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GOE 417 AIRFOIL (goe417-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 417 AIRFOIL (goe417-il)
Reynolds number: 200,000
Max Cl/Cd: 82.8 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe417-il-200000.txt
Download as CSV file: xf-goe417-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3069   0.09734   0.09420  -0.0152   1.0000   0.0242
  -7.000  -0.3186   0.09647   0.09340  -0.0122   1.0000   0.0243
  -6.750  -0.3275   0.09526   0.09225  -0.0101   1.0000   0.0246
  -6.500  -0.3321   0.09368   0.09072  -0.0092   1.0000   0.0249
  -6.250  -0.3343   0.09208   0.08916  -0.0091   1.0000   0.0253
  -6.000  -0.2985   0.08891   0.08596  -0.0211   0.9952   0.0260
  -5.750  -0.2536   0.08506   0.08200  -0.0348   0.9890   0.0262
  -5.500  -0.2191   0.07988   0.07678  -0.0427   0.9848   0.0264
  -5.250  -0.2105   0.07471   0.07166  -0.0406   0.9816   0.0269
  -5.000  -0.1895   0.07091   0.06785  -0.0430   0.9761   0.0277
  -4.750  -0.1558   0.06701   0.06390  -0.0491   0.9720   0.0290
  -4.500  -0.1188   0.06328   0.06011  -0.0560   0.9667   0.0315
  -4.250  -0.0448   0.06012   0.05663  -0.0720   0.9602   0.0337
  -4.000  -0.0114   0.05407   0.05055  -0.0774   0.9568   0.0345
  -3.750   0.0107   0.05066   0.04716  -0.0787   0.9492   0.0358
  -3.500   0.0555   0.04700   0.04339  -0.0848   0.9443   0.0384
  -3.250   0.1302   0.04238   0.03836  -0.0970   0.9414   0.0446
  -3.000   0.1519   0.03945   0.03547  -0.0977   0.9324   0.0465
  -2.750   0.1970   0.03656   0.03244  -0.1027   0.9291   0.0517
  -2.500   0.2653   0.01503   0.01096  -0.1074   0.9122   0.0635
  -2.250   0.2977   0.01324   0.00887  -0.1092   0.9031   0.0721
  -2.000   0.3298   0.01134   0.00694  -0.1109   0.8984   0.0790
  -1.750   0.3579   0.00994   0.00533  -0.1115   0.8890   0.0884
  -1.500   0.3915   0.00847   0.00368  -0.1130   0.8835   0.1023
  -1.250   0.4165   0.00758   0.00269  -0.1128   0.8725   0.1177
  -1.000   0.4436   0.00670   0.00170  -0.1129   0.8626   0.1339
  -0.750   0.4727   0.00587   0.00072  -0.1131   0.8534   0.1603
   0.250   0.6093   0.01496   0.00814  -0.1163   0.8305   0.0818
   0.500   0.6383   0.01398   0.00686  -0.1155   0.8158   0.0716
   0.750   0.6660   0.01347   0.00623  -0.1147   0.7994   0.0692
   1.000   0.6933   0.01279   0.00545  -0.1140   0.7819   0.0680
   1.250   0.7187   0.01234   0.00494  -0.1130   0.7601   0.0677
   1.500   0.7446   0.01208   0.00457  -0.1121   0.7373   0.0695
   1.750   0.7693   0.01175   0.00420  -0.1110   0.7113   0.0718
   2.000   0.7940   0.01160   0.00395  -0.1100   0.6830   0.0731
   2.250   0.8181   0.01162   0.00378  -0.1088   0.6519   0.0759
   2.500   0.8415   0.01177   0.00372  -0.1076   0.6189   0.0813
   2.750   0.8643   0.01190   0.00374  -0.1063   0.5844   0.1070
   3.000   0.8934   0.01079   0.00391  -0.1067   0.5481   1.0000
   3.250   0.9160   0.01114   0.00401  -0.1055   0.5169   1.0000
   3.500   0.9390   0.01149   0.00416  -0.1045   0.4909   1.0000
   3.750   0.9623   0.01185   0.00435  -0.1036   0.4688   1.0000
   4.000   0.9857   0.01222   0.00459  -0.1027   0.4499   1.0000
   4.250   1.0093   0.01259   0.00484  -0.1019   0.4336   1.0000
   4.500   1.0331   0.01296   0.00511  -0.1011   0.4193   1.0000
   4.750   1.0571   0.01332   0.00541  -0.1004   0.4062   1.0000
   5.000   1.0810   0.01369   0.00572  -0.0997   0.3940   1.0000
