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GOE 430 AIRFOIL (goe430-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 430 AIRFOIL (goe430-il)
Reynolds number: 50,000
Max Cl/Cd: 36.51 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe430-il-50000-n5.txt
Download as CSV file: xf-goe430-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 430 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3621   0.10851   0.10102  -0.0451   1.0000   0.1037
  -9.250  -0.3681   0.10609   0.09867  -0.0438   1.0000   0.1035
  -9.000  -0.3802   0.10350   0.09616  -0.0428   1.0000   0.1036
  -8.750  -0.3960   0.10083   0.09357  -0.0417   1.0000   0.1038
  -8.500  -0.3877   0.10003   0.09283  -0.0388   1.0000   0.1054
  -8.250  -0.3990   0.09797   0.09084  -0.0371   1.0000   0.1057
  -8.000  -0.4177   0.09554   0.08851  -0.0353   1.0000   0.1056
  -7.750  -0.4392   0.09249   0.08556  -0.0344   1.0000   0.1051
  -7.500  -0.4548   0.08720   0.08033  -0.0376   0.9984   0.1045
  -7.250  -0.4444   0.07930   0.07236  -0.0479   0.9906   0.1044
  -7.000  -0.4281   0.07081   0.06374  -0.0596   0.9831   0.1049
  -6.750  -0.4067   0.06640   0.05923  -0.0657   0.9759   0.1066
  -6.500  -0.3813   0.05972   0.05229  -0.0763   0.9693   0.1095
  -6.250  -0.3508   0.05058   0.04255  -0.0907   0.9622   0.1126
  -6.000  -0.3062   0.04327   0.03433  -0.1033   0.9580   0.1160
  -5.750  -0.2733   0.04057   0.03127  -0.1074   0.9516   0.1189
  -5.500  -0.2381   0.03946   0.03007  -0.1102   0.9460   0.1232
  -5.250  -0.1981   0.03733   0.02745  -0.1148   0.9410   0.1297
  -5.000  -0.1649   0.03586   0.02575  -0.1172   0.9341   0.1346
  -4.750  -0.1259   0.03472   0.02445  -0.1203   0.9291   0.1409
  -4.500  -0.0913   0.03352   0.02295  -0.1226   0.9223   0.1497
  -4.250  -0.0556   0.03275   0.02207  -0.1249   0.9155   0.1614
  -4.000  -0.0133   0.03197   0.02126  -0.1281   0.9108   0.1749
  -3.750   0.0156   0.03140   0.02067  -0.1287   0.9004   0.1869
  -3.500   0.0597   0.03087   0.02009  -0.1319   0.8944   0.2051
  -3.250   0.0886   0.03064   0.01983  -0.1324   0.8831   0.2213
  -3.000   0.1295   0.03041   0.01956  -0.1349   0.8761   0.2448
  -2.750   0.1592   0.03028   0.01943  -0.1354   0.8657   0.2629
  -2.500   0.1964   0.02991   0.01900  -0.1371   0.8587   0.2800
  -2.000   0.2622   0.02922   0.01821  -0.1389   0.8424   0.3115
  -1.500   0.3240   0.02871   0.01773  -0.1399   0.8251   0.3480
  -1.250   0.3539   0.02854   0.01760  -0.1402   0.8160   0.3699
  -1.000   0.3836   0.02843   0.01753  -0.1404   0.8072   0.3954
  -0.750   0.4148   0.02828   0.01745  -0.1407   0.7990   0.4221
  -0.500   0.4417   0.02830   0.01750  -0.1404   0.7892   0.4482
  -0.250   0.4747   0.02811   0.01734  -0.1408   0.7820   0.4788
   0.000   0.4992   0.02822   0.01752  -0.1401   0.7716   0.5059
   0.250   0.5323   0.02797   0.01733  -0.1403   0.7651   0.5365
   0.500   0.5549   0.02816   0.01760  -0.1393   0.7540   0.5665
   0.750   0.5872   0.02788   0.01742  -0.1391   0.7482   0.6055
   1.000   0.6078   0.02813   0.01776  -0.1377   0.7368   0.6411
   1.250   0.6396   0.02784   0.01751  -0.1376   0.7309   0.6808
   1.500   0.6602   0.02802   0.01778  -0.1363   0.7202   0.7132
   1.750   0.6879   0.02774   0.01759  -0.1356   0.7134   0.7477
   2.000   0.7078   0.02774   0.01774  -0.1338   0.7038   0.7871
   2.500   0.7566   0.02756   0.01771  -0.1320   0.6870   1.0000
