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GOE 619 AIRFOIL (goe619-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 619 AIRFOIL (goe619-il)
Reynolds number: 100,000
Max Cl/Cd: 51.3 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe619-il-100000-n5.txt
Download as CSV file: xf-goe619-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 619 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3518   0.09558   0.09040  -0.0470   1.0000   0.0544
  -9.750  -0.3679   0.09195   0.08686  -0.0465   1.0000   0.0546
  -9.250  -0.5298   0.04745   0.04191  -0.0872   0.9672   0.0542
  -9.000  -0.5256   0.04111   0.03499  -0.0930   0.9565   0.0553
  -8.750  -0.5131   0.03730   0.03068  -0.0951   0.9468   0.0564
  -8.500  -0.4941   0.03425   0.02715  -0.0966   0.9393   0.0575
  -8.250  -0.4707   0.03204   0.02460  -0.0977   0.9323   0.0585
  -8.000  -0.4383   0.03080   0.02330  -0.0996   0.9284   0.0599
  -7.750  -0.4165   0.02973   0.02212  -0.0993   0.9198   0.0612
  -7.500  -0.3856   0.02848   0.02067  -0.1007   0.9149   0.0635
  -7.250  -0.3537   0.02709   0.01896  -0.1022   0.9107   0.0667
  -7.000  -0.3304   0.02631   0.01815  -0.1018   0.9023   0.0690
  -6.750  -0.2973   0.02544   0.01718  -0.1032   0.8979   0.0726
  -6.500  -0.2684   0.02444   0.01594  -0.1037   0.8919   0.0771
  -6.250  -0.2420   0.02376   0.01527  -0.1037   0.8846   0.0813
  -6.000  -0.2085   0.02296   0.01425  -0.1049   0.8803   0.0890
  -5.750  -0.1828   0.02245   0.01375  -0.1047   0.8729   0.0961
  -5.500  -0.1533   0.02188   0.01304  -0.1051   0.8665   0.1050
  -5.250  -0.1191   0.02134   0.01241  -0.1064   0.8623   0.1142
  -5.000  -0.0958   0.02096   0.01198  -0.1056   0.8539   0.1209
  -4.750  -0.0648   0.02055   0.01150  -0.1062   0.8482   0.1291
  -4.500  -0.0326   0.02019   0.01111  -0.1070   0.8432   0.1397
  -4.250  -0.0088   0.02000   0.01089  -0.1063   0.8347   0.1502
  -4.000   0.0236   0.01972   0.01054  -0.1070   0.8296   0.1619
  -3.750   0.0496   0.01950   0.01035  -0.1066   0.8223   0.1704
  -3.500   0.0780   0.01920   0.00998  -0.1065   0.8155   0.1792
  -3.250   0.1112   0.01884   0.00962  -0.1073   0.8110   0.1890
  -3.000   0.1334   0.01872   0.00951  -0.1062   0.8022   0.1997
  -2.750   0.1639   0.01847   0.00924  -0.1065   0.7964   0.2147
  -2.500   0.1908   0.01833   0.00909  -0.1061   0.7894   0.2305
  -2.250   0.2177   0.01821   0.00895  -0.1057   0.7820   0.2466
  -2.000   0.2505   0.01800   0.00870  -0.1063   0.7769   0.2640
  -1.750   0.2722   0.01802   0.00871  -0.1050   0.7676   0.2793
  -1.500   0.3032   0.01786   0.00852  -0.1053   0.7614   0.2963
  -1.250   0.3268   0.01783   0.00852  -0.1043   0.7526   0.3106
  -1.000   0.3566   0.01766   0.00833  -0.1043   0.7451   0.3259
  -0.750   0.3807   0.01760   0.00829  -0.1033   0.7353   0.3403
  -0.500   0.4115   0.01741   0.00806  -0.1034   0.7269   0.3576
  -0.250   0.4343   0.01736   0.00806  -0.1022   0.7154   0.3767
   0.000   0.4610   0.01724   0.00795  -0.1016   0.7049   0.3997
   0.250   0.4886   0.01709   0.00781  -0.1011   0.6945   0.4222
   0.500   0.5124   0.01701   0.00779  -0.1001   0.6830   0.4431
   0.750   0.5399   0.01688   0.00766  -0.0996   0.6733   0.4657
   1.000   0.5651   0.01677   0.00762  -0.0989   0.6629   0.4924
   1.250   0.5896   0.01663   0.00760  -0.0980   0.6527   0.5282
   1.500   0.6145   0.01627   0.00756  -0.0970   0.6432   0.6018
   1.750   0.6743   0.01564   0.00763  -0.1027   0.6297   1.0000
   2.000   0.6973   0.01578   0.00765  -0.1015   0.6179   1.0000
