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GOE 436 AIRFOIL (goe436-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 436 AIRFOIL (goe436-il)
Reynolds number: 500,000
Max Cl/Cd: 96.72 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe436-il-500000.txt
Download as CSV file: xf-goe436-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 436 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3183   0.08145   0.07932  -0.0409   1.0000   0.0409
  -9.250  -0.3261   0.07781   0.07572  -0.0386   1.0000   0.0414
  -9.000  -0.3202   0.07599   0.07393  -0.0374   0.9994   0.0417
  -8.750  -0.3000   0.07325   0.07117  -0.0393   0.9976   0.0425
  -8.500  -0.2836   0.06968   0.06760  -0.0425   0.9951   0.0437
  -8.250  -0.2763   0.06454   0.06246  -0.0473   0.9916   0.0456
  -8.000  -0.4074   0.05047   0.04794  -0.0727   0.9831   0.0416
  -7.750  -0.4303   0.02866   0.02469  -0.0814   0.9710   0.0412
  -7.500  -0.4028   0.02753   0.02355  -0.0824   0.9665   0.0420
  -7.250  -0.3239   0.04338   0.04059  -0.0820   0.9710   0.0465
  -7.000  -0.3303   0.02790   0.02404  -0.0861   0.9601   0.0438
  -6.750  -0.3013   0.02446   0.02018  -0.0880   0.9568   0.0454
  -6.500  -0.2812   0.02156   0.01682  -0.0874   0.9487   0.0467
  -6.250  -0.2518   0.02006   0.01497  -0.0880   0.9434   0.0477
  -6.000  -0.2278   0.01787   0.01251  -0.0879   0.9365   0.0491
  -5.750  -0.2002   0.01711   0.01169  -0.0880   0.9289   0.0500
  -5.500  -0.1719   0.01644   0.01094  -0.0881   0.9214   0.0509
  -5.250  -0.1448   0.01580   0.01020  -0.0878   0.9127   0.0519
  -5.000  -0.1183   0.01514   0.00942  -0.0874   0.9031   0.0531
  -4.750  -0.0900   0.01458   0.00872  -0.0873   0.8943   0.0545
  -4.500  -0.0643   0.01408   0.00809  -0.0866   0.8837   0.0556
  -4.250  -0.0369   0.01374   0.00762  -0.0863   0.8743   0.0563
  -4.000  -0.0116   0.01253   0.00629  -0.0857   0.8645   0.0578
  -3.750   0.0143   0.01205   0.00579  -0.0852   0.8545   0.0592
  -3.500   0.0412   0.01177   0.00545  -0.0849   0.8450   0.0607
  -3.250   0.0672   0.01152   0.00515  -0.0843   0.8339   0.0624
  -3.000   0.0934   0.01123   0.00480  -0.0837   0.8231   0.0639
  -2.750   0.1197   0.01098   0.00448  -0.0831   0.8122   0.0653
  -2.500   0.1458   0.01082   0.00426  -0.0825   0.8005   0.0664
  -2.250   0.1700   0.01022   0.00363  -0.0816   0.7887   0.0690
  -2.000   0.1954   0.01000   0.00339  -0.0810   0.7758   0.0713
  -1.750   0.2209   0.00984   0.00319  -0.0803   0.7612   0.0737
  -1.500   0.2461   0.00969   0.00299  -0.0795   0.7447   0.0759
  -1.250   0.2714   0.00959   0.00281  -0.0787   0.7259   0.0779
  -1.000   0.2955   0.00936   0.00252  -0.0778   0.7053   0.0814
  -0.750   0.3199   0.00927   0.00235  -0.0769   0.6836   0.0855
  -0.500   0.3444   0.00925   0.00224  -0.0760   0.6609   0.0896
  -0.250   0.3685   0.00925   0.00212  -0.0750   0.6393   0.0942
   0.000   0.3927   0.00922   0.00205  -0.0741   0.6181   0.1030
   0.250   0.4170   0.00919   0.00200  -0.0733   0.5966   0.1194
   0.500   0.4389   0.00888   0.00198  -0.0722   0.5745   0.2375
   0.750   0.4502   0.00772   0.00205  -0.0692   0.5521   0.6646
   1.000   0.5111   0.00737   0.00230  -0.0757   0.5126   0.9682
   1.250   0.5710   0.00773   0.00239  -0.0826   0.4759   0.9955
   1.500   0.6077   0.00795   0.00245  -0.0846   0.4541   1.0000
   1.750   0.6289   0.00814   0.00253  -0.0832   0.4405   1.0000
   2.000   0.6503   0.00834   0.00262  -0.0819   0.4295   1.0000
   2.250   0.6729   0.00849   0.00271  -0.0807   0.4203   1.0000
   2.500   0.6950   0.00868   0.00282  -0.0795   0.4124   1.0000
   2.750   0.7180   0.00882   0.00293  -0.0785   0.4048   1.0000
   3.000   0.7401   0.00903   0.00305  -0.0773   0.3966   1.0000
   3.250   0.7636   0.00916   0.00315  -0.0763   0.3887   1.0000
