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GOE 121 (MVA H.1) AIRFOIL (goe121-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 121 (MVA H.1) AIRFOIL (goe121-il)
Reynolds number: 50,000
Max Cl/Cd: 43.42 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe121-il-50000-n5.txt
Download as CSV file: xf-goe121-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3580   0.10761   0.10050  -0.0204   1.0000   0.0995
  -8.000  -0.3606   0.10611   0.09910  -0.0219   1.0000   0.1012
  -7.750  -0.3642   0.10492   0.09803  -0.0247   1.0000   0.1020
  -7.500  -0.3609   0.10207   0.09528  -0.0271   1.0000   0.1028
  -7.250  -0.3461   0.09665   0.08983  -0.0225   1.0000   0.1068
  -7.000  -0.3412   0.09396   0.08721  -0.0231   1.0000   0.1099
  -6.750  -0.3377   0.09156   0.08487  -0.0249   1.0000   0.1126
  -6.500  -0.3339   0.08968   0.08306  -0.0292   1.0000   0.1149
  -6.250  -0.3260   0.08752   0.08093  -0.0344   1.0000   0.1157
  -6.000  -0.3178   0.08414   0.07760  -0.0357   1.0000   0.1163
  -5.750  -0.3121   0.08040   0.07391  -0.0331   1.0000   0.1174
  -5.500  -0.3058   0.07743   0.07097  -0.0312   1.0000   0.1201
  -5.250  -0.2967   0.07503   0.06858  -0.0323   1.0000   0.1263
  -4.750  -0.2749   0.06938   0.06292  -0.0355   1.0000   0.1336
  -4.250  -0.2208   0.05963   0.05269  -0.0475   1.0000   0.0883
  -4.000  -0.2057   0.05671   0.04974  -0.0479   1.0000   0.0854
  -3.750  -0.1818   0.05321   0.04608  -0.0510   1.0000   0.0821
  -3.500  -0.1514   0.04932   0.04190  -0.0554   1.0000   0.0797
  -3.250  -0.1287   0.04709   0.03954  -0.0570   1.0000   0.0820
  -3.000  -0.1013   0.04451   0.03674  -0.0595   1.0000   0.0838
  -2.750  -0.0554   0.04092   0.03276  -0.0655   0.9953   0.0828
  -2.500  -0.0063   0.03738   0.02875  -0.0717   0.9892   0.0817
  -2.250   0.0402   0.03444   0.02530  -0.0767   0.9836   0.0816
  -2.000   0.0846   0.03202   0.02241  -0.0809   0.9773   0.0825
  -1.750   0.1273   0.03000   0.01992  -0.0845   0.9704   0.0844
  -1.500   0.1721   0.02818   0.01749  -0.0880   0.9640   0.0887
  -1.250   0.2090   0.02737   0.01660  -0.0903   0.9546   0.0963
  -1.000   0.2505   0.02616   0.01500  -0.0929   0.9457   0.1042
  -0.750   0.2957   0.02499   0.01353  -0.0959   0.9366   0.1144
  -0.500   0.3372   0.02397   0.01234  -0.0981   0.9246   0.1312
  -0.250   0.3789   0.02337   0.01184  -0.1006   0.9120   0.1636
   0.000   0.4186   0.02301   0.01156  -0.1026   0.8991   0.2024
   0.250   0.4558   0.02254   0.01110  -0.1039   0.8864   0.2254
   0.500   0.4911   0.02210   0.01065  -0.1048   0.8733   0.2423
   0.750   0.5242   0.02173   0.01034  -0.1053   0.8590   0.2673
   1.000   0.5557   0.02129   0.01007  -0.1056   0.8436   0.3037
   1.250   0.5857   0.02014   0.00985  -0.1059   0.8282   0.4902
   1.500   0.6094   0.01945   0.00956  -0.1037   0.8101   1.0000
   1.750   0.6394   0.01947   0.00939  -0.1034   0.7925   1.0000
   2.000   0.6696   0.01948   0.00926  -0.1029   0.7750   1.0000
   2.250   0.6970   0.01958   0.00926  -0.1022   0.7549   1.0000
   2.500   0.7253   0.01966   0.00923  -0.1015   0.7346   1.0000
   2.750   0.7539   0.01974   0.00922  -0.1007   0.7143   1.0000