   2.250   0.7214   0.01589   0.00763  -0.1006   0.6064   1.0000
   2.500   0.7443   0.01603   0.00767  -0.0994   0.5939   1.0000
   2.750   0.7660   0.01620   0.00777  -0.0980   0.5804   1.0000
   3.000   0.7879   0.01637   0.00785  -0.0967   0.5662   1.0000
   3.250   0.8094   0.01654   0.00794  -0.0953   0.5508   1.0000
   3.500   0.8304   0.01673   0.00804  -0.0938   0.5342   1.0000
   3.750   0.8510   0.01694   0.00816  -0.0922   0.5165   1.0000
   4.000   0.8712   0.01718   0.00829  -0.0906   0.4978   1.0000
   4.250   0.8911   0.01745   0.00844  -0.0890   0.4791   1.0000
   4.500   0.9104   0.01776   0.00862  -0.0873   0.4605   1.0000
   4.750   0.9291   0.01811   0.00885  -0.0856   0.4418   1.0000
   5.000   0.9473   0.01851   0.00913  -0.0837   0.4237   1.0000
   5.250   0.9651   0.01894   0.00944  -0.0819   0.4069   1.0000
   5.500   0.9828   0.01940   0.00979  -0.0801   0.3916   1.0000
   6.000   1.0186   0.02036   0.01059  -0.0767   0.3660   1.0000
   6.250   1.0370   0.02085   0.01102  -0.0751   0.3557   1.0000
   6.500   1.0550   0.02136   0.01145  -0.0735   0.3467   1.0000
   6.750   1.0727   0.02186   0.01194  -0.0718   0.3374   1.0000
   7.000   1.0896   0.02241   0.01239  -0.0701   0.3291   1.0000
   7.250   1.1062   0.02293   0.01293  -0.0683   0.3198   1.0000
   7.500   1.1224   0.02351   0.01341  -0.0665   0.3119   1.0000
   7.750   1.1387   0.02404   0.01401  -0.0648   0.3037   1.0000
   8.000   1.1551   0.02464   0.01454  -0.0631   0.2969   1.0000
   8.250   1.1721   0.02521   0.01516  -0.0616   0.2904   1.0000
   8.500   1.1891   0.02580   0.01579  -0.0601   0.2846   1.0000
   8.750   1.2063   0.02644   0.01636  -0.0587   0.2794   1.0000
   9.000   1.2221   0.02705   0.01709  -0.0571   0.2736   1.0000
   9.250   1.2373   0.02770   0.01779  -0.0555   0.2680   1.0000
   9.500   1.2541   0.02838   0.01842  -0.0541   0.2636   1.0000
   9.750   1.2704   0.02906   0.01925  -0.0528   0.2593   1.0000
  10.000   1.2858   0.02977   0.02006  -0.0513   0.2549   1.0000
  10.250   1.3002   0.03051   0.02085  -0.0498   0.2504   1.0000
  10.500   1.3142   0.03128   0.02163  -0.0483   0.2458   1.0000
  10.750   1.3251   0.03215   0.02268  -0.0465   0.2404   1.0000
  11.000   1.3357   0.03304   0.02365  -0.0448   0.2352   1.0000
  11.250   1.3453   0.03398   0.02458  -0.0430   0.2298   1.0000
  11.500   1.3504   0.03513   0.02592  -0.0411   0.2227   1.0000
  11.750   1.3553   0.03633   0.02714  -0.0392   0.2160   1.0000
  12.000   1.3596   0.03768   0.02864  -0.0375   0.2085   1.0000
  12.250   1.3633   0.03912   0.03016  -0.0358   0.2015   1.0000
  12.500   1.3671   0.04068   0.03183  -0.0344   0.1942   1.0000
  12.750   1.3694   0.04241   0.03367  -0.0331   0.1865   1.0000
  13.000   1.3729   0.04418   0.03556  -0.0320   0.1797   1.0000
  13.250   1.3745   0.04618   0.03768  -0.0310   0.1718   1.0000
  13.500   1.3762   0.04829   0.03992  -0.0301   0.1638   1.0000
  13.750   1.3745   0.05077   0.04248  -0.0294   0.1552   1.0000
  14.000   1.3737   0.05334   0.04517  -0.0288   0.1453   1.0000
  14.250   1.3697   0.05633   0.04823  -0.0285   0.1356   1.0000
  14.500   1.3631   0.05974   0.05169  -0.0283   0.1269   1.0000
  14.750   1.3534   0.06370   0.05568  -0.0285   0.1177   1.0000
  15.000   1.3421   0.06807   0.06011  -0.0290   0.1097   1.0000
  15.500   1.3151   0.07807   0.07026  -0.0311   0.0988   1.0000
  15.750   1.3000   0.08367   0.07597  -0.0327   0.0951   1.0000
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