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GOE 124 (MVA H.4) AIRFOIL (goe124-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 124 (MVA H.4) AIRFOIL (goe124-il)
Reynolds number: 200,000
Max Cl/Cd: 84.37 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe124-il-200000.txt
Download as CSV file: xf-goe124-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 124 (MVA H.4) AIRFOIL                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2817   0.09363   0.09030  -0.0268   1.0000   0.0346
  -7.500  -0.2824   0.09182   0.08857  -0.0279   1.0000   0.0358
  -7.250  -0.2982   0.09162   0.08850  -0.0264   1.0000   0.0362
  -7.000  -0.2665   0.08824   0.08508  -0.0444   0.9909   0.0367
  -6.750  -0.2452   0.08224   0.07908  -0.0474   0.9861   0.0372
  -6.500  -0.2242   0.07788   0.07472  -0.0476   0.9831   0.0379
  -6.250  -0.1966   0.07389   0.07071  -0.0521   0.9754   0.0390
  -6.000  -0.1626   0.06967   0.06645  -0.0595   0.9685   0.0407
  -5.750  -0.0979   0.06496   0.06149  -0.0801   0.9565   0.0449
  -5.500  -0.0663   0.05956   0.05598  -0.0871   0.9449   0.0456
  -5.250  -0.0519   0.05623   0.05268  -0.0861   0.9339   0.0464
  -5.000  -0.0324   0.05352   0.04995  -0.0868   0.9224   0.0475
  -4.750  -0.0095   0.05086   0.04720  -0.0887   0.9100   0.0492
  -4.500   0.0183   0.04800   0.04421  -0.0919   0.8971   0.0519
  -4.250   0.0659   0.04358   0.03936  -0.1007   0.8857   0.0564
  -4.000   0.0832   0.04118   0.03696  -0.1002   0.8752   0.0576
  -3.750   0.1059   0.03911   0.03482  -0.1008   0.8643   0.0596
  -3.500   0.1347   0.03691   0.03246  -0.1026   0.8535   0.0632
  -3.250   0.1742   0.03378   0.02884  -0.1065   0.8444   0.0695
  -3.000   0.1966   0.03189   0.02696  -0.1066   0.8333   0.0717
  -2.750   0.2244   0.03034   0.02526  -0.1073   0.8218   0.0774
  -2.500   0.2553   0.02823   0.02285  -0.1087   0.8113   0.0857
  -2.000   0.3124   0.02525   0.01952  -0.1101   0.7891   0.1023
  -1.750   0.3421   0.02399   0.01804  -0.1108   0.7799   0.1161
  -1.500   0.3705   0.02288   0.01680  -0.1114   0.7710   0.1318
  -1.250   0.3982   0.02192   0.01578  -0.1119   0.7618   0.1504
  -1.000   0.4254   0.02107   0.01485  -0.1122   0.7536   0.1799
   0.000   0.5607   0.01590   0.00798  -0.1120   0.7212   0.0766
   0.250   0.5905   0.01525   0.00712  -0.1118   0.7117   0.0706
   0.500   0.6191   0.01499   0.00673  -0.1115   0.7033   0.0688
   0.750   0.6476   0.01450   0.00621  -0.1113   0.6943   0.0691
   1.000   0.6760   0.01401   0.00577  -0.1114   0.6856   0.0718
   1.250   0.7044   0.01372   0.00546  -0.1112   0.6770   0.0726
   1.500   0.7330   0.01350   0.00528  -0.1113   0.6674   0.0739
   1.750   0.7615   0.01336   0.00509  -0.1112   0.6588   0.0766
   2.000   0.7899   0.01328   0.00499  -0.1111   0.6482   0.0808
   2.250   0.8183   0.01319   0.00490  -0.1111   0.6378   0.0940
   2.500   0.8376   0.01145   0.00492  -0.1091   0.6291   1.0000
   2.750   0.8655   0.01158   0.00493  -0.1089   0.6175   1.0000
   3.000   0.8932   0.01173   0.00498  -0.1087   0.6059   1.0000
   3.250   0.9206   0.01187   0.00502  -0.1085   0.5934   1.0000
   3.500   0.9478   0.01202   0.00507  -0.1082   0.5799   1.0000
   3.750   0.9748   0.01217   0.00515  -0.1079   0.5655   1.0000
   4.000   1.0018   0.01233   0.00525  -0.1077   0.5507   1.0000
   4.250   1.0286   0.01252   0.00538  -0.1074   0.5355   1.0000
   4.500   1.0553   0.01272   0.00555  -0.1071   0.5197   1.0000
   4.750   1.0818   0.01295   0.00573  -0.1069   0.5048   1.0000
