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GOE 142 (MVA H.19) AIRFOIL (goe142-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 142 (MVA H.19) AIRFOIL (goe142-il)
Reynolds number: 100,000
Max Cl/Cd: 56.63 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe142-il-100000-n5.txt
Download as CSV file: xf-goe142-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 142 (MVA H.19) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3873   0.10151   0.09659  -0.0105   1.0000   0.0382
  -7.750  -0.3824   0.09867   0.09380  -0.0123   1.0000   0.0392
  -7.500  -0.3790   0.09620   0.09139  -0.0147   1.0000   0.0403
  -7.250  -0.3734   0.09378   0.08904  -0.0193   1.0000   0.0410
  -7.000  -0.3631   0.09088   0.08617  -0.0248   1.0000   0.0413
  -6.750  -0.3507   0.08763   0.08294  -0.0295   1.0000   0.0415
  -6.500  -0.2960   0.07272   0.06847  -0.0317   1.0000   0.0418
  -6.250  -0.2953   0.06706   0.06289  -0.0260   1.0000   0.0432
  -5.750  -0.3152   0.07235   0.06777  -0.0333   1.0000   0.0434
  -5.500  -0.3086   0.06970   0.06517  -0.0315   1.0000   0.0457
  -5.250  -0.2970   0.06681   0.06228  -0.0328   1.0000   0.0481
  -5.000  -0.2826   0.06368   0.05912  -0.0349   1.0000   0.0501
  -4.750  -0.2509   0.06074   0.05593  -0.0421   1.0000   0.0540
  -4.500  -0.2303   0.05754   0.05256  -0.0443   1.0000   0.0543
  -4.250  -0.2262   0.05204   0.04717  -0.0422   1.0000   0.0390
  -4.000  -0.2059   0.04805   0.04305  -0.0440   0.9998   0.0351
  -3.500  -0.1126   0.03698   0.03116  -0.0567   0.9892   0.0323
  -3.250  -0.0732   0.03449   0.02844  -0.0606   0.9838   0.0354
  -3.000  -0.0315   0.03038   0.02385  -0.0642   0.9772   0.0351
  -2.750   0.0117   0.02676   0.01968  -0.0676   0.9720   0.0357
  -2.500   0.0519   0.02395   0.01631  -0.0700   0.9653   0.0383
  -2.250   0.0937   0.02155   0.01321  -0.0723   0.9591   0.0421
  -2.000   0.1315   0.01986   0.01127  -0.0744   0.9516   0.0450
  -1.750   0.1696   0.01882   0.00999  -0.0762   0.9434   0.0517
  -1.500   0.2041   0.01758   0.00853  -0.0771   0.9329   0.0565
  -1.250   0.2382   0.01681   0.00771  -0.0782   0.9218   0.0640
  -1.000   0.2714   0.01607   0.00690  -0.0789   0.9097   0.0729
  -0.750   0.3032   0.01547   0.00622  -0.0792   0.8963   0.0828
  -0.500   0.3336   0.01498   0.00573  -0.0794   0.8813   0.0970
  -0.250   0.3629   0.01452   0.00527  -0.0792   0.8652   0.1118
   0.000   0.3919   0.01416   0.00492  -0.0790   0.8480   0.1388
   0.250   0.4211   0.01373   0.00461  -0.0789   0.8301   0.1879
   0.500   0.4475   0.01166   0.00438  -0.0780   0.8114   1.0000
   0.750   0.4749   0.01171   0.00417  -0.0773   0.7899   1.0000
   1.000   0.5018   0.01178   0.00403  -0.0766   0.7673   1.0000
   1.250   0.5286   0.01187   0.00391  -0.0758   0.7440   1.0000
   1.500   0.5550   0.01200   0.00386  -0.0751   0.7190   1.0000
   1.750   0.5812   0.01214   0.00384  -0.0744   0.6935   1.0000
   2.000   0.6073   0.01232   0.00384  -0.0737   0.6678   1.0000
   2.250   0.6332   0.01252   0.00388  -0.0730   0.6419   1.0000
   2.500   0.6590   0.01276   0.00395  -0.0723   0.6160   1.0000
   2.750   0.6848   0.01301   0.00408  -0.0716   0.5899   1.0000
   3.000   0.7104   0.01328   0.00422  -0.0710   0.5643   1.0000
