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GOE 364 AIRFOIL (goe364-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 364 AIRFOIL (goe364-il)
Reynolds number: 200,000
Max Cl/Cd: 76.59 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe364-il-200000-n5.txt
Download as CSV file: xf-goe364-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 364 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.0990   0.09368   0.09026  -0.0613   0.9540   0.0262
  -8.500  -0.0834   0.08984   0.08640  -0.0691   0.9406   0.0272
  -8.250  -0.0684   0.08597   0.08251  -0.0758   0.9224   0.0273
  -8.000  -0.0471   0.08173   0.07824  -0.0789   0.9054   0.0275
  -7.750  -0.0219   0.07803   0.07448  -0.0819   0.8869   0.0281
  -7.500  -0.0005   0.07458   0.07094  -0.0861   0.8641   0.0287
  -7.250   0.0132   0.07165   0.06791  -0.0891   0.8418   0.0296
  -7.000   0.0236   0.06887   0.06502  -0.0923   0.8231   0.0312
  -6.750   0.0332   0.06524   0.06123  -0.1003   0.8055   0.0322
  -6.500   0.0444   0.06179   0.05770  -0.1023   0.7927   0.0326
  -6.250   0.0570   0.05956   0.05543  -0.1015   0.7821   0.0331
  -6.000   0.0709   0.05725   0.05304  -0.1021   0.7716   0.0338
  -5.750   0.0861   0.05476   0.05048  -0.1036   0.7619   0.0348
  -5.500   0.1037   0.05196   0.04755  -0.1059   0.7530   0.0363
  -5.250   0.1288   0.04718   0.04248  -0.1119   0.7441   0.0389
  -5.000   0.1430   0.04553   0.04081  -0.1109   0.7360   0.0398
  -4.750   0.1614   0.04362   0.03884  -0.1111   0.7273   0.0414
  -4.500   0.1935   0.04020   0.03488  -0.1145   0.7197   0.0459
  -4.250   0.2118   0.03707   0.03164  -0.1148   0.7121   0.0464
  -4.000   0.2295   0.03549   0.03008  -0.1143   0.7045   0.0476
  -3.750   0.2565   0.03011   0.02397  -0.1145   0.6984   0.0386
  -3.500   0.2777   0.02866   0.02251  -0.1142   0.6906   0.0378
  -3.250   0.3006   0.02666   0.02026  -0.1137   0.6838   0.0373
  -3.000   0.3250   0.02429   0.01740  -0.1129   0.6760   0.0381
  -2.750   0.3488   0.02270   0.01553  -0.1123   0.6688   0.0378
  -2.500   0.3730   0.02124   0.01381  -0.1115   0.6606   0.0376
  -2.250   0.3979   0.02000   0.01225  -0.1108   0.6530   0.0377
  -2.000   0.4236   0.01918   0.01107  -0.1100   0.6451   0.0385
  -1.750   0.4485   0.01810   0.00981  -0.1094   0.6374   0.0392
  -1.500   0.4741   0.01736   0.00888  -0.1087   0.6294   0.0392
  -1.250   0.4998   0.01672   0.00807  -0.1081   0.6209   0.0394
  -1.000   0.5254   0.01618   0.00741  -0.1074   0.6119   0.0396
  -0.750   0.5510   0.01572   0.00683  -0.1068   0.6032   0.0400
  -0.500   0.5764   0.01533   0.00638  -0.1061   0.5933   0.0406
  -0.250   0.6017   0.01505   0.00603  -0.1054   0.5839   0.0418
   0.000   0.6266   0.01480   0.00571  -0.1047   0.5729   0.0431
   0.250   0.6512   0.01456   0.00541  -0.1039   0.5610   0.0437
   0.500   0.6755   0.01436   0.00514  -0.1030   0.5491   0.0442
   1.000   0.7238   0.01412   0.00478  -0.1013   0.5255   0.0455
   1.250   0.7478   0.01404   0.00465  -0.1004   0.5137   0.0465
   1.500   0.7715   0.01401   0.00455  -0.0995   0.5028   0.0484
   1.750   0.7956   0.01403   0.00451  -0.0987   0.4925   0.0516
   2.000   0.8200   0.01408   0.00450  -0.0979   0.4837   0.0545
   2.250   0.8440   0.01414   0.00452  -0.0971   0.4752   0.0590
   2.500   0.8683   0.01418   0.00460  -0.0963   0.4678   0.0787
   3.000   0.9489   0.01295   0.00505  -0.1022   0.4522   1.0000
   3.250   0.9724   0.01317   0.00517  -0.1013   0.4451   1.0000
   3.500   0.9958   0.01341   0.00532  -0.1004   0.4385   1.0000
   3.750   1.0193   0.01362   0.00548  -0.0996   0.4312   1.0000
   4.000   1.0420   0.01389   0.00565  -0.0986   0.4244   1.0000
   4.250   1.0656   0.01410   0.00586  -0.0978   0.4178   1.0000
