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GOE 115 (MVA MK.2) AIRFOIL (goe115-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 115 (MVA MK.2) AIRFOIL (goe115-il)
Reynolds number: 1,000,000
Max Cl/Cd: 98.72 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe115-il-1000000-n5.txt
Download as CSV file: xf-goe115-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 115 (MVA MK.2) 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.6003   0.07414   0.07262  -0.0454   1.0000   0.0039
 -11.250  -0.7757   0.03595   0.03400  -0.0759   1.0000   0.0032
 -11.000  -0.7717   0.02863   0.02616  -0.0830   0.9903   0.0033
 -10.750  -0.7521   0.02522   0.02242  -0.0859   0.9828   0.0034
 -10.500  -0.7256   0.02275   0.01966  -0.0887   0.9762   0.0035
 -10.250  -0.6973   0.02067   0.01731  -0.0911   0.9670   0.0036
 -10.000  -0.6676   0.01855   0.01491  -0.0937   0.9546   0.0038
  -9.750  -0.6369   0.01728   0.01344  -0.0955   0.9388   0.0041
  -9.500  -0.6102   0.01633   0.01229  -0.0961   0.9178   0.0042
  -9.250  -0.5863   0.01564   0.01142  -0.0959   0.8972   0.0044
  -9.000  -0.5635   0.01497   0.01055  -0.0953   0.8780   0.0046
  -8.750  -0.5404   0.01434   0.00973  -0.0948   0.8623   0.0049
  -8.500  -0.5168   0.01375   0.00899  -0.0943   0.8486   0.0051
  -8.250  -0.4927   0.01323   0.00831  -0.0939   0.8363   0.0053
  -8.000  -0.4683   0.01271   0.00764  -0.0935   0.8247   0.0056
  -7.750  -0.4439   0.01214   0.00695  -0.0931   0.8135   0.0062
  -7.500  -0.4188   0.01173   0.00645  -0.0927   0.8027   0.0067
  -7.250  -0.3933   0.01140   0.00601  -0.0924   0.7914   0.0074
  -6.750  -0.3420   0.01068   0.00507  -0.0918   0.7684   0.0088
  -6.500  -0.3157   0.01044   0.00477  -0.0916   0.7570   0.0100
  -6.250  -0.2893   0.01024   0.00450  -0.0914   0.7450   0.0113
  -6.000  -0.2628   0.01007   0.00425  -0.0912   0.7322   0.0128
  -5.750  -0.2354   0.01012   0.00430  -0.0911   0.7185   0.0147
  -5.500  -0.2082   0.01012   0.00423  -0.0909   0.7043   0.0164
  -5.250  -0.1814   0.01006   0.00408  -0.0908   0.6897   0.0175
  -5.000  -0.1541   0.01011   0.00405  -0.0907   0.6757   0.0181
  -4.750  -0.1282   0.00979   0.00363  -0.0904   0.6628   0.0193
  -4.500  -0.1013   0.00967   0.00344  -0.0902   0.6513   0.0203
  -4.250  -0.0742   0.00956   0.00328  -0.0901   0.6419   0.0214
  -4.000  -0.0473   0.00940   0.00305  -0.0900   0.6335   0.0224
  -3.750  -0.0202   0.00924   0.00282  -0.0899   0.6258   0.0233
  -3.500   0.0068   0.00909   0.00260  -0.0897   0.6189   0.0241
  -3.250   0.0340   0.00892   0.00236  -0.0896   0.6126   0.0247
  -3.000   0.0612   0.00880   0.00218  -0.0895   0.6066   0.0253
  -2.750   0.0886   0.00866   0.00200  -0.0894   0.6013   0.0258
  -2.500   0.1160   0.00856   0.00186  -0.0893   0.5956   0.0263
  -2.250   0.1434   0.00849   0.00175  -0.0892   0.5905   0.0266
  -2.000   0.1709   0.00834   0.00155  -0.0892   0.5859   0.0275
  -1.750   0.1983   0.00823   0.00139  -0.0891   0.5813   0.0285
  -1.250   0.2534   0.00809   0.00119  -0.0889   0.5722   0.0299
  -1.000   0.2809   0.00805   0.00113  -0.0889   0.5668   0.0304
  -0.500   0.3360   0.00799   0.00102  -0.0887   0.5571   0.0313
  -0.250   0.3637   0.00796   0.00099  -0.0887   0.5528   0.0323
   0.000   0.3912   0.00794   0.00096  -0.0886   0.5489   0.0333
   0.250   0.4188   0.00793   0.00095  -0.0886   0.5450   0.0340
   0.500   0.4465   0.00792   0.00094  -0.0886   0.5404   0.0353
   0.750   0.4738   0.00785   0.00094  -0.0885   0.5367   0.0717
   1.000   0.4999   0.00752   0.00090  -0.0883   0.5335   0.1838
   1.250   0.5267   0.00737   0.00098  -0.0882   0.5303   0.2567
   1.500   0.5543   0.00736   0.00104  -0.0882   0.5262   0.2720
   1.750   0.5818   0.00739   0.00109  -0.0881   0.5218   0.2807
   2.000   0.6091   0.00743   0.00115  -0.0880   0.5175   0.2873