   3.250   0.7360   0.01357   0.00439  -0.0704   0.5393   1.0000
   3.500   0.7614   0.01389   0.00459  -0.0698   0.5154   1.0000
   3.750   0.7868   0.01422   0.00485  -0.0693   0.4914   1.0000
   4.000   0.8121   0.01457   0.00512  -0.0687   0.4688   1.0000
   4.250   0.8372   0.01494   0.00540  -0.0682   0.4471   1.0000
   4.500   0.8625   0.01531   0.00573  -0.0677   0.4261   1.0000
   4.750   0.8875   0.01571   0.00612  -0.0672   0.4064   1.0000
   5.000   0.9124   0.01613   0.00650  -0.0667   0.3878   1.0000
   5.250   0.9373   0.01655   0.00692  -0.0662   0.3696   1.0000
   5.500   0.9621   0.01699   0.00737  -0.0657   0.3524   1.0000
   5.750   0.9867   0.01746   0.00785  -0.0651   0.3362   1.0000
   6.000   1.0111   0.01794   0.00840  -0.0646   0.3208   1.0000
   6.250   1.0353   0.01845   0.00895  -0.0640   0.3060   1.0000
   6.500   1.0594   0.01897   0.00953  -0.0635   0.2916   1.0000
   6.750   1.0833   0.01952   0.01014  -0.0629   0.2775   1.0000
   7.000   1.1068   0.02008   0.01082  -0.0623   0.2630   1.0000
   7.250   1.1298   0.02064   0.01148  -0.0616   0.2465   1.0000
   7.500   1.1521   0.02119   0.01211  -0.0609   0.2251   1.0000
   7.750   1.1735   0.02179   0.01274  -0.0602   0.1994   1.0000
   8.000   1.1947   0.02248   0.01346  -0.0594   0.1738   1.0000
   8.250   1.2152   0.02328   0.01433  -0.0586   0.1465   1.0000
   8.500   1.2335   0.02439   0.01534  -0.0576   0.1088   1.0000
   8.750   1.2479   0.02607   0.01679  -0.0563   0.0708   1.0000
   9.000   1.2600   0.02802   0.01859  -0.0546   0.0512   1.0000
   9.250   1.2721   0.02982   0.02050  -0.0528   0.0425   1.0000
   9.500   1.2833   0.03158   0.02244  -0.0509   0.0374   1.0000
   9.750   1.2930   0.03335   0.02435  -0.0491   0.0330   1.0000
  10.000   1.2981   0.03543   0.02660  -0.0468   0.0302   1.0000
  10.250   1.3047   0.03730   0.02871  -0.0445   0.0284   1.0000
  10.500   1.3077   0.03927   0.03088  -0.0419   0.0269   1.0000
  10.750   1.3095   0.04136   0.03313  -0.0395   0.0256   1.0000
  11.000   1.3101   0.04359   0.03550  -0.0375   0.0242   1.0000
  11.250   1.3082   0.04618   0.03819  -0.0357   0.0230   1.0000
  11.500   1.3050   0.04927   0.04138  -0.0341   0.0219   1.0000
  11.750   1.3057   0.05199   0.04438  -0.0331   0.0211   1.0000
  12.000   1.3045   0.05512   0.04776  -0.0322   0.0205   1.0000
  12.250   1.3017   0.05859   0.05147  -0.0316   0.0200   1.0000
  12.500   1.2971   0.06241   0.05554  -0.0315   0.0196   1.0000
  12.750   1.2903   0.06665   0.06002  -0.0319   0.0193   1.0000
  13.000   1.2814   0.07134   0.06496  -0.0329   0.0190   1.0000
  13.250   1.2706   0.07652   0.07038  -0.0345   0.0189   1.0000
  13.500   1.2578   0.08223   0.07633  -0.0368   0.0187   1.0000
  13.750   1.2431   0.08856   0.08288  -0.0398   0.0187   1.0000
  14.000   1.2268   0.09547   0.09001  -0.0434   0.0187   1.0000
  14.250   1.2088   0.10309   0.09783  -0.0477   0.0188   1.0000
  14.500   1.1897   0.11140   0.10633  -0.0527   0.0189   1.0000
  14.750   1.1693   0.12061   0.11572  -0.0584   0.0191   1.0000
  15.000   1.1477   0.13077   0.12603  -0.0647   0.0194   1.0000
  15.250   1.1250   0.14205   0.13742  -0.0718   0.0198   1.0000
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