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GOE 417 AIRFOIL (goe417-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 417 AIRFOIL (goe417-il)
Reynolds number: 1,000,000
Max Cl/Cd: 127.21 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe417-il-1000000.txt
Download as CSV file: xf-goe417-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 417 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.1786   0.08940   0.08792  -0.0397   0.9938   0.0097
  -8.750  -0.1687   0.08552   0.08404  -0.0422   0.9916   0.0097
  -8.500  -0.1593   0.08076   0.07929  -0.0440   0.9896   0.0098
  -8.250  -0.1460   0.07710   0.07563  -0.0464   0.9875   0.0100
  -8.000  -0.1315   0.07350   0.07202  -0.0493   0.9854   0.0102
  -7.750  -0.1167   0.06985   0.06837  -0.0525   0.9838   0.0106
  -7.500  -0.2025   0.08436   0.08282  -0.0453   0.9867   0.0101
  -7.250  -0.1801   0.08109   0.07954  -0.0503   0.9841   0.0107
  -7.000  -0.1590   0.07752   0.07597  -0.0553   0.9793   0.0109
  -6.750  -0.1326   0.07360   0.07204  -0.0619   0.9752   0.0123
  -6.500  -0.0956   0.06900   0.06741  -0.0725   0.9722   0.0126
  -6.250  -0.0608   0.06455   0.06292  -0.0821   0.9666   0.0127
  -6.000  -0.0329   0.06069   0.05902  -0.0880   0.9593   0.0127
  -5.750  -0.0144   0.05651   0.05482  -0.0909   0.9517   0.0130
  -5.500   0.0069   0.05396   0.05223  -0.0933   0.9426   0.0132
  -5.250   0.0271   0.05163   0.04985  -0.0954   0.9317   0.0137
  -5.000   0.0499   0.04905   0.04721  -0.0981   0.9206   0.0149
  -4.750   0.0868   0.04509   0.04310  -0.1045   0.9096   0.0162
  -4.500   0.1134   0.04177   0.03968  -0.1073   0.8998   0.0162
  -4.250   0.1406   0.03850   0.03630  -0.1097   0.8903   0.0163
  -4.000   0.1590   0.03541   0.03313  -0.1109   0.8812   0.0168
  -3.750   0.1828   0.03374   0.03138  -0.1118   0.8710   0.0174
  -3.500   0.2099   0.03167   0.02921  -0.1131   0.8615   0.0188
  -3.250   0.2487   0.02841   0.02570  -0.1153   0.8527   0.0205
  -3.000   0.2781   0.02531   0.02238  -0.1163   0.8431   0.0206
  -2.750   0.3013   0.02176   0.01865  -0.1173   0.8332   0.0214
  -2.500   0.3263   0.02071   0.01749  -0.1174   0.8222   0.0221
  -2.250   0.3527   0.01939   0.01601  -0.1174   0.8105   0.0234
  -2.000   0.3837   0.01815   0.01448  -0.1168   0.7982   0.0261
  -1.750   0.4110   0.01660   0.01264  -0.1165   0.7853   0.0262
   1.250   0.7139   0.00898   0.00256  -0.1096   0.4775   0.0356
   1.500   0.7386   0.00915   0.00256  -0.1089   0.4401   0.0333
   1.750   0.7632   0.00907   0.00234  -0.1082   0.4105   0.0332
   2.000   0.7886   0.00915   0.00231  -0.1077   0.3889   0.0340
   2.250   0.8139   0.00907   0.00216  -0.1072   0.3725   0.0343
   2.500   0.8396   0.00907   0.00209  -0.1068   0.3591   0.0347
   2.750   0.8655   0.00908   0.00206  -0.1063   0.3481   0.0352
   3.000   0.8915   0.00913   0.00208  -0.1059   0.3386   0.0364
   3.250   0.9174   0.00922   0.00212  -0.1055   0.3297   0.0369
   3.500   0.9436   0.00929   0.00217  -0.1052   0.3224   0.0382
   3.750   0.9695   0.00939   0.00224  -0.1048   0.3148   0.0413
   4.000   0.9956   0.00947   0.00234  -0.1044   0.3084   0.0538
   4.250   1.0247   0.00818   0.00274  -0.1054   0.3012   1.0000
   4.500   1.0505   0.00833   0.00286  -0.1050   0.2949   1.0000
   4.750   1.0761   0.00849   0.00299  -0.1045   0.2876   1.0000
   5.000   1.1016   0.00866   0.00313  -0.1041   0.2787   1.0000
   5.250   1.1265   0.00888   0.00328  -0.1036   0.2633   1.0000
   5.500   1.1512   0.00912   0.00345  -0.1031   0.2473   1.0000
   5.750   1.1757   0.00938   0.00364  -0.1025   0.2315   1.0000
