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GOE 614 AIRFOIL (goe614-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 614 AIRFOIL (goe614-il)
Reynolds number: 200,000
Max Cl/Cd: 59.11 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe614-il-200000-n5.txt
Download as CSV file: xf-goe614-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 614 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.3776   0.06537   0.06060  -0.1195   0.9593   0.0329
 -12.750  -0.4094   0.05561   0.05049  -0.1303   0.9508   0.0327
 -12.500  -0.4170   0.04972   0.04436  -0.1377   0.9428   0.0327
 -12.250  -0.4205   0.04526   0.03968  -0.1431   0.9328   0.0327
 -12.000  -0.4102   0.04173   0.03600  -0.1484   0.9258   0.0329
 -11.750  -0.4052   0.03906   0.03317  -0.1513   0.9149   0.0331
 -11.500  -0.3892   0.03661   0.03053  -0.1546   0.9083   0.0333
 -11.250  -0.3848   0.03502   0.02881  -0.1538   0.8965   0.0335
 -11.000  -0.3631   0.03316   0.02678  -0.1557   0.8902   0.0339
 -10.750  -0.3529   0.03187   0.02535  -0.1548   0.8791   0.0341
 -10.250  -0.3150   0.02924   0.02241  -0.1551   0.8617   0.0345
  -9.750  -0.2743   0.02708   0.01998  -0.1547   0.8440   0.0348
  -9.250  -0.2331   0.02527   0.01792  -0.1538   0.8261   0.0353
  -9.000  -0.2085   0.02441   0.01693  -0.1539   0.8180   0.0356
  -8.750  -0.1918   0.02374   0.01618  -0.1523   0.8078   0.0357
  -8.500  -0.1680   0.02302   0.01533  -0.1521   0.7995   0.0360
  -8.250  -0.1507   0.02244   0.01468  -0.1505   0.7894   0.0362
  -8.000  -0.1276   0.02184   0.01395  -0.1500   0.7809   0.0365
  -7.750  -0.1095   0.02134   0.01338  -0.1484   0.7709   0.0368
  -7.500  -0.0886   0.02066   0.01266  -0.1476   0.7622   0.0372
  -7.250  -0.0716   0.02010   0.01209  -0.1459   0.7521   0.0377
  -7.000  -0.0497   0.01958   0.01148  -0.1451   0.7430   0.0383
  -6.750  -0.0314   0.01913   0.01099  -0.1435   0.7327   0.0388
  -6.500  -0.0091   0.01871   0.01045  -0.1427   0.7239   0.0393
  -6.250   0.0107   0.01832   0.01000  -0.1412   0.7136   0.0398
  -6.000   0.0330   0.01797   0.00953  -0.1403   0.7042   0.0402
  -5.750   0.0540   0.01765   0.00911  -0.1390   0.6936   0.0407
  -5.500   0.0764   0.01735   0.00870  -0.1380   0.6840   0.0413
  -5.250   0.0983   0.01708   0.00832  -0.1369   0.6739   0.0418
  -5.000   0.1206   0.01677   0.00791  -0.1359   0.6648   0.0427
  -4.750   0.1427   0.01650   0.00755  -0.1348   0.6550   0.0438
  -4.500   0.1655   0.01629   0.00724  -0.1337   0.6456   0.0450
  -4.250   0.1881   0.01610   0.00694  -0.1327   0.6358   0.0467
  -4.000   0.2106   0.01587   0.00667  -0.1316   0.6270   0.0496
  -3.750   0.2318   0.01550   0.00639  -0.1305   0.6181   0.0650
  -3.500   0.2547   0.01531   0.00623  -0.1295   0.6103   0.1021
  -3.250   0.2776   0.01518   0.00608  -0.1285   0.6019   0.1148
  -3.000   0.3007   0.01504   0.00592  -0.1276   0.5944   0.1290
  -2.750   0.3231   0.01491   0.00585  -0.1266   0.5863   0.1456
  -2.500   0.3462   0.01484   0.00581  -0.1257   0.5787   0.1714
  -2.250   0.3695   0.01481   0.00579  -0.1248   0.5717   0.1924
  -2.000   0.3931   0.01482   0.00576  -0.1239   0.5647   0.2066
  -1.500   0.4403   0.01485   0.00574  -0.1222   0.5524   0.2351
  -1.250   0.4635   0.01487   0.00574  -0.1212   0.5460   0.2479
  -0.750   0.5100   0.01493   0.00578  -0.1194   0.5344   0.2747
  -0.500   0.5328   0.01496   0.00582  -0.1184   0.5287   0.2905
  -0.250   0.5563   0.01501   0.00586  -0.1176   0.5238   0.3069
   0.250   0.6023   0.01510   0.00600  -0.1157   0.5141   0.3390
   0.500   0.6247   0.01515   0.00607  -0.1147   0.5091   0.3550
   0.750   0.6473   0.01524   0.00612  -0.1137   0.5044   0.3721
   1.000   0.6680   0.01528   0.00622  -0.1123   0.4991   0.3905
   1.250   0.6883   0.01533   0.00632  -0.1108   0.4939   0.4117
   1.500   0.7091   0.01540   0.00641  -0.1095   0.4891   0.4341
   1.750   0.7301   0.01550   0.00650  -0.1082   0.4841   0.4586
   2.000   0.7486   0.01555   0.00665  -0.1064   0.4786   0.4844
   2.250   0.7673   0.01563   0.00679  -0.1047   0.4729   0.5111
