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


Details Polar file
Airfoil: GOE 121 (MVA H.1) AIRFOIL (goe121-il)
Reynolds number: 1,000,000
Max Cl/Cd: 97.71 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe121-il-1000000-n5.txt
Download as CSV file: xf-goe121-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.5106   0.16737   0.16560   0.0072   1.0000   0.0041
 -14.000  -0.5063   0.16294   0.16117   0.0056   1.0000   0.0044
 -13.750  -0.5064   0.15695   0.15519   0.0038   1.0000   0.0047
 -13.500  -0.5007   0.15351   0.15175   0.0024   1.0000   0.0049
 -13.250  -0.4936   0.15050   0.14875   0.0011   1.0000   0.0050
 -13.000  -0.4868   0.14743   0.14568  -0.0002   1.0000   0.0051
 -12.750  -0.4804   0.14422   0.14248  -0.0014   1.0000   0.0053
  -7.250  -0.2956   0.02092   0.01807  -0.1060   0.9321   0.0209
  -7.000  -0.2667   0.01864   0.01544  -0.1078   0.9173   0.0214
  -6.750  -0.2396   0.01737   0.01392  -0.1084   0.9067   0.0217
  -6.500  -0.2126   0.01660   0.01298  -0.1086   0.8965   0.0220
  -6.250  -0.1858   0.01562   0.01180  -0.1089   0.8865   0.0221
  -6.000  -0.1590   0.01478   0.01075  -0.1090   0.8753   0.0222
  -5.750  -0.1319   0.01405   0.00984  -0.1090   0.8642   0.0223
  -5.500  -0.1046   0.01342   0.00905  -0.1091   0.8537   0.0224
  -5.250  -0.0780   0.01125   0.00647  -0.1096   0.8418   0.0235
  -5.000  -0.0511   0.01070   0.00576  -0.1095   0.8219   0.0239
  -4.750  -0.0248   0.01038   0.00523  -0.1091   0.7877   0.0243
  -4.500   0.0017   0.01013   0.00479  -0.1088   0.7585   0.0247
  -4.250   0.0290   0.00989   0.00440  -0.1086   0.7390   0.0250
  -4.000   0.0565   0.00965   0.00404  -0.1084   0.7241   0.0254
  -3.750   0.0842   0.00941   0.00369  -0.1083   0.7124   0.0257
  -3.500   0.1121   0.00917   0.00336  -0.1082   0.7018   0.0259
  -3.250   0.1401   0.00894   0.00305  -0.1082   0.6922   0.0262
  -3.000   0.1681   0.00874   0.00276  -0.1081   0.6809   0.0264
  -2.750   0.1958   0.00857   0.00250  -0.1080   0.6622   0.0266
  -2.500   0.2231   0.00849   0.00226  -0.1077   0.6272   0.0268
  -2.250   0.2484   0.00869   0.00209  -0.1072   0.5398   0.0270
  -2.000   0.2756   0.00869   0.00193  -0.1070   0.5103   0.0272
  -1.750   0.3032   0.00866   0.00181  -0.1069   0.4919   0.0275
  -1.500   0.3309   0.00863   0.00169  -0.1068   0.4747   0.0280
  -1.250   0.3585   0.00863   0.00159  -0.1066   0.4514   0.0283
  -1.000   0.3855   0.00872   0.00150  -0.1064   0.4131   0.0286
  -0.750   0.4125   0.00884   0.00145  -0.1062   0.3741   0.0289
  -0.500   0.4396   0.00893   0.00141  -0.1060   0.3470   0.0295
  -0.250   0.4670   0.00901   0.00140  -0.1059   0.3272   0.0301
   0.000   0.4946   0.00906   0.00139  -0.1057   0.3141   0.0306
   0.250   0.5223   0.00909   0.00136  -0.1056   0.3035   0.0330
   0.500   0.5499   0.00914   0.00137  -0.1055   0.2926   0.0371
   1.000   0.6051   0.00917   0.00149  -0.1053   0.2697   0.0859
   1.250   0.6323   0.00930   0.00155  -0.1051   0.2535   0.0893
   1.500   0.6575   0.00973   0.00172  -0.1047   0.1899   0.0928
   1.750   0.6841   0.00995   0.00186  -0.1044   0.1692   0.0961
   2.000   0.7113   0.01006   0.00196  -0.1043   0.1621   0.0991
   2.250   0.7386   0.01017   0.00206  -0.1041   0.1580   0.1019
   2.500   0.7659   0.01026   0.00215  -0.1040   0.1541   0.1073
   2.750   0.7931   0.01036   0.00226  -0.1038   0.1499   0.1099
   3.000   0.8205   0.01043   0.00235  -0.1036   0.1478   0.1116
   3.250   0.8478   0.01051   0.00245  -0.1035   0.1452   0.1134
   3.500   0.8749   0.01062   0.00257  -0.1033   0.1415   0.1153