   3.000   0.7795   0.01995   0.00937  -0.0998   0.6898   1.0000
   3.250   0.8054   0.02016   0.00951  -0.0988   0.6652   1.0000
   3.500   0.8309   0.02039   0.00970  -0.0977   0.6400   1.0000
   3.750   0.8555   0.02066   0.00993  -0.0967   0.6137   1.0000
   4.000   0.8806   0.02092   0.01012  -0.0956   0.5890   1.0000
   4.250   0.9061   0.02122   0.01034  -0.0946   0.5667   1.0000
   4.500   0.9311   0.02162   0.01067  -0.0937   0.5447   1.0000
   4.750   0.9562   0.02209   0.01107  -0.0928   0.5245   1.0000
   5.000   0.9815   0.02261   0.01159  -0.0921   0.5060   1.0000
   5.250   1.0064   0.02318   0.01217  -0.0914   0.4882   1.0000
   5.500   1.0306   0.02379   0.01286  -0.0906   0.4699   1.0000
   5.750   1.0544   0.02440   0.01357  -0.0898   0.4522   1.0000
   6.000   1.0780   0.02501   0.01433  -0.0889   0.4352   1.0000
   6.250   1.1015   0.02565   0.01510  -0.0881   0.4192   1.0000
   6.500   1.1249   0.02630   0.01592  -0.0872   0.4040   1.0000
   6.750   1.1480   0.02698   0.01677  -0.0863   0.3890   1.0000
   7.000   1.1677   0.02754   0.01739  -0.0847   0.3669   1.0000
   7.250   1.1830   0.02810   0.01801  -0.0827   0.3360   1.0000
   7.500   1.1987   0.02879   0.01875  -0.0808   0.3067   1.0000
   7.750   1.2123   0.02955   0.01965  -0.0788   0.2674   1.0000
   8.000   1.2244   0.03052   0.02060  -0.0767   0.2147   1.0000
   8.250   1.2289   0.03253   0.02205  -0.0741   0.1518   1.0000
   8.500   1.2303   0.03543   0.02432  -0.0717   0.0865   1.0000
   8.750   1.2315   0.03828   0.02706  -0.0691   0.0727   1.0000
   9.000   1.2325   0.04086   0.02977  -0.0664   0.0651   1.0000
   9.250   1.2357   0.04295   0.03212  -0.0638   0.0587   1.0000
   9.500   1.2356   0.04536   0.03460  -0.0615   0.0544   1.0000
   9.750   1.2378   0.04767   0.03714  -0.0594   0.0506   1.0000
  10.000   1.2381   0.05024   0.03986  -0.0577   0.0481   1.0000
  10.250   1.2376   0.05301   0.04274  -0.0562   0.0464   1.0000
  10.500   1.2376   0.05587   0.04567  -0.0548   0.0451   1.0000
  10.750   1.2424   0.05848   0.04853  -0.0533   0.0435   1.0000
  11.000   1.2470   0.06119   0.05146  -0.0520   0.0416   1.0000
  11.250   1.2502   0.06406   0.05452  -0.0509   0.0398   1.0000
  11.500   1.2525   0.06706   0.05766  -0.0501   0.0382   1.0000
  11.750   1.2566   0.07006   0.06081  -0.0491   0.0370   1.0000
  12.000   1.2652   0.07309   0.06393  -0.0476   0.0361   1.0000
  12.250   1.2658   0.07690   0.06808  -0.0471   0.0357   1.0000
  12.500   1.2619   0.08125   0.07275  -0.0472   0.0355   1.0000
  12.750   1.2540   0.08611   0.07791  -0.0479   0.0353   1.0000
  13.000   1.2428   0.09152   0.08361  -0.0494   0.0352   1.0000
  13.250   1.2293   0.09748   0.08983  -0.0517   0.0351   1.0000
  13.500   1.2143   0.10401   0.09660  -0.0547   0.0352   1.0000
  13.750   1.1981   0.11111   0.10392  -0.0585   0.0352   1.0000
  14.000   1.1814   0.11873   0.11173  -0.0629   0.0354   1.0000
  14.250   1.1650   0.12684   0.12000  -0.0678   0.0356   1.0000
  14.500   1.1493   0.13542   0.12872  -0.0731   0.0358   1.0000
  14.750   1.1351   0.14424   0.13764  -0.0785   0.0361   1.0000
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