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GOE 115 (MVA MK.2) AIRFOIL (goe115-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 115 (MVA MK.2) AIRFOIL (goe115-il)
Reynolds number: 1,000,000
Max Cl/Cd: 131.98 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe115-il-1000000.txt
Download as CSV file: xf-goe115-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3251   0.08013   0.07866  -0.0418   1.0000   0.0127
  -9.750  -0.3259   0.07666   0.07520  -0.0424   1.0000   0.0129
  -9.250  -0.4497   0.04211   0.04071  -0.0530   1.0000   0.0092
  -9.000  -0.4323   0.04331   0.04195  -0.0518   1.0000   0.0095
  -8.750  -0.5171   0.03683   0.03488  -0.0811   0.9874   0.0085
  -8.500  -0.5163   0.02199   0.01877  -0.0910   0.9731   0.0094
  -8.250  -0.4823   0.02148   0.01815  -0.0932   0.9672   0.0097
  -8.000  -0.4498   0.02048   0.01698  -0.0952   0.9578   0.0101
  -7.750  -0.4201   0.01875   0.01500  -0.0966   0.9446   0.0107
  -7.500  -0.3941   0.01681   0.01275  -0.0970   0.9279   0.0115
  -7.250  -0.3699   0.01561   0.01130  -0.0967   0.9102   0.0121
  -7.000  -0.3486   0.01403   0.00944  -0.0959   0.8930   0.0130
  -6.750  -0.3225   0.01407   0.00941  -0.0957   0.8779   0.0135
  -6.500  -0.2960   0.01425   0.00951  -0.0955   0.8638   0.0142
  -6.250  -0.2709   0.01385   0.00899  -0.0951   0.8505   0.0151
  -6.000  -0.2457   0.01338   0.00837  -0.0946   0.8380   0.0161
  -5.750  -0.2194   0.01326   0.00811  -0.0942   0.8261   0.0168
  -5.500  -0.1966   0.01193   0.00666  -0.0935   0.8144   0.0181
  -5.250  -0.1707   0.01166   0.00634  -0.0933   0.8028   0.0191
  -5.000  -0.1445   0.01148   0.00609  -0.0930   0.7912   0.0203
  -4.750  -0.1185   0.01115   0.00567  -0.0927   0.7792   0.0215
  -4.500  -0.0922   0.01090   0.00533  -0.0923   0.7666   0.0226
  -4.250  -0.0651   0.01093   0.00526  -0.0921   0.7530   0.0234
  -4.000  -0.0420   0.00983   0.00406  -0.0914   0.7389   0.0252
  -3.750  -0.0166   0.00939   0.00355  -0.0909   0.7241   0.0264
  -3.500   0.0093   0.00908   0.00315  -0.0906   0.7094   0.0276
  -3.250   0.0355   0.00884   0.00281  -0.0902   0.6952   0.0287
  -3.000   0.0620   0.00865   0.00253  -0.0900   0.6819   0.0301
  -2.750   0.0887   0.00848   0.00227  -0.0897   0.6699   0.0308
  -2.500   0.1156   0.00833   0.00203  -0.0895   0.6593   0.0313
  -2.250   0.1426   0.00820   0.00183  -0.0893   0.6501   0.0316
  -2.000   0.1697   0.00810   0.00165  -0.0891   0.6414   0.0320
  -1.750   0.1970   0.00800   0.00151  -0.0889   0.6338   0.0326
  -1.500   0.2241   0.00791   0.00132  -0.0887   0.6266   0.0341
  -1.250   0.2517   0.00784   0.00120  -0.0886   0.6197   0.0363
  -1.000   0.2789   0.00782   0.00112  -0.0885   0.6129   0.0389
  -0.750   0.3065   0.00777   0.00107  -0.0884   0.6068   0.0424
  -0.500   0.3325   0.00739   0.00096  -0.0881   0.6010   0.1491
  -0.250   0.3584   0.00712   0.00096  -0.0879   0.5960   0.2409
   0.000   0.3860   0.00708   0.00101  -0.0879   0.5913   0.2736
   0.250   0.4135   0.00710   0.00106  -0.0878   0.5864   0.2905
   0.500   0.4409   0.00714   0.00110  -0.0877   0.5817   0.3004
   0.750   0.4687   0.00712   0.00113  -0.0877   0.5775   0.3094
   1.000   0.4964   0.00715   0.00116  -0.0877   0.5732   0.3152
   1.250   0.5238   0.00719   0.00120  -0.0876   0.5693   0.3202
   1.500   0.5514   0.00720   0.00125  -0.0875   0.5654   0.3263
   1.750   0.5791   0.00721   0.00129  -0.0875   0.5609   0.3330
   2.000   0.6064   0.00722   0.00134  -0.0874   0.5566   0.3438