   3.750   0.9018   0.01077   0.00270  -0.1031   0.1358   0.1197
   4.000   0.9262   0.01127   0.00299  -0.1026   0.0859   0.1280
   4.250   0.9527   0.01139   0.00327  -0.1024   0.0788   0.2250
   4.500   0.9795   0.01149   0.00348  -0.1023   0.0760   0.2728
   4.750   1.0063   0.01157   0.00370  -0.1021   0.0738   0.3314
   5.000   1.0282   0.01060   0.00403  -0.1012   0.0700   1.0000
   5.250   1.0543   0.01087   0.00428  -0.1008   0.0652   1.0000
   5.500   1.0807   0.01106   0.00447  -0.1006   0.0589   1.0000
   5.750   1.1042   0.01169   0.00491  -0.0999   0.0255   1.0000
   6.000   1.1294   0.01204   0.00524  -0.0994   0.0198   1.0000
   6.250   1.1550   0.01234   0.00555  -0.0990   0.0171   1.0000
   6.500   1.1800   0.01270   0.00589  -0.0986   0.0144   1.0000
   6.750   1.2049   0.01305   0.00626  -0.0981   0.0126   1.0000
   7.000   1.2300   0.01337   0.00660  -0.0976   0.0117   1.0000
   7.250   1.2546   0.01373   0.00698  -0.0971   0.0107   1.0000
   7.500   1.2788   0.01415   0.00739  -0.0965   0.0097   1.0000
   7.750   1.3025   0.01461   0.00788  -0.0959   0.0088   1.0000
   8.000   1.3267   0.01498   0.00830  -0.0953   0.0083   1.0000
   8.250   1.3504   0.01540   0.00874  -0.0947   0.0078   1.0000
   8.500   1.3737   0.01584   0.00921  -0.0940   0.0073   1.0000
   8.750   1.3964   0.01632   0.00972  -0.0933   0.0069   1.0000
   9.000   1.4182   0.01691   0.01034  -0.0924   0.0064   1.0000
   9.250   1.4394   0.01754   0.01104  -0.0914   0.0061   1.0000
   9.500   1.4610   0.01808   0.01163  -0.0905   0.0059   1.0000
   9.750   1.4820   0.01865   0.01226  -0.0895   0.0057   1.0000
  10.000   1.5026   0.01922   0.01289  -0.0885   0.0054   1.0000
  10.250   1.5228   0.01981   0.01352  -0.0874   0.0051   1.0000
  10.500   1.5424   0.02041   0.01417  -0.0863   0.0049   1.0000
  10.750   1.5611   0.02106   0.01487  -0.0850   0.0047   1.0000
  11.000   1.5782   0.02181   0.01568  -0.0836   0.0045   1.0000
  11.250   1.5927   0.02274   0.01668  -0.0818   0.0043   1.0000
  11.500   1.6042   0.02382   0.01786  -0.0795   0.0041   1.0000
  11.750   1.6162   0.02466   0.01878  -0.0773   0.0041   1.0000
  12.000   1.6252   0.02557   0.01977  -0.0746   0.0040   1.0000
  12.250   1.6327   0.02660   0.02089  -0.0719   0.0039   1.0000
  12.500   1.6392   0.02774   0.02214  -0.0693   0.0038   1.0000
  12.750   1.6447   0.02904   0.02354  -0.0669   0.0038   1.0000
  13.000   1.6492   0.03052   0.02511  -0.0646   0.0037   1.0000
  13.250   1.6525   0.03220   0.02692  -0.0626   0.0036   1.0000
  13.500   1.6549   0.03408   0.02891  -0.0608   0.0036   1.0000
  13.750   1.6567   0.03614   0.03107  -0.0593   0.0035   1.0000
  14.000   1.6572   0.03847   0.03352  -0.0581   0.0034   1.0000
  14.250   1.6565   0.04107   0.03623  -0.0572   0.0034   1.0000
  14.500   1.6550   0.04395   0.03922  -0.0566   0.0033   1.0000
  14.750   1.6519   0.04718   0.04257  -0.0563   0.0033   1.0000
  15.000   1.6466   0.05080   0.04631  -0.0563   0.0032   1.0000
  15.250   1.6403   0.05474   0.05037  -0.0567   0.0032   1.0000
  15.500   1.6325   0.05907   0.05482  -0.0575   0.0032   1.0000
  15.750   1.6225   0.06395   0.05984  -0.0587   0.0031   1.0000
  16.000   1.6122   0.06916   0.06517  -0.0602   0.0031   1.0000
  16.250   1.5997   0.07485   0.07099  -0.0621   0.0031   1.0000
  16.500   1.5856   0.08089   0.07716  -0.0642   0.0031   1.0000
  16.750   1.5699   0.08731   0.08371  -0.0666   0.0031   1.0000
  17.000   1.5527   0.09408   0.09062  -0.0691   0.0031   1.0000
  17.250   1.5366   0.10077   0.09742  -0.0717   0.0031   1.0000
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