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GOE 57 AIRFOIL (goe57-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 57 AIRFOIL (goe57-il)
Reynolds number: 100,000
Max Cl/Cd: 63.31 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe57-il-100000.txt
Download as CSV file: xf-goe57-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 57 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.3113   0.09385   0.08935  -0.0223   1.0000   0.0591
  -6.750  -0.3127   0.09180   0.08736  -0.0214   1.0000   0.0604
  -6.500  -0.3154   0.08993   0.08556  -0.0204   1.0000   0.0617
  -6.250  -0.3179   0.08811   0.08380  -0.0198   1.0000   0.0631
  -6.000  -0.3188   0.08627   0.08200  -0.0199   1.0000   0.0647
  -5.750  -0.3154   0.08466   0.08042  -0.0220   1.0000   0.0668
  -5.500  -0.2917   0.08490   0.08053  -0.0341   1.0000   0.0686
  -5.250  -0.2866   0.08054   0.07622  -0.0342   1.0000   0.0693
  -5.000  -0.2916   0.07640   0.07218  -0.0284   1.0000   0.0706
  -4.750  -0.2885   0.07358   0.06940  -0.0261   1.0000   0.0726
  -4.500  -0.2784   0.07098   0.06681  -0.0267   1.0000   0.0753
  -4.250  -0.2616   0.06834   0.06412  -0.0296   1.0000   0.0790
  -4.000  -0.2142   0.06595   0.06142  -0.0422   1.0000   0.0837
  -3.750  -0.2117   0.06219   0.05775  -0.0395   1.0000   0.0850
  -3.500  -0.2016   0.05954   0.05513  -0.0386   1.0000   0.0877
  -3.250  -0.1454   0.05716   0.05237  -0.0499   0.9977   0.0980
  -3.000  -0.1187   0.05280   0.04810  -0.0520   0.9927   0.1014
  -2.750  -0.0574   0.04975   0.04467  -0.0623   0.9861   0.1127
  -2.500  -0.0213   0.04642   0.04136  -0.0660   0.9796   0.1195
  -2.250   0.0368   0.04413   0.03875  -0.0743   0.9724   0.1387
  -2.000   0.0780   0.04106   0.03562  -0.0789   0.9641   0.1509
  -1.750   0.1323   0.03840   0.03272  -0.0859   0.9579   0.1721
  -1.500   0.1740   0.03621   0.03045  -0.0897   0.9479   0.1939
  -1.250   0.2220   0.03379   0.02790  -0.0948   0.9392   0.2306
  -1.000   0.2676   0.03124   0.02539  -0.0989   0.9309   0.2915
  -0.750   0.3040   0.02897   0.02322  -0.1008   0.9203   0.3631
  -0.500   0.3573   0.02659   0.02079  -0.1053   0.9136   0.4141
  -0.250   0.4483   0.02529   0.01766  -0.1135   0.9044   0.1435
   0.000   0.4975   0.02343   0.01538  -0.1160   0.8964   0.1205
   0.250   0.5408   0.02205   0.01378  -0.1179   0.8875   0.1203
   0.500   0.5768   0.02103   0.01259  -0.1184   0.8757   0.1213
   0.750   0.6127   0.01995   0.01140  -0.1188   0.8636   0.1213
   1.000   0.6467   0.01904   0.01040  -0.1187   0.8505   0.1243
   1.250   0.6772   0.01811   0.00953  -0.1181   0.8356   0.1309
   1.500   0.7053   0.01739   0.00887  -0.1169   0.8186   0.1469
   1.750   0.7339   0.01672   0.00818  -0.1157   0.8006   0.1662
   2.000   0.7627   0.01590   0.00759  -0.1149   0.7830   0.2456
   2.250   0.7864   0.01437   0.00713  -0.1129   0.7631   1.0000
   2.500   0.8122   0.01431   0.00691  -0.1116   0.7415   1.0000
   2.750   0.8376   0.01429   0.00676  -0.1104   0.7177   1.0000
   3.000   0.8632   0.01429   0.00661  -0.1091   0.6922   1.0000
   3.250   0.8883   0.01436   0.00654  -0.1079   0.6638   1.0000
   3.500   0.9127   0.01453   0.00654  -0.1066   0.6321   1.0000
   3.750   0.9365   0.01480   0.00662  -0.1052   0.5971   1.0000
   4.000   0.9592   0.01515   0.00679  -0.1037   0.5576   1.0000
   4.250   0.9809   0.01559   0.00702  -0.1022   0.5123   1.0000
