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GOE 124 (MVA H.4) AIRFOIL (goe124-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 124 (MVA H.4) AIRFOIL (goe124-il)
Reynolds number: 500,000
Max Cl/Cd: 107.21 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe124-il-500000-n5.txt
Download as CSV file: xf-goe124-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2852   0.09012   0.08769  -0.0278   0.8806   0.0144
  -7.750  -0.2785   0.08708   0.08459  -0.0295   0.8636   0.0147
  -7.500  -0.2715   0.08400   0.08145  -0.0315   0.8482   0.0150
  -7.250  -0.2598   0.07765   0.07503  -0.0401   0.8340   0.0161
  -7.000  -0.2452   0.07588   0.07321  -0.0409   0.8212   0.0165
  -6.750  -0.2284   0.07383   0.07110  -0.0431   0.8084   0.0170
  -6.500  -0.2098   0.07078   0.06800  -0.0470   0.7962   0.0177
  -6.250  -0.1889   0.06699   0.06413  -0.0522   0.7852   0.0180
  -6.000  -0.1656   0.06301   0.06006  -0.0578   0.7746   0.0184
  -5.750  -0.1316   0.05672   0.05363  -0.0682   0.7644   0.0201
  -5.500  -0.1122   0.05562   0.05249  -0.0687   0.7543   0.0209
  -5.000  -0.0548   0.04898   0.04564  -0.0778   0.7356   0.0222
  -4.750  -0.0223   0.04500   0.04150  -0.0831   0.7263   0.0223
  -4.500   0.0125   0.04101   0.03732  -0.0882   0.7163   0.0230
  -4.250   0.0515   0.03622   0.03227  -0.0938   0.7069   0.0237
  -4.000   0.0869   0.03214   0.02791  -0.0977   0.6976   0.0238
  -3.750   0.1255   0.02691   0.02226  -0.1017   0.6889   0.0248
  -3.500   0.1518   0.02620   0.02148  -0.1026   0.6796   0.0253
  -3.250   0.1797   0.02524   0.02042  -0.1035   0.6698   0.0261
  -3.000   0.2155   0.02159   0.01632  -0.1057   0.6608   0.0257
  -2.750   0.2468   0.01978   0.01422  -0.1068   0.6510   0.0259
  -2.500   0.2780   0.01817   0.01235  -0.1077   0.6424   0.0260
  -2.250   0.3089   0.01682   0.01072  -0.1085   0.6355   0.0262
  -2.000   0.3389   0.01595   0.00968  -0.1090   0.6284   0.0267
  -1.750   0.3691   0.01505   0.00856  -0.1095   0.6211   0.0271
  -1.500   0.3996   0.01404   0.00734  -0.1100   0.6139   0.0270
  -1.250   0.4295   0.01328   0.00638  -0.1103   0.6067   0.0272
  -1.000   0.4591   0.01267   0.00563  -0.1106   0.6003   0.0276
  -0.750   0.4885   0.01218   0.00502  -0.1109   0.5932   0.0280
  -0.500   0.5176   0.01178   0.00452  -0.1111   0.5867   0.0285
  -0.250   0.5467   0.01143   0.00411  -0.1112   0.5790   0.0289
   0.000   0.5756   0.01116   0.00376  -0.1114   0.5715   0.0292
   0.250   0.6045   0.01099   0.00354  -0.1115   0.5627   0.0299
   0.500   0.6331   0.01088   0.00340  -0.1117   0.5546   0.0304
   0.750   0.6620   0.01069   0.00318  -0.1118   0.5458   0.0306
   1.000   0.6911   0.01037   0.00284  -0.1121   0.5374   0.0310
   1.250   0.7201   0.01019   0.00264  -0.1124   0.5281   0.0318
   1.500   0.7489   0.01010   0.00254  -0.1126   0.5165   0.0326
   1.750   0.7773   0.01009   0.00248  -0.1127   0.5021   0.0336
   2.000   0.8057   0.01011   0.00247  -0.1128   0.4875   0.0347
   2.250   0.8339   0.01015   0.00247  -0.1129   0.4736   0.0358
   2.500   0.8619   0.01025   0.00250  -0.1130   0.4573   0.0376
   2.750   0.8895   0.01040   0.00257  -0.1130   0.4366   0.0393
   3.000   0.9172   0.01054   0.00262  -0.1130   0.4164   0.0425
   3.250   0.9448   0.01070   0.00272  -0.1131   0.3993   0.0489
   3.750   0.9939   0.00944   0.00319  -0.1123   0.3751   1.0000
   4.000   1.0212   0.00967   0.00334  -0.1122   0.3630   1.0000