   6.000   1.1992   0.00972   0.00388  -0.1018   0.2098   1.0000
   6.250   1.2216   0.01017   0.00417  -0.1010   0.1837   1.0000
   6.500   1.2440   0.01062   0.00450  -0.1001   0.1616   1.0000
   6.750   1.2668   0.01102   0.00482  -0.0994   0.1467   1.0000
   7.000   1.2895   0.01141   0.00516  -0.0986   0.1333   1.0000
   7.250   1.3123   0.01179   0.00548  -0.0978   0.1212   1.0000
   7.500   1.3341   0.01227   0.00587  -0.0969   0.1044   1.0000
   7.750   1.3450   0.01384   0.00699  -0.0943   0.0308   1.0000
   8.000   1.3630   0.01468   0.00773  -0.0928   0.0157   1.0000
   8.250   1.3846   0.01513   0.00824  -0.0918   0.0141   1.0000
   8.500   1.4051   0.01565   0.00881  -0.0906   0.0128   1.0000
   8.750   1.4240   0.01632   0.00954  -0.0892   0.0115   1.0000
   9.000   1.4413   0.01711   0.01044  -0.0875   0.0106   1.0000
   9.250   1.4605   0.01766   0.01106  -0.0862   0.0102   1.0000
   9.500   1.4787   0.01825   0.01171  -0.0847   0.0096   1.0000
   9.750   1.4961   0.01886   0.01238  -0.0832   0.0090   1.0000
  10.000   1.5120   0.01953   0.01311  -0.0814   0.0085   1.0000
  10.250   1.5226   0.02041   0.01405  -0.0787   0.0079   1.0000
  10.500   1.5245   0.02166   0.01543  -0.0747   0.0076   1.0000
  10.750   1.5252   0.02299   0.01689  -0.0706   0.0073   1.0000
  11.000   1.5350   0.02381   0.01779  -0.0682   0.0072   1.0000
  11.250   1.5425   0.02481   0.01888  -0.0655   0.0070   1.0000
  11.500   1.5483   0.02595   0.02011  -0.0628   0.0068   1.0000
  11.750   1.5539   0.02716   0.02140  -0.0603   0.0066   1.0000
  12.000   1.5576   0.02856   0.02290  -0.0579   0.0064   1.0000
  12.250   1.5562   0.03044   0.02489  -0.0551   0.0063   1.0000
  12.500   1.5595   0.03206   0.02660  -0.0531   0.0061   1.0000
  12.750   1.5594   0.03408   0.02872  -0.0512   0.0060   1.0000
  13.000   1.5602   0.03614   0.03087  -0.0496   0.0058   1.0000
  13.250   1.5610   0.03834   0.03316  -0.0483   0.0057   1.0000
  13.500   1.5588   0.04098   0.03589  -0.0473   0.0055   1.0000
  13.750   1.5558   0.04387   0.03888  -0.0466   0.0054   1.0000
  14.000   1.5493   0.04740   0.04251  -0.0463   0.0053   1.0000
  14.250   1.5366   0.05195   0.04718  -0.0463   0.0052   1.0000
  14.500   1.5148   0.05799   0.05338  -0.0468   0.0050   1.0000
  14.750   1.5037   0.06287   0.05840  -0.0476   0.0049   1.0000
  15.000   1.4977   0.06723   0.06288  -0.0486   0.0049   1.0000
  15.250   1.4942   0.07148   0.06725  -0.0500   0.0049   1.0000
  15.500   1.4886   0.07613   0.07202  -0.0515   0.0048   1.0000
  15.750   1.4827   0.08101   0.07702  -0.0533   0.0047   1.0000
  16.000   1.4755   0.08619   0.08232  -0.0553   0.0047   1.0000
  16.250   1.4681   0.09153   0.08779  -0.0575   0.0046   1.0000
  16.500   1.4602   0.09703   0.09341  -0.0598   0.0046   1.0000
  16.750   1.4524   0.10269   0.09919  -0.0623   0.0046   1.0000
  17.000   1.4438   0.10856   0.10519  -0.0650   0.0045   1.0000
  17.250   1.4358   0.11442   0.11117  -0.0678   0.0045   1.0000
  17.500   1.4266   0.12058   0.11746  -0.0708   0.0045   1.0000
  17.750   1.4183   0.12673   0.12372  -0.0740   0.0044   1.0000
  18.000   1.4088   0.13316   0.13029  -0.0775   0.0044   1.0000
  18.250   1.3998   0.13964   0.13689  -0.0811   0.0044   1.0000
  18.500   1.3900   0.14640   0.14377  -0.0850   0.0044   1.0000
  18.750   1.3801   0.15333   0.15083  -0.0892   0.0044   1.0000
  19.000   1.3704   0.16036   0.15799  -0.0936   0.0043   1.0000
  19.250   1.3599   0.16779   0.16554  -0.0983   0.0043   1.0000
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