   2.250   0.6368   0.00744   0.00121  -0.0880   0.5138   0.2931
   2.500   0.6641   0.00747   0.00128  -0.0880   0.5077   0.3005
   2.750   0.6911   0.00751   0.00136  -0.0878   0.4980   0.3116
   3.000   0.7179   0.00757   0.00145  -0.0877   0.4892   0.3236
   3.250   0.7450   0.00760   0.00153  -0.0876   0.4798   0.3350
   3.500   0.7700   0.00780   0.00163  -0.0871   0.4439   0.3426
   4.000   0.8116   0.00901   0.00227  -0.0849   0.2969   0.3633
   4.250   0.8327   0.00959   0.00262  -0.0839   0.2347   0.3818
   4.500   0.8413   0.01130   0.00355  -0.0810   0.0510   0.4066
   4.750   0.8634   0.01139   0.00389  -0.0802   0.0327   0.5342
   5.250   0.9244   0.01115   0.00460  -0.0820   0.0129   1.0000
   5.500   0.9487   0.01142   0.00488  -0.0814   0.0113   1.0000
   5.750   0.9723   0.01172   0.00520  -0.0808   0.0097   1.0000
   6.000   0.9950   0.01211   0.00560  -0.0799   0.0081   1.0000
   6.250   1.0181   0.01245   0.00597  -0.0791   0.0075   1.0000
   6.500   1.0409   0.01281   0.00636  -0.0783   0.0069   1.0000
   6.750   1.0632   0.01319   0.00677  -0.0774   0.0064   1.0000
   7.000   1.0854   0.01356   0.00713  -0.0766   0.0057   1.0000
   7.250   1.1049   0.01413   0.00777  -0.0752   0.0052   1.0000
   7.500   1.1259   0.01455   0.00823  -0.0742   0.0049   1.0000
   7.750   1.1457   0.01505   0.00878  -0.0729   0.0047   1.0000
   8.000   1.1651   0.01555   0.00933  -0.0716   0.0044   1.0000
   8.250   1.1832   0.01611   0.00994  -0.0701   0.0042   1.0000
   8.500   1.2012   0.01664   0.01051  -0.0686   0.0039   1.0000
   8.750   1.2176   0.01724   0.01116  -0.0668   0.0038   1.0000
   9.000   1.2326   0.01784   0.01180  -0.0649   0.0036   1.0000
   9.250   1.2443   0.01848   0.01251  -0.0623   0.0035   1.0000
   9.500   1.2526   0.01930   0.01339  -0.0593   0.0033   1.0000
   9.750   1.2582   0.02034   0.01452  -0.0560   0.0033   1.0000
  10.000   1.2672   0.02125   0.01552  -0.0535   0.0031   1.0000
  10.250   1.2780   0.02210   0.01644  -0.0514   0.0030   1.0000
  10.500   1.2846   0.02330   0.01774  -0.0489   0.0030   1.0000
  10.750   1.2968   0.02415   0.01866  -0.0473   0.0028   1.0000
  11.000   1.3020   0.02560   0.02022  -0.0451   0.0028   1.0000
  11.250   1.3121   0.02672   0.02141  -0.0435   0.0027   1.0000
  11.500   1.3212   0.02796   0.02274  -0.0420   0.0026   1.0000
  11.750   1.3286   0.02941   0.02429  -0.0405   0.0025   1.0000
  12.000   1.3322   0.03132   0.02633  -0.0387   0.0025   1.0000
  12.250   1.3418   0.03264   0.02772  -0.0377   0.0023   1.0000
  12.500   1.3475   0.03441   0.02959  -0.0364   0.0023   1.0000
  12.750   1.3504   0.03652   0.03184  -0.0351   0.0023   1.0000
  13.000   1.3603   0.03789   0.03325  -0.0345   0.0022   1.0000
  13.250   1.3618   0.04025   0.03575  -0.0335   0.0022   1.0000
  13.500   1.3669   0.04223   0.03782  -0.0328   0.0021   1.0000
  13.750   1.3667   0.04490   0.04063  -0.0321   0.0021   1.0000
  14.000   1.3690   0.04731   0.04315  -0.0317   0.0020   1.0000
  14.250   1.3693   0.05003   0.04599  -0.0313   0.0020   1.0000
  14.500   1.3664   0.05322   0.04932  -0.0311   0.0020   1.0000
  14.750   1.3607   0.05687   0.05312  -0.0311   0.0020   1.0000
  15.000   1.3552   0.06064   0.05704  -0.0313   0.0020   1.0000
  15.250   1.3460   0.06510   0.06166  -0.0320   0.0019   1.0000
  15.500   1.3315   0.07048   0.06724  -0.0330   0.0019   1.0000
  15.750   1.3221   0.07536   0.07227  -0.0343   0.0019   1.0000
  16.000   1.3027   0.08211   0.07923  -0.0364   0.0019   1.0000
  16.250   1.2819   0.08945   0.08678  -0.0391   0.0018   1.0000
  16.500   1.2752   0.09460   0.09204  -0.0413   0.0019   1.0000
  16.750   1.2449   0.10468   0.10235  -0.0460   0.0018   1.0000
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