   5.000   1.1084   0.01322   0.00595  -0.1067   0.4913   1.0000
   5.250   1.1348   0.01349   0.00621  -0.1064   0.4775   1.0000
   5.500   1.1610   0.01378   0.00649  -0.1062   0.4636   1.0000
   5.750   1.1871   0.01407   0.00678  -0.1059   0.4507   1.0000
   6.000   1.2130   0.01439   0.00710  -0.1056   0.4386   1.0000
   6.250   1.2387   0.01473   0.00744  -0.1053   0.4275   1.0000
   6.750   1.2891   0.01540   0.00813  -0.1045   0.4023   1.0000
   7.000   1.3141   0.01574   0.00852  -0.1041   0.3897   1.0000
   7.250   1.3387   0.01611   0.00895  -0.1037   0.3771   1.0000
   7.500   1.3626   0.01649   0.00938  -0.1031   0.3625   1.0000
   7.750   1.3852   0.01692   0.00980  -0.1024   0.3436   1.0000
   8.000   1.4070   0.01739   0.01028  -0.1016   0.3208   1.0000
   8.250   1.4275   0.01793   0.01083  -0.1006   0.2905   1.0000
   8.500   1.4456   0.01868   0.01144  -0.0994   0.2395   1.0000
   8.750   1.4564   0.02018   0.01249  -0.0974   0.1781   1.0000
   9.000   1.4679   0.02161   0.01374  -0.0955   0.1542   1.0000
   9.250   1.4805   0.02285   0.01495  -0.0937   0.1402   1.0000
   9.500   1.4939   0.02395   0.01607  -0.0919   0.1285   1.0000
   9.750   1.5064   0.02503   0.01721  -0.0901   0.1179   1.0000
  10.000   1.5166   0.02617   0.01840  -0.0879   0.1067   1.0000
  10.250   1.5248   0.02727   0.01954  -0.0855   0.0917   1.0000
  10.500   1.5283   0.02882   0.02099  -0.0828   0.0676   1.0000
  10.750   1.5241   0.03112   0.02316  -0.0797   0.0527   1.0000
  11.000   1.5222   0.03344   0.02554  -0.0773   0.0458   1.0000
  11.500   1.5173   0.03868   0.03093  -0.0736   0.0394   1.0000
  11.750   1.5170   0.04129   0.03364  -0.0723   0.0372   1.0000
  12.000   1.5132   0.04435   0.03676  -0.0712   0.0354   1.0000
  12.250   1.5069   0.04776   0.04023  -0.0700   0.0340   1.0000
  12.500   1.5083   0.05043   0.04306  -0.0691   0.0326   1.0000
  12.750   1.5079   0.05332   0.04608  -0.0683   0.0314   1.0000
  13.000   1.5071   0.05629   0.04915  -0.0675   0.0304   1.0000
  13.250   1.5060   0.05928   0.05221  -0.0668   0.0296   1.0000
  13.500   1.5048   0.06228   0.05527  -0.0659   0.0288   1.0000
  13.750   1.5047   0.06508   0.05811  -0.0646   0.0280   1.0000
  14.000   1.5074   0.06763   0.06074  -0.0629   0.0274   1.0000
  14.250   1.5089   0.07052   0.06381  -0.0622   0.0269   1.0000
  14.500   1.5096   0.07358   0.06704  -0.0617   0.0263   1.0000
  14.750   1.5093   0.07680   0.07045  -0.0614   0.0256   1.0000
  15.000   1.5083   0.08017   0.07397  -0.0613   0.0250   1.0000
  15.250   1.5061   0.08376   0.07772  -0.0614   0.0244   1.0000
  15.500   1.5038   0.08746   0.08159  -0.0615   0.0241   1.0000
  15.750   1.4999   0.09145   0.08575  -0.0618   0.0238   1.0000
  16.000   1.4947   0.09572   0.09019  -0.0625   0.0235   1.0000
  16.250   1.4881   0.10033   0.09498  -0.0634   0.0233   1.0000
  16.500   1.4799   0.10532   0.10016  -0.0648   0.0232   1.0000
  16.750   1.4697   0.11080   0.10584  -0.0668   0.0231   1.0000
  17.000   1.4571   0.11691   0.11217  -0.0693   0.0230   1.0000
  17.250   1.4419   0.12381   0.11931  -0.0728   0.0231   1.0000
  17.500   1.4239   0.13165   0.12741  -0.0772   0.0232   1.0000
  17.750   1.4025   0.14079   0.13682  -0.0829   0.0234   1.0000
  18.000   1.3708   0.15322   0.14959  -0.0915   0.0239   1.0000
  18.250   1.3187   0.17304   0.16978  -0.1060   0.0249   1.0000
  18.500   1.2334   0.21228   0.20916  -0.1314   0.0283   1.0000
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