   5.250   1.1047   0.01408   0.00607  -0.0990   0.3825   1.0000
   5.500   1.1283   0.01450   0.00642  -0.0982   0.3715   1.0000
   5.750   1.1520   0.01483   0.00678  -0.0975   0.3599   1.0000
   6.000   1.1756   0.01521   0.00718  -0.0968   0.3488   1.0000
   6.250   1.1988   0.01563   0.00761  -0.0960   0.3379   1.0000
   6.500   1.2217   0.01608   0.00804  -0.0952   0.3271   1.0000
   6.750   1.2440   0.01646   0.00846  -0.0943   0.3141   1.0000
   7.000   1.2652   0.01683   0.00885  -0.0932   0.2992   1.0000
   7.250   1.2857   0.01715   0.00922  -0.0920   0.2820   1.0000
   7.500   1.3061   0.01743   0.00956  -0.0908   0.2629   1.0000
   7.750   1.3266   0.01780   0.00996  -0.0896   0.2461   1.0000
   8.000   1.3466   0.01822   0.01040  -0.0884   0.2299   1.0000
   8.250   1.3658   0.01868   0.01087  -0.0871   0.2106   1.0000
   8.500   1.3845   0.01922   0.01140  -0.0858   0.1900   1.0000
   8.750   1.4007   0.01996   0.01206  -0.0841   0.1630   1.0000
   9.000   1.4059   0.02178   0.01329  -0.0811   0.0712   1.0000
   9.250   1.4042   0.02421   0.01541  -0.0770   0.0405   1.0000
   9.500   1.4111   0.02559   0.01693  -0.0738   0.0349   1.0000
   9.750   1.4185   0.02683   0.01831  -0.0708   0.0320   1.0000
  10.000   1.4214   0.02833   0.01997  -0.0674   0.0299   1.0000
  10.250   1.4161   0.03038   0.02216  -0.0634   0.0283   1.0000
  10.500   1.4192   0.03194   0.02385  -0.0606   0.0274   1.0000
  10.750   1.4218   0.03361   0.02566  -0.0580   0.0259   1.0000
  11.000   1.4216   0.03560   0.02777  -0.0555   0.0250   1.0000
  11.250   1.4208   0.03780   0.03008  -0.0532   0.0244   1.0000
  11.500   1.4201   0.04015   0.03253  -0.0511   0.0238   1.0000
  11.750   1.4199   0.04264   0.03511  -0.0494   0.0232   1.0000
  12.000   1.4208   0.04521   0.03777  -0.0478   0.0228   1.0000
  12.250   1.4235   0.04785   0.04050  -0.0464   0.0223   1.0000
  12.500   1.4301   0.05044   0.04316  -0.0450   0.0220   1.0000
  12.750   1.4410   0.05331   0.04613  -0.0436   0.0214   1.0000
  13.000   1.4517   0.05705   0.05005  -0.0424   0.0208   1.0000
  13.250   1.4486   0.05985   0.05308  -0.0416   0.0204   1.0000
  13.500   1.4474   0.06312   0.05658  -0.0409   0.0202   1.0000
  13.750   1.4465   0.06688   0.06057  -0.0404   0.0202   1.0000
  14.000   1.4421   0.07101   0.06494  -0.0402   0.0202   1.0000
  14.250   1.4349   0.07557   0.06974  -0.0403   0.0202   1.0000
  14.500   1.4249   0.08053   0.07494  -0.0410   0.0203   1.0000
  14.750   1.4131   0.08595   0.08059  -0.0421   0.0204   1.0000
  15.000   1.4008   0.09196   0.08681  -0.0436   0.0207   1.0000
  15.250   1.3930   0.09781   0.09289  -0.0449   0.0210   1.0000
  15.500   1.3811   0.10289   0.09815  -0.0474   0.0211   1.0000
  15.750   1.3682   0.10844   0.10389  -0.0505   0.0213   1.0000
  16.000   1.3538   0.11464   0.11029  -0.0544   0.0215   1.0000
  16.250   1.3373   0.12175   0.11761  -0.0591   0.0217   1.0000
  16.500   1.3172   0.13028   0.12637  -0.0651   0.0221   1.0000
  16.750   1.2927   0.14062   0.13695  -0.0726   0.0226   1.0000
  17.000   1.2631   0.15314   0.14970  -0.0819   0.0230   1.0000
  17.250   1.2275   0.16900   0.16577  -0.0935   0.0236   1.0000
  17.500   1.1793   0.19272   0.18954  -0.1088   0.0257   1.0000
  17.750   1.1705   0.20233   0.19913  -0.1139   0.0274   1.0000
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