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GOE 803 (HACKLINGER) AIRFOIL (goe803h-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 803 (HACKLINGER) AIRFOIL (goe803h-il)
Reynolds number: 50,000
Max Cl/Cd: 48.14 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe803h-il-50000-n5.txt
Download as CSV file: xf-goe803h-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 803 (HACKLINGER) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.2453   0.10576   0.09920  -0.0240   1.0000   0.0660
  -6.750  -0.2486   0.10509   0.09865  -0.0239   1.0000   0.0667
  -6.500  -0.2527   0.10469   0.09838  -0.0241   1.0000   0.0671
  -6.250  -0.2559   0.10435   0.09815  -0.0249   1.0000   0.0674
  -6.000  -0.2565   0.10389   0.09777  -0.0266   1.0000   0.0676
  -5.500  -0.2549   0.09678   0.09083  -0.0213   0.9987   0.0691
  -5.250  -0.2321   0.09254   0.08658  -0.0240   0.9921   0.0719
  -5.000  -0.2015   0.08909   0.08310  -0.0308   0.9837   0.0762
  -4.750  -0.1398   0.08772   0.08152  -0.0514   0.9713   0.0802
  -4.500  -0.1254   0.08245   0.07633  -0.0505   0.9647   0.0814
  -4.250  -0.1065   0.07851   0.07240  -0.0513   0.9567   0.0838
  -4.000  -0.0731   0.07503   0.06887  -0.0571   0.9495   0.0880
  -3.750  -0.0010   0.07303   0.06661  -0.0769   0.9396   0.0946
  -3.500   0.0093   0.06842   0.06209  -0.0744   0.9326   0.0966
  -3.250   0.0382   0.06513   0.05878  -0.0774   0.9254   0.1021
  -3.000   0.0894   0.06194   0.05546  -0.0879   0.9185   0.1120
  -2.750   0.1441   0.05937   0.05269  -0.0984   0.9113   0.1257
  -2.500   0.1714   0.05557   0.04896  -0.0996   0.9068   0.1324
  -2.250   0.2128   0.05297   0.04626  -0.1060   0.8979   0.1444
  -2.000   0.2602   0.05001   0.04319  -0.1127   0.8930   0.1607
  -1.750   0.2983   0.04769   0.04080  -0.1172   0.8850   0.1789
  -1.250   0.3710   0.04316   0.03623  -0.1243   0.8709   0.2561
  -0.750   0.5286   0.03632   0.02802  -0.1468   0.8605   0.0865
  -0.500   0.5747   0.03469   0.02580  -0.1505   0.8510   0.0798
  -0.250   0.6176   0.03280   0.02376  -0.1539   0.8446   0.0829
   0.000   0.6524   0.03164   0.02232  -0.1553   0.8337   0.0832
   0.250   0.6920   0.03025   0.02056  -0.1570   0.8222   0.0824
   0.500   0.7292   0.02894   0.01898  -0.1579   0.8084   0.0844
   0.750   0.7634   0.02791   0.01766  -0.1581   0.7929   0.0901
   1.000   0.7971   0.02696   0.01633  -0.1580   0.7774   0.0931
   1.250   0.8278   0.02615   0.01530  -0.1575   0.7632   0.0999
   1.500   0.8574   0.02556   0.01446  -0.1568   0.7498   0.1067
   1.750   0.8846   0.02512   0.01391  -0.1560   0.7356   0.1156
   2.000   0.9120   0.02480   0.01345  -0.1551   0.7215   0.1245
   2.250   0.9396   0.02450   0.01313  -0.1545   0.7071   0.1372
   2.500   0.9673   0.02429   0.01289  -0.1538   0.6923   0.1528
   2.750   0.9950   0.02409   0.01276  -0.1533   0.6768   0.1773
   3.000   1.0175   0.02281   0.01283  -0.1519   0.6612   1.0000
   3.250   1.0431   0.02303   0.01273  -0.1507   0.6440   1.0000
   3.500   1.0680   0.02326   0.01276  -0.1495   0.6258   1.0000
   3.750   1.0929   0.02346   0.01280  -0.1483   0.6066   1.0000
