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GOE 414 AIRFOIL (goe414-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 414 AIRFOIL (goe414-il)
Reynolds number: 200,000
Max Cl/Cd: 74.47 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe414-il-200000.txt
Download as CSV file: xf-goe414-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 414 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2157   0.08801   0.08480  -0.0733   0.9722   0.0710
  -8.250  -0.2026   0.08403   0.08081  -0.0779   0.9666   0.0740
  -8.000  -0.2822   0.05039   0.04675  -0.1105   0.9439   0.0457
  -7.750  -0.2828   0.04300   0.03895  -0.1136   0.9348   0.0452
  -7.500  -0.2699   0.03556   0.03069  -0.1172   0.9289   0.0455
  -7.250  -0.2413   0.03069   0.02503  -0.1202   0.9262   0.0460
  -7.000  -0.2300   0.02745   0.02138  -0.1185   0.9163   0.0471
  -6.750  -0.1938   0.02619   0.02005  -0.1206   0.9133   0.0500
  -6.500  -0.1665   0.02478   0.01837  -0.1208   0.9077   0.0525
  -6.250  -0.1398   0.02319   0.01640  -0.1206   0.9013   0.0546
  -6.000  -0.1059   0.02154   0.01455  -0.1219   0.8980   0.0577
  -5.750  -0.0805   0.02091   0.01388  -0.1213   0.8903   0.0610
  -5.500  -0.0492   0.01990   0.01265  -0.1217   0.8850   0.0646
  -5.250  -0.0155   0.01878   0.01143  -0.1226   0.8816   0.0694
  -5.000   0.0074   0.01830   0.01091  -0.1215   0.8718   0.0745
  -4.750   0.0394   0.01729   0.00980  -0.1219   0.8674   0.0819
  -4.500   0.0638   0.01686   0.00929  -0.1211   0.8582   0.0935
  -4.250   0.0938   0.01615   0.00862  -0.1213   0.8530   0.1129
  -4.000   0.1189   0.01584   0.00826  -0.1207   0.8441   0.1275
  -3.750   0.1492   0.01544   0.00777  -0.1209   0.8381   0.1394
  -3.500   0.1747   0.01523   0.00750  -0.1204   0.8289   0.1496
  -3.250   0.2044   0.01477   0.00702  -0.1206   0.8226   0.1593
  -3.000   0.2297   0.01454   0.00674  -0.1200   0.8130   0.1690
  -2.750   0.2596   0.01419   0.00634  -0.1202   0.8068   0.1820
  -2.500   0.2842   0.01393   0.00614  -0.1196   0.7967   0.1968
  -2.250   0.3117   0.01357   0.00585  -0.1195   0.7891   0.2175
  -2.000   0.3377   0.01324   0.00565  -0.1191   0.7799   0.2530
  -1.750   0.3635   0.01293   0.00552  -0.1187   0.7710   0.3124
  -1.500   0.3907   0.01265   0.00533  -0.1184   0.7626   0.3683
  -1.250   0.4154   0.01243   0.00523  -0.1178   0.7523   0.4168
  -1.000   0.4408   0.01209   0.00507  -0.1173   0.7435   0.4801
  -0.750   0.4605   0.01140   0.00503  -0.1155   0.7338   0.6543
  -0.500   0.5451   0.01084   0.00498  -0.1264   0.7236   1.0000
  -0.250   0.5704   0.01089   0.00485  -0.1258   0.7137   1.0000
   0.000   0.5951   0.01095   0.00475  -0.1252   0.7030   1.0000
   0.250   0.6189   0.01104   0.00472  -0.1243   0.6915   1.0000
   0.500   0.6433   0.01115   0.00469  -0.1236   0.6802   1.0000
   0.750   0.6682   0.01127   0.00466  -0.1230   0.6692   1.0000
   1.000   0.6928   0.01142   0.00465  -0.1223   0.6574   1.0000
   1.250   0.7162   0.01158   0.00471  -0.1214   0.6446   1.0000
   1.500   0.7400   0.01177   0.00479  -0.1206   0.6320   1.0000
   1.750   0.7643   0.01198   0.00488  -0.1200   0.6202   1.0000
   2.000   0.7894   0.01221   0.00497  -0.1194   0.6096   1.0000
   2.250   0.8130   0.01242   0.00512  -0.1187   0.5983   1.0000
   2.500   0.8371   0.01266   0.00529  -0.1180   0.5879   1.0000
   2.750   0.8626   0.01290   0.00541  -0.1177   0.5792   1.0000
   3.000   0.8859   0.01311   0.00560  -0.1169   0.5693   1.0000
   3.250   0.9106   0.01334   0.00577  -0.1164   0.5609   1.0000
   3.500   0.9350   0.01354   0.00593  -0.1158   0.5527   1.0000
   3.750   0.9601   0.01379   0.00614  -0.1154   0.5459   1.0000
   4.000   0.9847   0.01402   0.00637  -0.1150   0.5390   1.0000
