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GOE 118 (MVA MK.7) AIRFOIL (goe118-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 118 (MVA MK.7) AIRFOIL (goe118-il)
Reynolds number: 200,000
Max Cl/Cd: 82.7 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe118-il-200000-n5.txt
Download as CSV file: xf-goe118-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 118 (MVA MK.7) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2592   0.11050   0.10723  -0.0395   1.0000   0.0136
  -9.000  -0.2551   0.10778   0.10456  -0.0401   1.0000   0.0139
  -8.750  -0.2523   0.10521   0.10203  -0.0404   0.9998   0.0143
  -8.500  -0.2371   0.10134   0.09817  -0.0444   0.9887   0.0148
  -8.250  -0.2223   0.09755   0.09439  -0.0482   0.9748   0.0153
  -8.000  -0.2075   0.09380   0.09059  -0.0521   0.9588   0.0159
  -7.500  -0.1799   0.08659   0.08335  -0.0592   0.9224   0.0173
  -7.250  -0.1688   0.08328   0.08001  -0.0621   0.9031   0.0180
  -7.000  -0.1587   0.08019   0.07688  -0.0652   0.8844   0.0189
  -6.750  -0.1424   0.07687   0.07350  -0.0714   0.8667   0.0198
  -6.500  -0.1235   0.07327   0.06984  -0.0771   0.8515   0.0202
  -6.250  -0.1040   0.06954   0.06604  -0.0820   0.8381   0.0203
  -6.000  -0.0829   0.06560   0.06201  -0.0870   0.8257   0.0204
  -5.750  -0.0601   0.06149   0.05780  -0.0920   0.8145   0.0205
  -5.500  -0.0355   0.05721   0.05340  -0.0972   0.8042   0.0205
  -5.250  -0.0091   0.05278   0.04885  -0.1022   0.7940   0.0205
  -5.000   0.0160   0.02896   0.02514  -0.0964   0.7602   0.0151
  -4.750   0.0522   0.02226   0.01822  -0.1046   0.7546   0.0112
  -3.750   0.1731   0.02215   0.01584  -0.1252   0.7474   0.0115
  -3.500   0.2026   0.01995   0.01310  -0.1259   0.7397   0.0114
  -3.250   0.2316   0.01803   0.01066  -0.1262   0.7330   0.0115
  -3.000   0.2602   0.01634   0.00861  -0.1264   0.7255   0.0118
  -2.500   0.3163   0.01426   0.00611  -0.1266   0.7119   0.0151
  -2.250   0.3446   0.01367   0.00532  -0.1265   0.7055   0.0175
  -2.000   0.3730   0.01320   0.00465  -0.1265   0.6982   0.0197
  -1.750   0.4011   0.01267   0.00391  -0.1265   0.6918   0.0274
  -1.500   0.4290   0.01229   0.00364  -0.1266   0.6848   0.0903
  -1.250   0.4565   0.01241   0.00366  -0.1266   0.6781   0.1126
  -1.000   0.4841   0.01246   0.00363  -0.1267   0.6711   0.1270
  -0.750   0.5116   0.01237   0.00342  -0.1267   0.6642   0.1294
  -0.500   0.5391   0.01230   0.00327  -0.1268   0.6570   0.1325
  -0.250   0.5664   0.01225   0.00314  -0.1268   0.6496   0.1370
   0.000   0.5938   0.01218   0.00304  -0.1269   0.6416   0.1434
   0.250   0.6211   0.01216   0.00295  -0.1269   0.6344   0.1517
   0.500   0.6485   0.01210   0.00292  -0.1270   0.6267   0.1657
   0.750   0.6757   0.01199   0.00292  -0.1271   0.6202   0.2074
   1.000   0.6970   0.01074   0.00311  -0.1262   0.6134   0.7387
   1.250   0.7259   0.01049   0.00304  -0.1262   0.6069   1.0000
   1.500   0.7532   0.01061   0.00310  -0.1262   0.6002   1.0000