   2.250   0.6336   0.00725   0.00141  -0.0873   0.5527   0.3538
   2.500   0.6613   0.00724   0.00148  -0.0873   0.5494   0.3635
   2.750   0.6884   0.00724   0.00153  -0.0871   0.5432   0.3785
   3.000   0.7151   0.00719   0.00161  -0.0869   0.5345   0.4117
   3.250   0.7396   0.00693   0.00171  -0.0864   0.5225   0.5642
   3.500   0.7865   0.00610   0.00187  -0.0909   0.5074   1.0000
   3.750   0.8125   0.00621   0.00195  -0.0905   0.4951   1.0000
   4.000   0.8381   0.00635   0.00204  -0.0901   0.4723   1.0000
   4.250   0.8605   0.00674   0.00219  -0.0891   0.4133   1.0000
   4.500   0.8745   0.00790   0.00274  -0.0868   0.2907   1.0000
   4.750   0.8778   0.01006   0.00382  -0.0830   0.0697   1.0000
   5.000   0.8982   0.01070   0.00428  -0.0817   0.0300   1.0000
   5.250   0.9211   0.01110   0.00466  -0.0808   0.0214   1.0000
   5.500   0.9438   0.01151   0.00506  -0.0799   0.0175   1.0000
   5.750   0.9663   0.01194   0.00554  -0.0789   0.0158   1.0000
   6.000   0.9893   0.01230   0.00593  -0.0781   0.0147   1.0000
   6.250   1.0116   0.01271   0.00637  -0.0771   0.0136   1.0000
   6.500   1.0325   0.01322   0.00691  -0.0760   0.0125   1.0000
   6.750   1.0476   0.01417   0.00797  -0.0738   0.0113   1.0000
   7.000   1.0694   0.01455   0.00838  -0.0728   0.0109   1.0000
   7.250   1.0888   0.01510   0.00897  -0.0714   0.0104   1.0000
   7.500   1.1070   0.01570   0.00964  -0.0698   0.0099   1.0000
   7.750   1.1242   0.01634   0.01033  -0.0681   0.0094   1.0000
   8.000   1.1404   0.01703   0.01106  -0.0663   0.0091   1.0000
   8.250   1.1564   0.01768   0.01173  -0.0645   0.0086   1.0000
   8.500   1.1665   0.01862   0.01274  -0.0617   0.0084   1.0000
   8.750   1.1692   0.01997   0.01416  -0.0576   0.0080   1.0000
   9.000   1.1723   0.02195   0.01626  -0.0539   0.0077   1.0000
   9.250   1.1874   0.02249   0.01687  -0.0521   0.0075   1.0000
   9.500   1.2020   0.02312   0.01758  -0.0503   0.0071   1.0000
   9.750   1.2147   0.02422   0.01876  -0.0483   0.0069   1.0000
  10.000   1.2276   0.02546   0.02009  -0.0465   0.0067   1.0000
  10.250   1.2406   0.02682   0.02156  -0.0447   0.0065   1.0000
  10.500   1.2539   0.02843   0.02330  -0.0431   0.0064   1.0000
  10.750   1.2669   0.03036   0.02539  -0.0415   0.0063   1.0000
  11.000   1.2760   0.03142   0.02652  -0.0397   0.0061   1.0000
  11.250   1.2856   0.03401   0.02935  -0.0378   0.0060   1.0000
  11.500   1.2912   0.03427   0.02959  -0.0361   0.0058   1.0000
  11.750   1.2949   0.03790   0.03353  -0.0339   0.0058   1.0000
  12.000   1.2985   0.03871   0.03435  -0.0324   0.0056   1.0000
  12.250   1.3014   0.04013   0.03585  -0.0311   0.0055   1.0000
  12.500   1.2919   0.04501   0.04110  -0.0287   0.0056   1.0000
  12.750   1.2911   0.04690   0.04306  -0.0277   0.0055   1.0000
  13.000   1.2815   0.05060   0.04696  -0.0265   0.0054   1.0000
  13.250   1.2386   0.05882   0.05556  -0.0256   0.0052   1.0000
  13.500   1.2509   0.05952   0.05627  -0.0255   0.0053   1.0000
  13.750   1.2147   0.06742   0.06448  -0.0263   0.0052   1.0000
  14.000   1.2099   0.07094   0.06811  -0.0270   0.0052   1.0000
  14.250   1.1895   0.07713   0.07449  -0.0288   0.0052   1.0000
  14.500   1.1602   0.08528   0.08285  -0.0318   0.0052   1.0000
  14.750   1.1491   0.09087   0.08857  -0.0342   0.0053   1.0000
  15.000   1.1181   0.10065   0.09853  -0.0392   0.0052   1.0000
  15.250   1.1009   0.10854   0.10657  -0.0435   0.0053   1.0000
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