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GOE 401 AIRFOIL (goe401-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 401 AIRFOIL (goe401-il)
Reynolds number: 100,000
Max Cl/Cd: 55.95 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe401-il-100000-n5.txt
Download as CSV file: xf-goe401-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 401 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3121   0.09548   0.09059  -0.0234   1.0000   0.0523
  -7.500  -0.3200   0.09443   0.08965  -0.0247   1.0000   0.0532
  -7.250  -0.3212   0.09292   0.08821  -0.0288   1.0000   0.0536
  -7.000  -0.3178   0.09072   0.08607  -0.0327   1.0000   0.0539
  -6.750  -0.3114   0.08557   0.08098  -0.0256   1.0000   0.0553
  -6.500  -0.3070   0.08294   0.07842  -0.0242   1.0000   0.0566
  -6.250  -0.3043   0.08066   0.07620  -0.0238   1.0000   0.0581
  -6.000  -0.3032   0.07853   0.07413  -0.0237   1.0000   0.0595
  -5.750  -0.2943   0.07604   0.07165  -0.0259   0.9979   0.0616
  -5.500  -0.2299   0.07278   0.06798  -0.0465   0.9828   0.0649
  -5.250  -0.2147   0.06678   0.06210  -0.0461   0.9748   0.0661
  -5.000  -0.1924   0.06313   0.05848  -0.0470   0.9637   0.0686
  -4.750  -0.1610   0.05976   0.05502  -0.0516   0.9510   0.0727
  -4.500  -0.1029   0.05795   0.05266  -0.0634   0.9375   0.0780
  -4.250  -0.0757   0.05318   0.04784  -0.0665   0.9272   0.0788
  -4.000  -0.0484   0.04899   0.04365  -0.0688   0.9189   0.0800
  -3.750  -0.0194   0.04594   0.04056  -0.0709   0.9084   0.0823
  -3.500   0.0139   0.04344   0.03792  -0.0738   0.8971   0.0876
  -3.250   0.0638   0.04254   0.03634  -0.0789   0.8855   0.0932
  -2.750   0.1275   0.03198   0.02514  -0.0824   0.8621   0.0530
  -2.500   0.1571   0.02988   0.02283  -0.0832   0.8484   0.0522
  -2.250   0.1874   0.02778   0.02040  -0.0838   0.8344   0.0522
  -2.000   0.2174   0.02579   0.01799  -0.0840   0.8202   0.0531
  -1.750   0.2459   0.02413   0.01601  -0.0839   0.8053   0.0528
  -1.500   0.2739   0.02265   0.01422  -0.0837   0.7900   0.0524
  -1.250   0.3017   0.02130   0.01256  -0.0833   0.7743   0.0522
  -1.000   0.3294   0.02013   0.01107  -0.0828   0.7578   0.0522
  -0.750   0.3569   0.01913   0.00977  -0.0823   0.7409   0.0525
  -0.500   0.3840   0.01829   0.00869  -0.0816   0.7232   0.0529
  -0.250   0.4108   0.01764   0.00781  -0.0809   0.7048   0.0539
   0.000   0.4367   0.01719   0.00731  -0.0803   0.6856   0.0565
   0.250   0.4622   0.01685   0.00689  -0.0795   0.6650   0.0594
   0.500   0.4878   0.01645   0.00637  -0.0787   0.6443   0.0613
   0.750   0.5131   0.01613   0.00590  -0.0777   0.6239   0.0634
   1.000   0.5385   0.01588   0.00556  -0.0769   0.6029   0.0663
   1.250   0.5644   0.01577   0.00533  -0.0762   0.5825   0.0714
   1.500   0.5902   0.01570   0.00514  -0.0755   0.5640   0.0812
   1.750   0.6158   0.01567   0.00511  -0.0749   0.5467   0.1143
   2.000   0.6414   0.01571   0.00514  -0.0743   0.5310   0.1705
   2.500   0.7175   0.01441   0.00520  -0.0788   0.5008   1.0000
   2.750   0.7421   0.01468   0.00532  -0.0780   0.4888   1.0000
   3.000   0.7667   0.01496   0.00546  -0.0772   0.4778   1.0000
   3.250   0.7912   0.01528   0.00561  -0.0764   0.4683   1.0000
   3.500   0.8158   0.01557   0.00584  -0.0757   0.4582   1.0000
   3.750   0.8404   0.01589   0.00606  -0.0750   0.4494   1.0000
   4.000   0.8650   0.01622   0.00632  -0.0743   0.4406   1.0000
   4.250   0.8895   0.01655   0.00661  -0.0736   0.4320   1.0000
   4.500   0.9140   0.01691   0.00692  -0.0729   0.4240   1.0000
   4.750   0.9383   0.01725   0.00727  -0.0722   0.4156   1.0000