   1.750   0.7803   0.01074   0.00318  -0.1262   0.5936   1.0000
   2.000   0.8073   0.01087   0.00326  -0.1262   0.5858   1.0000
   2.250   0.8340   0.01102   0.00334  -0.1261   0.5775   1.0000
   2.500   0.8607   0.01115   0.00347  -0.1260   0.5684   1.0000
   2.750   0.8873   0.01131   0.00363  -0.1259   0.5602   1.0000
   3.000   0.9140   0.01146   0.00381  -0.1259   0.5525   1.0000
   3.250   0.9406   0.01164   0.00400  -0.1258   0.5460   1.0000
   3.500   0.9670   0.01181   0.00425  -0.1257   0.5374   1.0000
   3.750   0.9921   0.01200   0.00443  -0.1252   0.5208   1.0000
   4.000   1.0147   0.01227   0.00460  -0.1243   0.4837   1.0000
   4.250   1.0325   0.01291   0.00487  -0.1227   0.4083   1.0000
   4.500   1.0285   0.01590   0.00634  -0.1184   0.1620   1.0000
   4.750   1.0364   0.01795   0.00794  -0.1155   0.0236   1.0000
   5.000   1.0570   0.01864   0.00883  -0.1144   0.0177   1.0000
   5.250   1.0752   0.01952   0.00990  -0.1128   0.0144   1.0000
   5.500   1.0924   0.02041   0.01098  -0.1112   0.0124   1.0000
   5.750   1.1056   0.02157   0.01232  -0.1090   0.0114   1.0000
   6.000   1.1151   0.02290   0.01379  -0.1063   0.0106   1.0000
   6.250   1.1200   0.02436   0.01536  -0.1031   0.0094   1.0000
   6.500   1.1135   0.02655   0.01762  -0.0984   0.0085   1.0000
   6.750   1.1197   0.02807   0.01922  -0.0955   0.0081   1.0000
   7.000   1.1268   0.02972   0.02094  -0.0929   0.0079   1.0000
   7.250   1.1370   0.03142   0.02270  -0.0905   0.0077   1.0000
   7.500   1.1529   0.03314   0.02448  -0.0885   0.0076   1.0000
   7.750   1.1787   0.03502   0.02643  -0.0874   0.0075   1.0000
   8.000   1.2191   0.03755   0.02907  -0.0882   0.0075   1.0000
   8.250   1.2432   0.03919   0.03091  -0.0874   0.0066   1.0000
   8.500   1.2618   0.04097   0.03286  -0.0865   0.0057   1.0000
   8.750   1.2945   0.04422   0.03639  -0.0868   0.0057   1.0000
   9.000   1.3205   0.04813   0.04068  -0.0856   0.0064   1.0000
   9.250   1.3352   0.05214   0.04500  -0.0838   0.0070   1.0000
   9.500   1.3588   0.05606   0.04939  -0.0812   0.0117   1.0000
   9.750   1.3626   0.05934   0.05297  -0.0783   0.0120   1.0000
  10.000   1.3620   0.06245   0.05635  -0.0751   0.0120   1.0000
  10.250   1.3554   0.06530   0.05945  -0.0714   0.0118   1.0000
  10.500   1.3459   0.06817   0.06255  -0.0678   0.0117   1.0000
  10.750   1.3342   0.07122   0.06581  -0.0646   0.0116   1.0000
  11.000   1.3209   0.07446   0.06927  -0.0619   0.0115   1.0000
  11.250   1.3063   0.07798   0.07299  -0.0598   0.0114   1.0000
  11.500   1.2905   0.08176   0.07698  -0.0582   0.0114   1.0000
  11.750   1.2737   0.08586   0.08126  -0.0573   0.0113   1.0000
  12.000   1.2562   0.09028   0.08587  -0.0570   0.0113   1.0000
  12.250   1.2380   0.09505   0.09082  -0.0572   0.0113   1.0000
  12.500   1.2195   0.10016   0.09611  -0.0581   0.0113   1.0000
  12.750   1.2006   0.10564   0.10175  -0.0597   0.0114   1.0000
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