   2.750   0.7894   0.02783   0.01785  -0.1331   0.6797   1.0000
   3.000   0.8184   0.02824   0.01818  -0.1336   0.6711   1.0000
   3.250   0.8502   0.02843   0.01828  -0.1342   0.6636   1.0000
   3.750   0.9056   0.02905   0.01879  -0.1340   0.6446   1.0000
   4.000   0.9371   0.02908   0.01877  -0.1342   0.6360   1.0000
   4.250   0.9603   0.02963   0.01931  -0.1336   0.6257   1.0000
   4.500   0.9939   0.02956   0.01919  -0.1339   0.6182   1.0000
   4.750   1.0135   0.03030   0.01998  -0.1329   0.6074   1.0000
   5.000   1.0491   0.03009   0.01972  -0.1333   0.6002   1.0000
   5.250   1.0655   0.03097   0.02067  -0.1319   0.5887   1.0000
   5.500   1.0915   0.03126   0.02100  -0.1313   0.5791   1.0000
   5.750   1.1183   0.03143   0.02118  -0.1307   0.5688   1.0000
   6.000   1.1360   0.03214   0.02197  -0.1292   0.5573   1.0000
   6.250   1.1645   0.03228   0.02215  -0.1289   0.5484   1.0000
   6.500   1.1834   0.03292   0.02289  -0.1275   0.5374   1.0000
   6.750   1.2017   0.03358   0.02365  -0.1261   0.5264   1.0000
   7.000   1.2286   0.03369   0.02380  -0.1254   0.5161   1.0000
   7.250   1.2476   0.03417   0.02438  -0.1238   0.5034   1.0000
   7.500   1.2631   0.03478   0.02508  -0.1218   0.4895   1.0000
   7.750   1.2796   0.03526   0.02563  -0.1199   0.4748   1.0000
   8.000   1.2954   0.03570   0.02612  -0.1178   0.4588   1.0000
   8.250   1.3085   0.03622   0.02669  -0.1153   0.4420   1.0000
   8.500   1.3200   0.03683   0.02732  -0.1127   0.4239   1.0000
   8.750   1.3298   0.03759   0.02809  -0.1100   0.4051   1.0000
   9.000   1.3377   0.03855   0.02905  -0.1074   0.3861   1.0000
   9.250   1.3397   0.04004   0.03064  -0.1046   0.3666   1.0000
   9.500   1.3427   0.04163   0.03232  -0.1022   0.3477   1.0000
   9.750   1.3478   0.04317   0.03394  -0.1000   0.3301   1.0000
  10.000   1.3542   0.04467   0.03545  -0.0980   0.3139   1.0000
  10.250   1.3609   0.04618   0.03695  -0.0961   0.2992   1.0000
  10.500   1.3678   0.04774   0.03847  -0.0942   0.2861   1.0000
  10.750   1.3752   0.04931   0.03997  -0.0925   0.2745   1.0000
  11.000   1.3831   0.05091   0.04150  -0.0908   0.2638   1.0000
  11.250   1.3895   0.05284   0.04349  -0.0892   0.2536   1.0000
  11.500   1.4006   0.05433   0.04492  -0.0877   0.2448   1.0000
  11.750   1.4091   0.05622   0.04691  -0.0863   0.2360   1.0000
  12.000   1.4229   0.05767   0.04836  -0.0850   0.2281   1.0000
  12.250   1.4319   0.05966   0.05051  -0.0837   0.2203   1.0000
  12.500   1.4524   0.06069   0.05155  -0.0825   0.2129   1.0000
  12.750   1.4532   0.06348   0.05460  -0.0813   0.2060   1.0000
  13.000   1.4700   0.06461   0.05563  -0.0801   0.1974   1.0000
  13.250   1.4570   0.06860   0.05997  -0.0790   0.1910   1.0000
  13.500   1.4593   0.07081   0.06219  -0.0780   0.1827   1.0000
  13.750   1.4457   0.07507   0.06672  -0.0775   0.1764   1.0000
  14.000   1.4366   0.07878   0.07057  -0.0771   0.1694   1.0000
  14.250   1.4278   0.08261   0.07453  -0.0771   0.1628   1.0000
  14.500   1.4129   0.08762   0.07979  -0.0777   0.1567   1.0000
  14.750   1.4079   0.09104   0.08323  -0.0780   0.1498   1.0000
  15.000   1.3892   0.09730   0.08981  -0.0797   0.1442   1.0000
  15.250   1.3873   0.10037   0.09285  -0.0803   0.1370   1.0000
  15.500   1.3653   0.10782   0.10065  -0.0831   0.1317   1.0000
  15.750   1.3626   0.11139   0.10424  -0.0843   0.1246   1.0000
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