   4.250   1.0107   0.01427   0.00655  -0.1147   0.5333   1.0000
   4.500   1.0343   0.01449   0.00682  -0.1141   0.5262   1.0000
   4.750   1.0601   0.01473   0.00700  -0.1139   0.5206   1.0000
   5.000   1.0842   0.01499   0.00731  -0.1133   0.5144   1.0000
   5.250   1.1088   0.01523   0.00756  -0.1129   0.5086   1.0000
   5.500   1.1358   0.01553   0.00781  -0.1129   0.5042   1.0000
   5.750   1.1593   0.01582   0.00821  -0.1123   0.4992   1.0000
   6.000   1.1845   0.01611   0.00854  -0.1121   0.4945   1.0000
   6.250   1.2117   0.01642   0.00880  -0.1121   0.4897   1.0000
   6.500   1.2318   0.01666   0.00916  -0.1109   0.4817   1.0000
   6.750   1.2536   0.01688   0.00935  -0.1098   0.4717   1.0000
   7.000   1.2741   0.01711   0.00956  -0.1086   0.4614   1.0000
   7.250   1.2938   0.01739   0.00993  -0.1073   0.4525   1.0000
   7.500   1.3146   0.01769   0.01021  -0.1062   0.4425   1.0000
   7.750   1.3318   0.01796   0.01051  -0.1043   0.4311   1.0000
   8.000   1.3480   0.01826   0.01091  -0.1024   0.4207   1.0000
   8.250   1.3622   0.01857   0.01125  -0.1001   0.4081   1.0000
   8.500   1.3715   0.01888   0.01160  -0.0969   0.3926   1.0000
   8.750   1.3775   0.01921   0.01200  -0.0931   0.3764   1.0000
   9.000   1.3803   0.01970   0.01249  -0.0889   0.3546   1.0000
   9.250   1.3828   0.02038   0.01317  -0.0851   0.3202   1.0000
   9.500   1.3700   0.02206   0.01446  -0.0796   0.2587   1.0000
   9.750   1.3552   0.02442   0.01646  -0.0745   0.2117   1.0000
  10.000   1.3375   0.02731   0.01896  -0.0698   0.1397   1.0000
  10.250   1.3144   0.03089   0.02214  -0.0652   0.0866   1.0000
  10.500   1.2964   0.03439   0.02538  -0.0617   0.0453   1.0000
  10.750   1.2933   0.03689   0.02790  -0.0596   0.0380   1.0000
  11.000   1.2933   0.03922   0.03033  -0.0579   0.0351   1.0000
  11.250   1.2913   0.04184   0.03308  -0.0563   0.0332   1.0000
  11.500   1.2870   0.04482   0.03621  -0.0549   0.0318   1.0000
  11.750   1.2855   0.04765   0.03919  -0.0538   0.0311   1.0000
  12.000   1.2829   0.05073   0.04242  -0.0529   0.0304   1.0000
  12.250   1.2789   0.05406   0.04589  -0.0522   0.0297   1.0000
  12.500   1.2738   0.05759   0.04955  -0.0516   0.0290   1.0000
  12.750   1.2683   0.06126   0.05334  -0.0512   0.0283   1.0000
  13.000   1.2625   0.06503   0.05721  -0.0509   0.0277   1.0000
  13.250   1.2563   0.06888   0.06115  -0.0506   0.0270   1.0000
  13.500   1.2498   0.07275   0.06508  -0.0504   0.0264   1.0000
  13.750   1.2447   0.07639   0.06877  -0.0500   0.0259   1.0000
  14.000   1.2425   0.07946   0.07189  -0.0492   0.0255   1.0000
  14.250   1.2457   0.08143   0.07383  -0.0477   0.0250   1.0000
  14.500   1.2535   0.08322   0.07568  -0.0467   0.0248   1.0000
  14.750   1.2637   0.08461   0.07713  -0.0455   0.0245   1.0000
  15.000   1.2767   0.08556   0.07812  -0.0440   0.0243   1.0000
  15.250   1.2913   0.08636   0.07898  -0.0425   0.0241   1.0000
  15.500   1.3036   0.08762   0.08033  -0.0412   0.0236   1.0000
  15.750   1.3144   0.08918   0.08202  -0.0403   0.0231   1.0000
  16.000   1.3250   0.09081   0.08376  -0.0393   0.0226   1.0000
  16.250   1.3375   0.09228   0.08537  -0.0380   0.0226   1.0000
  16.500   1.3488   0.09409   0.08735  -0.0368   0.0227   1.0000
  16.750   1.3574   0.09642   0.08987  -0.0359   0.0230   1.0000
  17.000   1.3632   0.09925   0.09291  -0.0352   0.0234   1.0000
  17.250   1.3676   0.10244   0.09631  -0.0346   0.0239   1.0000
  17.500   1.4054   0.10333   0.09729  -0.0316   0.0254   1.0000
  17.750   1.3894   0.10760   0.10183  -0.0333   0.0259   1.0000
  18.000   1.3498   0.11613   0.11088  -0.0372   0.0271   1.0000
  18.250   1.3245   0.12429   0.11944  -0.0401   0.0292   1.0000
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