   5.000   0.9626   0.01762   0.00760  -0.0715   0.4079   1.0000
   5.250   0.9868   0.01798   0.00803  -0.0708   0.3998   1.0000
   5.500   1.0109   0.01836   0.00840  -0.0701   0.3923   1.0000
   5.750   1.0347   0.01874   0.00885  -0.0694   0.3844   1.0000
   6.000   1.0586   0.01913   0.00929  -0.0686   0.3772   1.0000
   6.250   1.0819   0.01951   0.00976  -0.0678   0.3686   1.0000
   6.500   1.1048   0.01988   0.01013  -0.0669   0.3599   1.0000
   6.750   1.1269   0.02021   0.01060  -0.0659   0.3492   1.0000
   7.000   1.1490   0.02057   0.01104  -0.0649   0.3396   1.0000
   7.250   1.1710   0.02093   0.01149  -0.0639   0.3305   1.0000
   7.500   1.1928   0.02132   0.01202  -0.0629   0.3210   1.0000
   7.750   1.2142   0.02170   0.01247  -0.0618   0.3121   1.0000
   8.000   1.2350   0.02209   0.01304  -0.0606   0.3017   1.0000
   8.250   1.2557   0.02252   0.01361  -0.0595   0.2920   1.0000
   8.500   1.2755   0.02295   0.01413  -0.0582   0.2820   1.0000
   8.750   1.2936   0.02336   0.01466  -0.0566   0.2677   1.0000
   9.000   1.3099   0.02382   0.01525  -0.0549   0.2480   1.0000
   9.250   1.3228   0.02445   0.01585  -0.0528   0.2201   1.0000
   9.500   1.3335   0.02535   0.01666  -0.0505   0.1858   1.0000
   9.750   1.3407   0.02660   0.01775  -0.0479   0.1428   1.0000
  10.000   1.3381   0.02860   0.01936  -0.0445   0.0938   1.0000
  10.250   1.3336   0.03057   0.02117  -0.0407   0.0753   1.0000
  10.500   1.3293   0.03248   0.02307  -0.0371   0.0660   1.0000
  10.750   1.3256   0.03443   0.02515  -0.0340   0.0589   1.0000
  11.000   1.3186   0.03676   0.02757  -0.0313   0.0538   1.0000
  11.250   1.3114   0.03933   0.03026  -0.0292   0.0496   1.0000
  11.500   1.3057   0.04203   0.03314  -0.0278   0.0457   1.0000
  11.750   1.2971   0.04528   0.03653  -0.0269   0.0432   1.0000
  12.000   1.2846   0.04923   0.04058  -0.0267   0.0413   1.0000
  12.250   1.2771   0.05293   0.04444  -0.0268   0.0395   1.0000
  12.500   1.2702   0.05677   0.04845  -0.0272   0.0376   1.0000
  12.750   1.2623   0.06092   0.05273  -0.0279   0.0358   1.0000
  13.000   1.2546   0.06520   0.05712  -0.0290   0.0344   1.0000
  13.250   1.2458   0.06973   0.06173  -0.0302   0.0332   1.0000
  13.500   1.2398   0.07381   0.06591  -0.0310   0.0321   1.0000
  13.750   1.2371   0.07749   0.06974  -0.0316   0.0306   1.0000
  14.000   1.2352   0.08101   0.07337  -0.0321   0.0295   1.0000
  14.250   1.2340   0.08446   0.07694  -0.0326   0.0284   1.0000
  14.500   1.2334   0.08788   0.08044  -0.0332   0.0275   1.0000
  14.750   1.2334   0.09124   0.08385  -0.0338   0.0268   1.0000
  15.000   1.2343   0.09433   0.08695  -0.0341   0.0259   1.0000
  15.250   1.2353   0.09777   0.09059  -0.0346   0.0249   1.0000
  15.500   1.2344   0.10160   0.09460  -0.0356   0.0240   1.0000
  15.750   1.2325   0.10571   0.09887  -0.0369   0.0232   1.0000
  16.000   1.2303   0.10991   0.10322  -0.0383   0.0226   1.0000
  16.250   1.2274   0.11431   0.10776  -0.0399   0.0220   1.0000
  16.500   1.2240   0.11889   0.11247  -0.0417   0.0217   1.0000
  16.750   1.2200   0.12370   0.11744  -0.0438   0.0213   1.0000
  17.000   1.2145   0.12891   0.12281  -0.0463   0.0211   1.0000
  17.250   1.2081   0.13445   0.12849  -0.0491   0.0209   1.0000
  17.500   1.1995   0.14068   0.13488  -0.0525   0.0208   1.0000
  17.750   1.1884   0.14780   0.14217  -0.0567   0.0207   1.0000
  18.000   1.1701   0.15731   0.15191  -0.0626   0.0209   1.0000
  18.250   1.1243   0.17658   0.17147  -0.0749   0.0217   1.0000
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