   4.000   1.1170   0.02371   0.01294  -0.1470   0.5859   1.0000
   4.250   1.1406   0.02402   0.01314  -0.1458   0.5636   1.0000
   4.500   1.1649   0.02431   0.01329  -0.1445   0.5421   1.0000
   4.750   1.1879   0.02473   0.01364  -0.1433   0.5188   1.0000
   5.000   1.2112   0.02516   0.01394  -0.1421   0.4964   1.0000
   5.250   1.2341   0.02569   0.01434  -0.1409   0.4747   1.0000
   5.500   1.2567   0.02630   0.01486  -0.1397   0.4544   1.0000
   5.750   1.2796   0.02696   0.01546  -0.1387   0.4369   1.0000
   6.000   1.3025   0.02768   0.01611  -0.1377   0.4215   1.0000
   6.250   1.3254   0.02843   0.01681  -0.1367   0.4075   1.0000
   6.500   1.3483   0.02920   0.01754  -0.1358   0.3951   1.0000
   6.750   1.3717   0.02998   0.01830  -0.1350   0.3841   1.0000
   7.000   1.3939   0.03087   0.01927  -0.1341   0.3730   1.0000
   7.250   1.4161   0.03175   0.02017  -0.1332   0.3625   1.0000
   7.500   1.4391   0.03257   0.02096  -0.1323   0.3528   1.0000
   7.750   1.4592   0.03356   0.02215  -0.1312   0.3423   1.0000
   8.000   1.4808   0.03451   0.02315  -0.1302   0.3332   1.0000
   8.250   1.5019   0.03549   0.02423  -0.1292   0.3243   1.0000
   8.500   1.5223   0.03658   0.02549  -0.1282   0.3162   1.0000
   8.750   1.5432   0.03756   0.02653  -0.1272   0.3074   1.0000
   9.000   1.5589   0.03872   0.02796  -0.1256   0.2971   1.0000
   9.250   1.5753   0.03971   0.02903  -0.1240   0.2864   1.0000
   9.500   1.5905   0.04064   0.03002  -0.1222   0.2750   1.0000
   9.750   1.5994   0.04188   0.03152  -0.1199   0.2634   1.0000
  10.000   1.6095   0.04302   0.03285  -0.1176   0.2524   1.0000
  10.250   1.6194   0.04400   0.03387  -0.1153   0.2413   1.0000
  10.500   1.6213   0.04549   0.03566  -0.1124   0.2302   1.0000
  10.750   1.6246   0.04692   0.03728  -0.1096   0.2205   1.0000
  11.000   1.6258   0.04833   0.03886  -0.1065   0.2116   1.0000
  11.250   1.6235   0.05027   0.04108  -0.1035   0.2029   1.0000
  11.500   1.6235   0.05195   0.04288  -0.1009   0.1946   1.0000
  11.750   1.6161   0.05465   0.04595  -0.0985   0.1851   1.0000
  12.000   1.6105   0.05725   0.04875  -0.0966   0.1763   1.0000
  12.250   1.6029   0.06023   0.05192  -0.0950   0.1672   1.0000
  12.500   1.5926   0.06393   0.05585  -0.0939   0.1579   1.0000
  12.750   1.5831   0.06760   0.05962  -0.0932   0.1495   1.0000
  13.000   1.5724   0.07168   0.06381  -0.0928   0.1413   1.0000
  13.250   1.5603   0.07627   0.06852  -0.0929   0.1339   1.0000
  13.500   1.5498   0.08061   0.07286  -0.0930   0.1273   1.0000
  13.750   1.5360   0.08591   0.07831  -0.0937   0.1214   1.0000
  14.000   1.5239   0.09100   0.08347  -0.0945   0.1160   1.0000
  14.250   1.5150   0.09557   0.08803  -0.0950   0.1113   1.0000
  14.500   1.4981   0.10222   0.09494  -0.0970   0.1076   1.0000
  14.750   1.4853   0.10817   0.10104  -0.0987   0.1041   1.0000
  15.000   1.4847   0.11149   0.10431  -0.0990   0.1002   1.0000
  15.250   1.4687   0.11863   0.11165  -0.1018   0.0977   1.0000
  15.500   1.4418   0.12877   0.12208  -0.1071   0.0960   1.0000
  15.750   1.4029   0.14291   0.13644  -0.1154   0.0950   1.0000
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