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GOE 121 (MVA H.1) AIRFOIL (goe121-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 121 (MVA H.1) AIRFOIL (goe121-il)
Reynolds number: 500,000
Max Cl/Cd: 86.98 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe121-il-500000-n5.txt
Download as CSV file: xf-goe121-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 121 (MVA H.1) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3818   0.08839   0.08612  -0.0234   1.0000   0.0149
  -8.000  -0.3873   0.08507   0.08285  -0.0236   1.0000   0.0154
  -7.750  -0.4033   0.07743   0.07526  -0.0281   1.0000   0.0167
  -7.250  -0.3598   0.07268   0.07050  -0.0361   0.9944   0.0175
  -7.000  -0.3341   0.06984   0.06764  -0.0411   0.9880   0.0182
  -6.750  -0.3076   0.06544   0.06320  -0.0483   0.9784   0.0191
  -6.500  -0.2761   0.05880   0.05648  -0.0590   0.9669   0.0204
  -6.250  -0.2319   0.04635   0.04380  -0.0774   0.9537   0.0228
  -6.000  -0.1960   0.04259   0.03992  -0.0838   0.9450   0.0235
  -5.750  -0.1592   0.03984   0.03706  -0.0889   0.9359   0.0242
  -5.500  -0.1230   0.03690   0.03397  -0.0937   0.9236   0.0252
  -5.250  -0.0776   0.01770   0.01336  -0.1086   0.9133   0.0269
  -5.000  -0.0483   0.01617   0.01150  -0.1094   0.9008   0.0276
  -4.750  -0.0201   0.01485   0.00985  -0.1099   0.8900   0.0281
  -4.500   0.0075   0.01384   0.00858  -0.1100   0.8787   0.0285
  -4.250   0.0349   0.01306   0.00758  -0.1099   0.8660   0.0289
  -4.000   0.0622   0.01244   0.00676  -0.1098   0.8518   0.0293
  -3.750   0.0894   0.01192   0.00605  -0.1095   0.8348   0.0296
  -3.500   0.1163   0.01149   0.00544  -0.1092   0.8128   0.0299
  -3.250   0.1428   0.01114   0.00489  -0.1088   0.7858   0.0301
  -3.000   0.1695   0.01085   0.00439  -0.1084   0.7626   0.0303
  -2.500   0.2241   0.01033   0.00359  -0.1079   0.7326   0.0305
  -2.250   0.2517   0.01008   0.00325  -0.1077   0.7217   0.0307
  -2.000   0.2794   0.00968   0.00275  -0.1076   0.7110   0.0316
  -1.750   0.3070   0.00946   0.00244  -0.1074   0.6986   0.0321
  -1.500   0.3346   0.00930   0.00219  -0.1072   0.6819   0.0325
  -1.250   0.3620   0.00918   0.00199  -0.1070   0.6608   0.0331
  -1.000   0.3888   0.00916   0.00181  -0.1066   0.6225   0.0340
  -0.750   0.4134   0.00938   0.00167  -0.1059   0.5490   0.0352
  -0.500   0.4396   0.00951   0.00162  -0.1055   0.5124   0.0369
  -0.250   0.4664   0.00960   0.00159  -0.1052   0.4870   0.0391
   0.250   0.5207   0.00965   0.00162  -0.1049   0.4443   0.0761
   0.500   0.5477   0.00979   0.00168  -0.1046   0.4209   0.0887
   0.750   0.5745   0.00995   0.00175  -0.1044   0.3948   0.0958
   1.000   0.6013   0.01012   0.00181  -0.1041   0.3708   0.0998
   1.250   0.6281   0.01026   0.00188  -0.1039   0.3527   0.1041
   1.500   0.6551   0.01037   0.00196  -0.1037   0.3377   0.1096
   1.750   0.6821   0.01048   0.00203  -0.1035   0.3247   0.1134
   2.000   0.7091   0.01060   0.00211  -0.1033   0.3114   0.1182
   2.250   0.7362   0.01069   0.00219  -0.1031   0.3012   0.1227
   2.500   0.7632   0.01080   0.00229  -0.1029   0.2912   0.1254
   2.750   0.7902   0.01091   0.00239  -0.1027   0.2804   0.1288
   3.000   0.8171   0.01103   0.00251  -0.1025   0.2680   0.1366
   3.250   0.8439   0.01109   0.00270  -0.1024   0.2518   0.2049
   3.500   0.8703   0.01124   0.00290  -0.1022   0.2276   0.2730
   3.750   0.8949   0.01162   0.00318  -0.1019   0.1846   0.3309
   4.000   0.9156   0.01060   0.00344  -0.1005   0.1764   1.0000
   4.250   0.9420   0.01083   0.00365  -0.1002   0.1702   1.0000
   4.500   0.9676   0.01118   0.00391  -0.0998   0.1567   1.0000
   4.750   0.9933   0.01148   0.00418  -0.0994   0.1458   1.0000