   4.500   1.0014   0.01621   0.00731  -0.1005   0.4635   1.0000
   4.750   1.0213   0.01706   0.00778  -0.0989   0.4180   1.0000
   5.000   1.0425   0.01798   0.00840  -0.0976   0.3829   1.0000
   5.250   1.0655   0.01884   0.00905  -0.0967   0.3601   1.0000
   5.500   1.0899   0.01964   0.00976  -0.0961   0.3450   1.0000
   5.750   1.1142   0.02034   0.01042  -0.0955   0.3319   1.0000
   6.000   1.1374   0.02093   0.01097  -0.0948   0.3181   1.0000
   6.250   1.1600   0.02145   0.01149  -0.0939   0.3044   1.0000
   6.500   1.1809   0.02186   0.01193  -0.0929   0.2886   1.0000
   6.750   1.2034   0.02237   0.01249  -0.0920   0.2775   1.0000
   7.000   1.2258   0.02289   0.01305  -0.0912   0.2677   1.0000
   7.250   1.2467   0.02334   0.01352  -0.0901   0.2553   1.0000
   7.500   1.2658   0.02368   0.01402  -0.0888   0.2393   1.0000
   7.750   1.2864   0.02417   0.01460  -0.0877   0.2281   1.0000
   8.000   1.3051   0.02463   0.01517  -0.0863   0.2125   1.0000
   8.250   1.3222   0.02511   0.01577  -0.0847   0.1891   1.0000
   8.500   1.3372   0.02593   0.01654  -0.0830   0.1566   1.0000
   8.750   1.3461   0.02791   0.01799  -0.0806   0.0652   1.0000
   9.000   1.3556   0.02987   0.02003  -0.0780   0.0533   1.0000
   9.250   1.3651   0.03162   0.02191  -0.0755   0.0484   1.0000
   9.500   1.3713   0.03344   0.02388  -0.0726   0.0459   1.0000
   9.750   1.3761   0.03505   0.02569  -0.0695   0.0442   1.0000
  10.000   1.3788   0.03678   0.02760  -0.0664   0.0425   1.0000
  10.250   1.3800   0.03868   0.02964  -0.0635   0.0408   1.0000
  10.500   1.3792   0.04081   0.03189  -0.0608   0.0393   1.0000
  10.750   1.3763   0.04327   0.03444  -0.0583   0.0382   1.0000
  11.000   1.3749   0.04589   0.03711  -0.0559   0.0375   1.0000
  11.250   1.3800   0.04841   0.03966  -0.0537   0.0371   1.0000
  11.500   1.3939   0.05054   0.04185  -0.0519   0.0368   1.0000
  11.750   1.4154   0.05282   0.04421  -0.0505   0.0366   1.0000
  12.000   1.4412   0.05569   0.04722  -0.0495   0.0367   1.0000
  12.250   1.4649   0.05943   0.05117  -0.0488   0.0369   1.0000
  12.500   1.4790   0.06326   0.05528  -0.0477   0.0372   1.0000
  12.750   1.4754   0.06616   0.05847  -0.0455   0.0374   1.0000
  13.000   1.4678   0.06937   0.06197  -0.0435   0.0376   1.0000
  13.250   1.4568   0.07291   0.06584  -0.0419   0.0378   1.0000
  13.500   1.4428   0.07682   0.07005  -0.0408   0.0379   1.0000
  13.750   1.4260   0.08110   0.07462  -0.0404   0.0381   1.0000
  14.000   1.4064   0.08589   0.07972  -0.0408   0.0385   1.0000
  14.250   1.3834   0.09156   0.08571  -0.0424   0.0389   1.0000
  14.500   1.3525   0.09876   0.09322  -0.0458   0.0396   1.0000
  14.750   1.3188   0.10737   0.10216  -0.0511   0.0404   1.0000
  15.000   1.2866   0.11705   0.11210  -0.0576   0.0411   1.0000
  15.250   1.2548   0.12804   0.12332  -0.0656   0.0417   1.0000
  15.500   1.2210   0.14102   0.13646  -0.0753   0.0422   1.0000
  15.750   1.1809   0.15791   0.15344  -0.0875   0.0432   1.0000
  16.000   1.1562   0.17196   0.16745  -0.0962   0.0449   1.0000
  16.250   1.1524   0.17886   0.17433  -0.0993   0.0461   1.0000
  16.500   1.1242   0.20091   0.19626  -0.1124   0.0555   1.0000
  16.750   0.8491   0.17886   0.17452  -0.0785   0.0543   1.0000
  17.000   0.8480   0.18309   0.17876  -0.0797   0.0559   1.0000
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