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GOE 57 AIRFOIL (goe57-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 57 AIRFOIL (goe57-il)
Reynolds number: 200,000
Max Cl/Cd: 82.43 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe57-il-200000.txt
Download as CSV file: xf-goe57-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.750  -0.3318   0.08983   0.08676  -0.0179   1.0000   0.0350
  -6.500  -0.3379   0.08827   0.08525  -0.0160   1.0000   0.0354
  -6.250  -0.3419   0.08654   0.08357  -0.0148   1.0000   0.0360
  -6.000  -0.3433   0.08461   0.08166  -0.0143   1.0000   0.0367
  -5.750  -0.3148   0.08053   0.07754  -0.0213   0.9963   0.0390
  -5.500  -0.2388   0.07681   0.07359  -0.0458   0.9893   0.0426
  -5.250  -0.2048   0.07023   0.06694  -0.0539   0.9854   0.0431
  -5.000  -0.1903   0.06534   0.06209  -0.0536   0.9827   0.0441
  -4.750  -0.1683   0.06196   0.05870  -0.0553   0.9774   0.0455
  -4.500  -0.1336   0.05849   0.05516  -0.0606   0.9735   0.0485
  -4.250  -0.0578   0.05543   0.05171  -0.0764   0.9695   0.0546
  -4.000  -0.0201   0.05011   0.04620  -0.0827   0.9633   0.0555
  -3.750   0.0060   0.04584   0.04201  -0.0852   0.9598   0.0571
  -3.500   0.0434   0.04292   0.03903  -0.0892   0.9558   0.0603
  -3.250   0.0877   0.03996   0.03589  -0.0945   0.9486   0.0653
  -3.000   0.1511   0.03573   0.03125  -0.1035   0.9450   0.0704
  -2.750   0.1883   0.03300   0.02851  -0.1067   0.9377   0.0732
  -2.500   0.2414   0.03123   0.02621  -0.1117   0.9322   0.0839
  -2.250   0.2729   0.02823   0.02330  -0.1139   0.9263   0.0863
  -2.000   0.3065   0.02651   0.02149  -0.1155   0.9186   0.0915
  -1.750   0.3435   0.02465   0.01934  -0.1174   0.9104   0.1002
  -1.500   0.3795   0.02361   0.01799  -0.1186   0.9015   0.1126
  -1.250   0.4057   0.02177   0.01620  -0.1187   0.8899   0.1170
  -1.000   0.4350   0.02063   0.01490  -0.1189   0.8787   0.1301
  -0.750   0.4629   0.01964   0.01382  -0.1189   0.8674   0.1471
  -0.250   0.5298   0.01602   0.00913  -0.1175   0.8442   0.0801
   0.000   0.5575   0.01489   0.00780  -0.1168   0.8304   0.0762
   0.250   0.5849   0.01408   0.00679  -0.1161   0.8160   0.0750
   0.500   0.6118   0.01348   0.00607  -0.1153   0.8012   0.0758
   0.750   0.6384   0.01313   0.00561  -0.1146   0.7850   0.0801
   1.000   0.6648   0.01279   0.00516  -0.1137   0.7666   0.0827
   1.250   0.6905   0.01219   0.00458  -0.1129   0.7457   0.0859
   1.500   0.7165   0.01189   0.00425  -0.1121   0.7243   0.0918
   1.750   0.7424   0.01162   0.00396  -0.1114   0.7008   0.1007
   2.000   0.7682   0.01146   0.00376  -0.1107   0.6758   0.1215
   2.250   0.7911   0.00970   0.00364  -0.1095   0.6510   1.0000
   2.500   0.8163   0.00994   0.00358  -0.1086   0.6232   1.0000
   2.750   0.8411   0.01021   0.00364  -0.1077   0.5939   1.0000
   3.000   0.8655   0.01050   0.00374  -0.1068   0.5618   1.0000
   3.250   0.8895   0.01081   0.00388  -0.1059   0.5242   1.0000
   3.500   0.9125   0.01121   0.00404  -0.1049   0.4810   1.0000