   3.500   0.7858   0.00938   0.00329  -0.0751   0.3818   1.0000
   3.750   0.8098   0.00948   0.00341  -0.0743   0.3752   1.0000
   4.000   0.8327   0.00966   0.00353  -0.0732   0.3684   1.0000
   4.250   0.8561   0.00982   0.00367  -0.0723   0.3622   1.0000
   4.500   0.8797   0.00995   0.00379  -0.0714   0.3554   1.0000
   4.750   0.9023   0.01016   0.00395  -0.0703   0.3487   1.0000
   5.000   0.9264   0.01027   0.00408  -0.0695   0.3427   1.0000
   5.250   0.9496   0.01044   0.00424  -0.0685   0.3374   1.0000
   5.500   0.9726   0.01064   0.00442  -0.0676   0.3324   1.0000
   5.750   0.9967   0.01076   0.00458  -0.0668   0.3271   1.0000
   6.000   1.0198   0.01095   0.00475  -0.0658   0.3215   1.0000
   6.250   1.0429   0.01114   0.00495  -0.0649   0.3161   1.0000
   6.500   1.0668   0.01128   0.00513  -0.0641   0.3104   1.0000
   6.750   1.0892   0.01149   0.00531  -0.0631   0.3038   1.0000
   7.000   1.1129   0.01164   0.00551  -0.0623   0.2967   1.0000
   7.250   1.1354   0.01185   0.00571  -0.0613   0.2895   1.0000
   7.500   1.1585   0.01203   0.00592  -0.0604   0.2827   1.0000
   7.750   1.1807   0.01224   0.00614  -0.0594   0.2743   1.0000
   8.000   1.2032   0.01244   0.00637  -0.0584   0.2647   1.0000
   8.250   1.2245   0.01270   0.00661  -0.0573   0.2519   1.0000
   8.500   1.2446   0.01302   0.00688  -0.0560   0.2340   1.0000
   8.750   1.2622   0.01349   0.00723  -0.0543   0.2092   1.0000
   9.000   1.2751   0.01424   0.00777  -0.0519   0.1731   1.0000
   9.250   1.2858   0.01510   0.00843  -0.0492   0.1420   1.0000
   9.500   1.2950   0.01592   0.00911  -0.0462   0.1179   1.0000
   9.750   1.3045   0.01670   0.00978  -0.0433   0.0950   1.0000
  10.000   1.3116   0.01762   0.01055  -0.0401   0.0739   1.0000
  10.250   1.3224   0.01835   0.01125  -0.0376   0.0672   1.0000
  10.500   1.3329   0.01911   0.01201  -0.0351   0.0632   1.0000
  10.750   1.3430   0.01990   0.01283  -0.0327   0.0600   1.0000
  11.000   1.3559   0.02054   0.01355  -0.0307   0.0582   1.0000
  11.250   1.3663   0.02134   0.01443  -0.0285   0.0559   1.0000
  11.500   1.3737   0.02234   0.01548  -0.0261   0.0536   1.0000
  11.750   1.3759   0.02370   0.01688  -0.0233   0.0508   1.0000
  12.000   1.3900   0.02439   0.01766  -0.0220   0.0491   1.0000
  12.250   1.4007   0.02531   0.01866  -0.0204   0.0464   1.0000
  12.500   1.4054   0.02668   0.02007  -0.0185   0.0436   1.0000
  12.750   1.4138   0.02787   0.02134  -0.0170   0.0407   1.0000
  13.000   1.4241   0.02897   0.02247  -0.0158   0.0369   1.0000
  13.250   1.4311   0.03037   0.02391  -0.0145   0.0328   1.0000
  13.500   1.4344   0.03215   0.02569  -0.0132   0.0296   1.0000
  13.750   1.4391   0.03389   0.02749  -0.0121   0.0266   1.0000
  14.000   1.4398   0.03609   0.02973  -0.0111   0.0250   1.0000
  14.250   1.4378   0.03868   0.03241  -0.0104   0.0236   1.0000
  14.500   1.4374   0.04126   0.03508  -0.0099   0.0225   1.0000
  14.750   1.4342   0.04429   0.03820  -0.0097   0.0217   1.0000
  15.000   1.4270   0.04793   0.04192  -0.0099   0.0208   1.0000
  15.250   1.4165   0.05217   0.04626  -0.0104   0.0203   1.0000
  15.500   1.4080   0.05631   0.05052  -0.0111   0.0199   1.0000
  15.750   1.4006   0.06046   0.05479  -0.0120   0.0195   1.0000
  16.000   1.3934   0.06471   0.05915  -0.0130   0.0191   1.0000
  16.250   1.3844   0.06928   0.06384  -0.0143   0.0189   1.0000
  16.500   1.3749   0.07402   0.06868  -0.0156   0.0185   1.0000
  16.750   1.3658   0.07878   0.07354  -0.0171   0.0181   1.0000
  17.000   1.3565   0.08359   0.07845  -0.0186   0.0178   1.0000
  17.250   1.3470   0.08848   0.08342  -0.0202   0.0175   1.0000
  17.500   1.3352   0.09377   0.08878  -0.0221   0.0172   1.0000
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