   2.500   0.7872   0.01574   0.00692  -0.1032   0.4681   0.5420
   2.750   0.8059   0.01581   0.00710  -0.1015   0.4631   0.5763
   3.000   0.8234   0.01587   0.00729  -0.0996   0.4572   0.6143
   3.250   0.8409   0.01589   0.00747  -0.0976   0.4514   0.6747
   3.750   0.9328   0.01606   0.00808  -0.1056   0.4378   1.0000
   4.000   0.9512   0.01631   0.00824  -0.1040   0.4332   1.0000
   4.250   0.9701   0.01656   0.00843  -0.1025   0.4290   1.0000
   4.500   0.9892   0.01680   0.00866  -0.1011   0.4247   1.0000
   4.750   1.0072   0.01707   0.00889  -0.0995   0.4198   1.0000
   5.000   1.0253   0.01735   0.00912  -0.0980   0.4156   1.0000
   5.250   1.0434   0.01766   0.00937  -0.0965   0.4113   1.0000
   5.500   1.0611   0.01795   0.00968  -0.0949   0.4064   1.0000
   5.750   1.0783   0.01827   0.00999  -0.0933   0.4016   1.0000
   6.000   1.0956   0.01862   0.01029  -0.0918   0.3975   1.0000
   6.250   1.1133   0.01898   0.01062  -0.0904   0.3936   1.0000
   6.500   1.1308   0.01934   0.01101  -0.0890   0.3893   1.0000
   6.750   1.1473   0.01973   0.01140  -0.0874   0.3847   1.0000
   7.000   1.1631   0.02016   0.01181  -0.0858   0.3803   1.0000
   7.250   1.1794   0.02060   0.01223  -0.0843   0.3763   1.0000
   7.500   1.1957   0.02105   0.01272  -0.0829   0.3716   1.0000
   7.750   1.2105   0.02155   0.01324  -0.0813   0.3668   1.0000
   8.000   1.2246   0.02210   0.01376  -0.0796   0.3623   1.0000
   8.250   1.2396   0.02265   0.01434  -0.0782   0.3578   1.0000
   8.500   1.2533   0.02325   0.01497  -0.0766   0.3522   1.0000
   8.750   1.2658   0.02393   0.01564  -0.0749   0.3471   1.0000
   9.000   1.2790   0.02461   0.01634  -0.0734   0.3425   1.0000
   9.250   1.2915   0.02535   0.01712  -0.0719   0.3366   1.0000
   9.500   1.3030   0.02615   0.01793  -0.0703   0.3317   1.0000
   9.750   1.3145   0.02699   0.01879  -0.0688   0.3270   1.0000
  10.000   1.3263   0.02786   0.01970  -0.0674   0.3216   1.0000
  10.250   1.3356   0.02887   0.02073  -0.0659   0.3158   1.0000
  10.500   1.3444   0.02996   0.02183  -0.0643   0.3101   1.0000
  10.750   1.3540   0.03105   0.02297  -0.0630   0.3044   1.0000
  11.000   1.3619   0.03227   0.02420  -0.0615   0.2993   1.0000
  11.250   1.3703   0.03352   0.02548  -0.0602   0.2944   1.0000
  11.500   1.3791   0.03478   0.02679  -0.0590   0.2896   1.0000
  11.750   1.3854   0.03624   0.02828  -0.0577   0.2846   1.0000
  12.000   1.3917   0.03776   0.02982  -0.0565   0.2803   1.0000
  12.250   1.4001   0.03917   0.03130  -0.0555   0.2763   1.0000
  12.500   1.4052   0.04087   0.03304  -0.0544   0.2714   1.0000
  12.750   1.4100   0.04263   0.03483  -0.0534   0.2674   1.0000
  13.000   1.4162   0.04432   0.03658  -0.0525   0.2639   1.0000
  13.250   1.4222   0.04609   0.03842  -0.0517   0.2601   1.0000
  13.500   1.4271   0.04798   0.04038  -0.0509   0.2564   1.0000
  13.750   1.4309   0.05000   0.04244  -0.0501   0.2528   1.0000
  14.000   1.4337   0.05211   0.04458  -0.0494   0.2493   1.0000
  14.250   1.4375   0.05426   0.04683  -0.0488   0.2451   1.0000
  14.500   1.4382   0.05674   0.04937  -0.0482   0.2401   1.0000
  14.750   1.4379   0.05933   0.05198  -0.0477   0.2356   1.0000
  15.000   1.4372   0.06203   0.05474  -0.0473   0.2305   1.0000
  15.250   1.4362   0.06483   0.05762  -0.0469   0.2253   1.0000
  15.500   1.4326   0.06794   0.06076  -0.0466   0.2198   1.0000
  15.750   1.4302   0.07098   0.06386  -0.0464   0.2146   1.0000
  16.000   1.4294   0.07389   0.06686  -0.0463   0.2099   1.0000
  16.250   1.4242   0.07731   0.07033  -0.0463   0.2043   1.0000
  16.500   1.4224   0.08038   0.07347  -0.0463   0.2002   1.0000
  16.750   1.4169   0.08402   0.07720  -0.0465   0.1928   1.0000
  17.000   1.4100   0.08782   0.08104  -0.0467   0.1865   1.0000
  17.250   1.4052   0.09144   0.08477  -0.0471   0.1791   1.0000
  17.500   1.3980   0.09537   0.08876  -0.0475   0.1705   1.0000
  17.750   1.3863   0.09996   0.09335  -0.0482   0.1564   1.0000
  18.000   1.3700   0.10521   0.09857  -0.0490   0.1449   1.0000
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