   4.500   1.0884   0.01436   0.00606  -0.0969   0.4112   1.0000
   4.750   1.1112   0.01462   0.00628  -0.0960   0.4050   1.0000
   5.000   1.1339   0.01485   0.00652  -0.0951   0.3978   1.0000
   5.250   1.1554   0.01515   0.00675  -0.0940   0.3908   1.0000
   5.500   1.1777   0.01538   0.00701  -0.0930   0.3828   1.0000
   5.750   1.1984   0.01568   0.00727  -0.0918   0.3750   1.0000
   6.000   1.2200   0.01593   0.00755  -0.0907   0.3666   1.0000
   6.250   1.2398   0.01625   0.00783  -0.0894   0.3585   1.0000
   6.500   1.2602   0.01652   0.00815  -0.0882   0.3488   1.0000
   6.750   1.2790   0.01685   0.00846  -0.0867   0.3391   1.0000
   7.000   1.2967   0.01720   0.00880  -0.0850   0.3287   1.0000
   7.250   1.3145   0.01756   0.00916  -0.0834   0.3181   1.0000
   7.500   1.3298   0.01796   0.00955  -0.0813   0.3079   1.0000
   8.000   1.3563   0.01888   0.01042  -0.0766   0.2870   1.0000
   8.250   1.3685   0.01943   0.01093  -0.0743   0.2771   1.0000
   8.500   1.3797   0.02005   0.01152  -0.0718   0.2681   1.0000
   8.750   1.3931   0.02063   0.01211  -0.0698   0.2601   1.0000
   9.000   1.4050   0.02129   0.01277  -0.0677   0.2538   1.0000
   9.250   1.4180   0.02194   0.01344  -0.0658   0.2481   1.0000
   9.500   1.4311   0.02261   0.01416  -0.0640   0.2427   1.0000
   9.750   1.4425   0.02338   0.01494  -0.0620   0.2381   1.0000
  10.000   1.4549   0.02414   0.01575  -0.0603   0.2341   1.0000
  10.250   1.4684   0.02487   0.01655  -0.0588   0.2295   1.0000
  10.500   1.4795   0.02574   0.01748  -0.0571   0.2250   1.0000
  10.750   1.4887   0.02675   0.01850  -0.0553   0.2208   1.0000
  11.000   1.5013   0.02760   0.01945  -0.0539   0.2167   1.0000
  11.250   1.5124   0.02856   0.02050  -0.0525   0.2121   1.0000
  11.500   1.5219   0.02966   0.02167  -0.0510   0.2082   1.0000
  11.750   1.5295   0.03092   0.02294  -0.0494   0.2045   1.0000
  12.000   1.5408   0.03196   0.02413  -0.0483   0.1998   1.0000
  12.250   1.5481   0.03330   0.02556  -0.0470   0.1941   1.0000
  12.500   1.5522   0.03492   0.02720  -0.0457   0.1885   1.0000
  12.750   1.5593   0.03639   0.02880  -0.0447   0.1813   1.0000
  13.000   1.5616   0.03828   0.03072  -0.0435   0.1754   1.0000
  13.250   1.5679   0.03993   0.03250  -0.0427   0.1682   1.0000
  13.500   1.5700   0.04198   0.03460  -0.0418   0.1624   1.0000
  13.750   1.5741   0.04393   0.03665  -0.0411   0.1565   1.0000
  14.000   1.5748   0.04625   0.03905  -0.0404   0.1501   1.0000
  14.250   1.5753   0.04868   0.04156  -0.0399   0.1437   1.0000
  14.500   1.5734   0.05145   0.04437  -0.0394   0.1370   1.0000
  14.750   1.5714   0.05431   0.04731  -0.0391   0.1309   1.0000
  15.000   1.5681   0.05741   0.05048  -0.0390   0.1250   1.0000
  15.250   1.5640   0.06069   0.05382  -0.0390   0.1203   1.0000
  15.500   1.5603   0.06403   0.05725  -0.0391   0.1145   1.0000
  15.750   1.5526   0.06797   0.06125  -0.0395   0.1100   1.0000
  16.000   1.5481   0.07159   0.06498  -0.0399   0.1045   1.0000
  16.250   1.5414   0.07559   0.06906  -0.0406   0.1004   1.0000
  16.500   1.5327   0.08000   0.07355  -0.0414   0.0958   1.0000
  16.750   1.5269   0.08406   0.07773  -0.0423   0.0914   1.0000
  17.000   1.5131   0.08939   0.08310  -0.0437   0.0862   1.0000
  17.250   1.5063   0.09377   0.08760  -0.0448   0.0810   1.0000
  17.500   1.4926   0.09929   0.09319  -0.0465   0.0757   1.0000
  17.750   1.4835   0.10419   0.09819  -0.0481   0.0700   1.0000
  18.000   1.4681   0.11018   0.10425  -0.0502   0.0627   1.0000
  18.250   1.4551   0.11587   0.11001  -0.0523   0.0567   1.0000
  18.500   1.4362   0.12272   0.11690  -0.0551   0.0475   1.0000
  18.750   1.4160   0.12994   0.12415  -0.0583   0.0382   1.0000
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