   5.000   1.0191   0.01178   0.00442  -0.0991   0.1331   1.0000
   5.250   1.0424   0.01242   0.00481  -0.0984   0.0863   1.0000
   5.500   1.0672   0.01284   0.00519  -0.0979   0.0784   1.0000
   5.750   1.0927   0.01314   0.00553  -0.0975   0.0721   1.0000
   6.000   1.1177   0.01351   0.00591  -0.0970   0.0629   1.0000
   6.250   1.1398   0.01429   0.00648  -0.0962   0.0269   1.0000
   6.500   1.1639   0.01476   0.00697  -0.0956   0.0217   1.0000
   6.750   1.1878   0.01525   0.00751  -0.0949   0.0184   1.0000
   7.000   1.2119   0.01568   0.00799  -0.0943   0.0167   1.0000
   7.250   1.2354   0.01618   0.00851  -0.0936   0.0149   1.0000
   7.500   1.2574   0.01686   0.00924  -0.0927   0.0130   1.0000
   7.750   1.2802   0.01739   0.00984  -0.0919   0.0123   1.0000
   8.000   1.3026   0.01797   0.01049  -0.0910   0.0115   1.0000
   8.250   1.3242   0.01859   0.01118  -0.0901   0.0108   1.0000
   8.500   1.3454   0.01923   0.01187  -0.0891   0.0101   1.0000
   8.750   1.3654   0.01996   0.01265  -0.0880   0.0094   1.0000
   9.000   1.3826   0.02098   0.01374  -0.0865   0.0088   1.0000
   9.250   1.4018   0.02170   0.01455  -0.0853   0.0084   1.0000
   9.500   1.4193   0.02256   0.01552  -0.0838   0.0081   1.0000
   9.750   1.4356   0.02347   0.01653  -0.0822   0.0077   1.0000
  10.000   1.4508   0.02442   0.01756  -0.0804   0.0074   1.0000
  10.250   1.4648   0.02540   0.01863  -0.0786   0.0072   1.0000
  10.500   1.4772   0.02642   0.01973  -0.0765   0.0069   1.0000
  10.750   1.4860   0.02746   0.02085  -0.0739   0.0067   1.0000
  11.000   1.4928   0.02865   0.02213  -0.0712   0.0065   1.0000
  11.250   1.4960   0.03015   0.02372  -0.0682   0.0063   1.0000
  11.500   1.4943   0.03216   0.02587  -0.0652   0.0061   1.0000
  11.750   1.4999   0.03370   0.02753  -0.0632   0.0060   1.0000
  12.000   1.5042   0.03544   0.02940  -0.0613   0.0059   1.0000
  12.250   1.5071   0.03742   0.03152  -0.0596   0.0057   1.0000
  12.500   1.5086   0.03963   0.03387  -0.0582   0.0056   1.0000
  12.750   1.5090   0.04210   0.03648  -0.0570   0.0054   1.0000
  13.000   1.5079   0.04487   0.03939  -0.0560   0.0053   1.0000
  13.250   1.5057   0.04792   0.04259  -0.0554   0.0052   1.0000
  13.500   1.5024   0.05122   0.04603  -0.0551   0.0051   1.0000
  13.750   1.4984   0.05475   0.04971  -0.0551   0.0051   1.0000
  14.000   1.4932   0.05857   0.05367  -0.0553   0.0050   1.0000
  14.250   1.4869   0.06269   0.05793  -0.0559   0.0049   1.0000
  14.500   1.4797   0.06712   0.06251  -0.0569   0.0049   1.0000
  14.750   1.4715   0.07188   0.06742  -0.0582   0.0048   1.0000
  15.000   1.4622   0.07700   0.07268  -0.0598   0.0048   1.0000
  15.250   1.4526   0.08236   0.07818  -0.0616   0.0047   1.0000
  15.500   1.4421   0.08797   0.08393  -0.0637   0.0047   1.0000
  15.750   1.4305   0.09388   0.08999  -0.0660   0.0047   1.0000
  16.000   1.4188   0.09999   0.09626  -0.0686   0.0046   1.0000
  16.250   1.4063   0.10637   0.10277  -0.0714   0.0046   1.0000
  16.500   1.3932   0.11298   0.10952  -0.0744   0.0046   1.0000
  16.750   1.3799   0.11979   0.11647  -0.0776   0.0046   1.0000
  17.000   1.3656   0.12701   0.12383  -0.0812   0.0046   1.0000
  17.250   1.3525   0.13419   0.13115  -0.0850   0.0045   1.0000
  17.500   1.3383   0.14180   0.13889  -0.0891   0.0045   1.0000
  17.750   1.3228   0.15005   0.14729  -0.0938   0.0045   1.0000
  18.000   1.3076   0.15866   0.15602  -0.0989   0.0045   1.0000
  18.250   1.2887   0.16881   0.16634  -0.1051   0.0045   1.0000
  18.500   1.2631   0.18170   0.17943  -0.1131   0.0046   1.0000
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