   3.750   0.9346   0.01172   0.00427  -0.1037   0.4353   1.0000
   4.000   0.9562   0.01232   0.00458  -0.1026   0.3891   1.0000
   4.250   0.9774   0.01299   0.00498  -0.1015   0.3429   1.0000
   4.500   0.9994   0.01363   0.00539  -0.1005   0.3054   1.0000
   4.750   1.0220   0.01422   0.00580  -0.0996   0.2826   1.0000
   5.000   1.0455   0.01470   0.00616  -0.0989   0.2645   1.0000
   5.250   1.0691   0.01515   0.00653  -0.0983   0.2492   1.0000
   5.500   1.0927   0.01558   0.00690  -0.0976   0.2373   1.0000
   5.750   1.1160   0.01603   0.00727  -0.0969   0.2261   1.0000
   6.000   1.1396   0.01644   0.00765  -0.0963   0.2148   1.0000
   6.250   1.1631   0.01684   0.00803  -0.0957   0.2027   1.0000
   6.500   1.1865   0.01725   0.00849  -0.0950   0.1937   1.0000
   6.750   1.2091   0.01773   0.00895  -0.0942   0.1828   1.0000
   7.000   1.2314   0.01822   0.00941  -0.0934   0.1694   1.0000
   7.250   1.2546   0.01863   0.00984  -0.0927   0.1539   1.0000
   7.500   1.2790   0.01895   0.01022  -0.0921   0.1310   1.0000
   8.000   1.3078   0.02196   0.01256  -0.0882   0.0311   1.0000
   8.250   1.3266   0.02291   0.01362  -0.0867   0.0283   1.0000
   8.500   1.3447   0.02387   0.01476  -0.0852   0.0264   1.0000
   8.750   1.3607   0.02495   0.01605  -0.0834   0.0249   1.0000
   9.000   1.3742   0.02616   0.01743  -0.0813   0.0242   1.0000
   9.250   1.3841   0.02751   0.01894  -0.0788   0.0236   1.0000
   9.500   1.3897   0.02899   0.02054  -0.0757   0.0233   1.0000
   9.750   1.3921   0.03059   0.02224  -0.0723   0.0230   1.0000
  10.000   1.3944   0.03233   0.02409  -0.0690   0.0228   1.0000
  10.250   1.3969   0.03420   0.02606  -0.0661   0.0227   1.0000
  10.500   1.4007   0.03614   0.02809  -0.0635   0.0227   1.0000
  10.750   1.4062   0.03811   0.03018  -0.0611   0.0228   1.0000
  11.000   1.4132   0.04022   0.03237  -0.0590   0.0227   1.0000
  11.250   1.4230   0.04271   0.03492  -0.0570   0.0223   1.0000
  11.500   1.4408   0.04585   0.03814  -0.0557   0.0219   1.0000
  11.750   1.4541   0.04802   0.04047  -0.0542   0.0220   1.0000
  12.000   1.4635   0.04995   0.04256  -0.0524   0.0223   1.0000
  12.250   1.4691   0.05194   0.04478  -0.0505   0.0227   1.0000
  12.500   1.4730   0.05450   0.04769  -0.0484   0.0237   1.0000
  12.750   1.4711   0.05868   0.05234  -0.0462   0.0254   1.0000
  13.000   1.4666   0.06322   0.05723  -0.0444   0.0269   1.0000
  13.250   1.3079   0.06045   0.05456  -0.0313   0.0237   1.0000
  13.500   1.2934   0.06547   0.05990  -0.0301   0.0246   1.0000
  13.750   1.2757   0.07076   0.06547  -0.0295   0.0252   1.0000
  14.000   1.2557   0.07610   0.07106  -0.0294   0.0258   1.0000
  14.250   1.2336   0.08152   0.07671  -0.0297   0.0262   1.0000
  14.500   1.2098   0.08698   0.08238  -0.0306   0.0265   1.0000
  14.750   1.1825   0.09226   0.08785  -0.0319   0.0267   1.0000
  15.000   1.1525   0.09734   0.09313  -0.0335   0.0268   1.0000
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