918   0.00999  -0.0804   0.8944   0.0695
  -1.500   0.2298   0.01847   0.00907  -0.0806   0.8799   0.0726
  -1.250   0.2605   0.01774   0.00819  -0.0807   0.8647   0.0739
  -1.000   0.2897   0.01699   0.00743  -0.0805   0.8488   0.0758
  -0.750   0.3183   0.01645   0.00687  -0.0802   0.8321   0.0781
  -0.500   0.3460   0.01601   0.00638  -0.0797   0.8143   0.0811
  -0.250   0.3731   0.01572   0.00601  -0.0790   0.7951   0.0861
   0.000   0.3996   0.01538   0.00570  -0.0784   0.7750   0.0921
   0.250   0.4263   0.01514   0.00537  -0.0777   0.7543   0.0978
   0.500   0.4526   0.01490   0.00508  -0.0770   0.7312   0.1039
   0.750   0.4792   0.01474   0.00483  -0.0763   0.7076   0.1143
   1.000   0.5063   0.01451   0.00460  -0.0758   0.6827   0.1381
   1.250   0.5297   0.01237   0.00450  -0.0745   0.6587   1.0000
   1.500   0.5562   0.01256   0.00440  -0.0738   0.6340   1.0000
   1.750   0.5828   0.01277   0.00438  -0.0732   0.6096   1.0000
   2.000   0.6092   0.01301   0.00441  -0.0726   0.5871   1.0000
   2.250   0.6357   0.01327   0.00451  -0.0722   0.5659   1.0000
   2.500   0.6621   0.01356   0.00462  -0.0717   0.5462   1.0000
   2.750   0.6883   0.01385   0.00477  -0.0712   0.5257   1.0000
   3.000   0.7143   0.01416   0.00494  -0.0707   0.5043   1.0000
   3.250   0.7400   0.01449   0.00511  -0.0702   0.4826   1.0000
   3.500   0.7657   0.01481   0.00531  -0.0697   0.4598   1.0000
   4.000   0.8169   0.01548   0.00578  -0.0688   0.4195   1.0000
   4.250   0.8428   0.01581   0.00607  -0.0684   0.4037   1.0000
   4.500   0.8687   0.01614   0.00640  -0.0680   0.3879   1.0000
   4.750   0.8944   0.01647   0.00672  -0.0676   0.3718   1.0000
   5.000   0.9199   0.01682   0.00707  -0.0672   0.3554   1.0000
   5.250   0.9453   0.01718   0.00744  -0.0668   0.3388   1.0000
   5.500   0.9704   0.01756   0.00785  -0.0663   0.3210   1.0000
   5.750   0.9952   0.01797   0.00827  -0.0658   0.3016   1.0000
   6.000   1.0197   0.01841   0.00873  -0.0653   0.2792   1.0000
   6.250   1.0436   0.01893   0.00923  -0.0647   0.2552   1.0000
   6.500   1.0667   0.01955   0.00982  -0.0641   0.2312   1.0000
   6.750   1.0896   0.02022   0.01047  -0.0635   0.2109   1.0000
   7.000   1.1121   0.02095   0.01119  -0.0628   0.1959   1.0000
   7.250   1.1341   0.02171   0.01193  -0.0620   0.1821   1.0000
   7.500   1.1556   0.02248   0.01272  -0.0613   0.1673   1.0000
   7.750   1.1767   0.02327   0.01349  -0.0606   0.1522   1.0000
   8.000   1.1976   0.02405   0.01429  -0.0599   0.1391   1.0000
   8.250   1.2182   0.02485   0.01513  -0.0591   0.1289   1.0000
   8.500   1.2387   0.02564   0.01600  -0.0583   0.1172   1.0000
   8.750   1.2591   0.02643   0.01690  -0.0575   0.1017   1.0000
   9.000   1.2800   0.02721   0.01777  -0.0567   0.0775   1.0000
   9.500   1.3006   0.03103   0.02125  -0.0531   0.0332   1.0000
   9.750   1.3099   0.03289   0.02328  -0.0512   0.0306   1.0000
  10.000   1.3150   0.03498   0.02554  -0.0489   0.0284   1.0000
  10.250   1.3226   0.03666   0.02746  -0.0469   0.0269   1.0000
  10.500   1.3249   0.03850   0.02951  -0.0444   0.0256   1.0000
  10.750   1.3244   0.04061   0.03187  -0.0421   0.0247   1.0000
  11.000   1.3222   0.04304   0.03449  -0.0403   0.0240   1.0000
  11.250   1.3184   0.04581   0.03745  -0.0389   0.0234   1.0000
  11.500   1.3133   0.04895   0.04076  -0.0382   0.0230   1.0000
  11.750   1.3072   0.05247   0.04445  -0.0380   0.0225   1.0000
  12.000   1.3001   0.05634   0.04847  -0.0383   0.0220   1.0000
  12.250   1.2922   0.06052   0.05279  -0.0389   0.0216   1.0000
  12.500   1.2842   0.06487   0.05726  -0.0397   0.0211   1.0000
  12.750   1.2764   0.06916   0.06163  -0.0400   0.0206   1.0000
  13.000   1.2723   0.07328   0.06591  -0.0411   0.0202   1.0000
  13.250   1.2676   0.07763   0.07044  -0.0424   0.0199   1.0000
  13.500   1.2621   0.08217   0.07517  -0.0438   0.0195   1.0000
  13.750   1.2564   0.08680   0.07997  -0.0453   0.0192   1.0000
  14.000   1.2502   0.09154   0.08488  -0.0468   0.0190   1.0000
  14.250   1.2435   0.09651   0.09001  -0.0485   0.0189   1.0000
  14.500   1.2361   0.10177   0.09544  -0.0506   0.0187   1.0000
  14.750   1.2278   0.10737   0.10122  -0.0530   0.0186   1.0000
  15.000   1.2184   0.11336   0.10739  -0.0558   0.0185   1.0000
  15.250   1.2085   0.11972   0.11392  -0.0590   0.0185   1.0000
  15.500   1.1976   0.12654   0.12091  -0.0627   0.0185   1.0000
  15.750   1.1858   0.13386   0.12839  -0.0668   0.0185   1.0000
  16.000   1.1733   0.14171   0.13641  -0.0715   0.0185   1.0000
  16.250   1.1602   0.15019   0.14504  -0.0766   0.0186   1.0000
  16.500   1.1461   0.15947   0.15445  -0.0824   0.0188   1.0000
  16.750   1.1313   0.16960   0.16471  -0.0886   0.0190   1.0000
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