   4.250   1.0486   0.00989   0.00351  -0.1122   0.3534   1.0000
   4.750   1.1030   0.01033   0.00389  -0.1122   0.3361   1.0000
   5.000   1.1299   0.01059   0.00411  -0.1121   0.3269   1.0000
   5.250   1.1569   0.01081   0.00432  -0.1120   0.3189   1.0000
   5.500   1.1837   0.01106   0.00455  -0.1119   0.3117   1.0000
   5.750   1.2104   0.01129   0.00478  -0.1119   0.3026   1.0000
   6.000   1.2368   0.01156   0.00504  -0.1117   0.2919   1.0000
   6.250   1.2630   0.01185   0.00530  -0.1116   0.2810   1.0000
   6.500   1.2888   0.01216   0.00558  -0.1114   0.2660   1.0000
   6.750   1.3123   0.01275   0.00597  -0.1110   0.2234   1.0000
   7.250   1.3517   0.01484   0.00745  -0.1092   0.1254   1.0000
   7.500   1.3752   0.01533   0.00793  -0.1087   0.1158   1.0000
   7.750   1.3987   0.01580   0.00841  -0.1082   0.1079   1.0000
   8.000   1.4211   0.01637   0.00894  -0.1076   0.0981   1.0000
   8.250   1.4446   0.01678   0.00938  -0.1071   0.0917   1.0000
   8.500   1.4667   0.01732   0.00990  -0.1064   0.0836   1.0000
   8.750   1.4880   0.01790   0.01045  -0.1057   0.0724   1.0000
   9.000   1.5072   0.01865   0.01111  -0.1046   0.0563   1.0000
   9.250   1.5240   0.01956   0.01193  -0.1033   0.0409   1.0000
   9.500   1.5371   0.02074   0.01298  -0.1015   0.0231   1.0000
   9.750   1.5513   0.02172   0.01396  -0.0997   0.0177   1.0000
  10.000   1.5663   0.02256   0.01486  -0.0980   0.0154   1.0000
  10.250   1.5790   0.02344   0.01580  -0.0961   0.0140   1.0000
  10.500   1.5871   0.02444   0.01687  -0.0934   0.0129   1.0000
  10.750   1.5963   0.02545   0.01796  -0.0910   0.0123   1.0000
  11.000   1.6057   0.02653   0.01914  -0.0890   0.0117   1.0000
  11.250   1.6141   0.02777   0.02049  -0.0871   0.0112   1.0000
  11.500   1.6214   0.02918   0.02199  -0.0853   0.0107   1.0000
  11.750   1.6274   0.03080   0.02370  -0.0836   0.0102   1.0000
  12.000   1.6313   0.03271   0.02569  -0.0821   0.0097   1.0000
  12.250   1.6331   0.03492   0.02801  -0.0806   0.0093   1.0000
  12.500   1.6387   0.03685   0.03004  -0.0796   0.0090   1.0000
  12.750   1.6429   0.03900   0.03230  -0.0786   0.0087   1.0000
  13.000   1.6453   0.04140   0.03482  -0.0778   0.0085   1.0000
  13.250   1.6465   0.04402   0.03755  -0.0771   0.0083   1.0000
  13.500   1.6467   0.04682   0.04046  -0.0765   0.0080   1.0000
  13.750   1.6456   0.04982   0.04358  -0.0760   0.0078   1.0000
  14.000   1.6435   0.05301   0.04687  -0.0757   0.0077   1.0000
  14.250   1.6401   0.05644   0.05041  -0.0755   0.0075   1.0000
  14.500   1.6348   0.06014   0.05422  -0.0754   0.0073   1.0000
  14.750   1.6282   0.06415   0.05835  -0.0756   0.0072   1.0000
  15.000   1.6201   0.06853   0.06284  -0.0760   0.0071   1.0000
  15.250   1.6102   0.07325   0.06769  -0.0766   0.0070   1.0000
  15.500   1.5991   0.07830   0.07286  -0.0774   0.0069   1.0000
  15.750   1.5905   0.08310   0.07778  -0.0783   0.0068   1.0000
  16.000   1.5830   0.08783   0.08264  -0.0793   0.0067   1.0000
  16.250   1.5749   0.09270   0.08764  -0.0804   0.0067   1.0000
  16.500   1.5667   0.09770   0.09276  -0.0817   0.0066   1.0000
  16.750   1.5586   0.10276   0.09795  -0.0831   0.0065   1.0000
  17.000   1.5500   0.10796   0.10327  -0.0847   0.0064   1.0000
  17.250   1.5416   0.11316   0.10859  -0.0864   0.0063   1.0000
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