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GOE 387 AIRFOIL (goe387-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 387 AIRFOIL (goe387-il)
Reynolds number: 100,000
Max Cl/Cd: 43.6 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe387-il-100000.txt
Download as CSV file: xf-goe387-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 387 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.2241   0.13663   0.13159  -0.0453   1.0000   0.0927
 -11.500  -0.2506   0.13772   0.13282  -0.0452   1.0000   0.0933
 -11.250  -0.2797   0.13897   0.13424  -0.0428   1.0000   0.0935
 -11.000  -0.2575   0.13343   0.12874  -0.0380   1.0000   0.0945
 -10.750  -0.2662   0.13278   0.12819  -0.0337   1.0000   0.0952
 -10.500  -0.2732   0.13205   0.12754  -0.0306   0.9997   0.0963
 -10.250  -0.2484   0.12783   0.12330  -0.0352   0.9950   0.0995
 -10.000  -0.2331   0.12423   0.11969  -0.0413   0.9891   0.1035
  -9.750  -0.2521   0.12326   0.11877  -0.0546   0.9794   0.1058
  -9.500  -0.2021   0.11582   0.11128  -0.0520   0.9774   0.1079
  -9.250  -0.1737   0.11182   0.10725  -0.0551   0.9726   0.1114
  -9.000  -0.1608   0.10870   0.10413  -0.0608   0.9652   0.1171
  -8.750  -0.1647   0.10528   0.10074  -0.0708   0.9569   0.1202
  -8.500  -0.1234   0.10049   0.09591  -0.0699   0.9536   0.1233
  -8.250  -0.1033   0.09724   0.09265  -0.0727   0.9461   0.1276
  -8.000  -0.1177   0.09568   0.09112  -0.0823   0.9333   0.1339
  -7.750  -0.0937   0.09041   0.08585  -0.0852   0.9287   0.1361
  -7.500  -0.0518   0.08627   0.08167  -0.0867   0.9269   0.1403
  -7.250  -0.0394   0.08353   0.07892  -0.0901   0.9184   0.1461
  -7.000  -0.0573   0.07990   0.07528  -0.1008   0.9060   0.1518
  -6.750  -0.0321   0.07731   0.07272  -0.0969   0.8991   0.1543
  -6.500  -0.0062   0.07430   0.06969  -0.0989   0.8935   0.1600
  -6.250  -0.0445   0.07260   0.06787  -0.1052   0.8765   0.1685
  -6.000  -0.0028   0.06871   0.06405  -0.1041   0.8745   0.1716
  -5.750   0.0193   0.06622   0.06153  -0.1055   0.8691   0.1799
  -5.500   0.0021   0.06425   0.05947  -0.1064   0.8562   0.1876
  -5.250   0.0379   0.06148   0.05672  -0.1067   0.8532   0.1952
  -5.000   0.0163   0.06049   0.05562  -0.1052   0.8395   0.2056
  -4.750   0.0489   0.05769   0.05285  -0.1054   0.8359   0.2121
  -4.500   0.0338   0.05692   0.05197  -0.1030   0.8234   0.2241
  -4.250   0.0627   0.05427   0.04933  -0.1032   0.8190   0.2308
  -4.000   0.0366   0.04334   0.03682  -0.1050   0.8059   0.1215
  -3.750   0.0625   0.03881   0.03164  -0.1047   0.8011   0.1019
  -3.500   0.0967   0.03539   0.02722  -0.1049   0.7979   0.0931
  -3.250   0.0940   0.03515   0.02691  -0.1002   0.7859   0.0924
  -3.000   0.1324   0.03305   0.02450  -0.1013   0.7820   0.0915
  -2.750   0.1755   0.03127   0.02233  -0.1029   0.7790   0.0925
  -2.500   0.1755   0.03145   0.02241  -0.0984   0.7666   0.0928
  -2.250   0.2185   0.02987   0.02056  -0.0999   0.7629   0.0934
  -2.000   0.2318   0.02957   0.02023  -0.0973   0.7535   0.0939
  -1.750   0.2645   0.02847   0.01912  -0.0975   0.7475   0.0955
  -1.500   0.3067   0.02720   0.01785  -0.0990   0.7438   0.0986
  -1.250   0.3141   0.02747   0.01815  -0.0955   0.7330   0.1009
  -1.000   0.3495   0.02660   0.01725  -0.0959   0.7280   0.1072
  -0.750   0.3902   0.02559   0.01625  -0.0971   0.7244   0.1196
  -0.500   0.3935   0.02601   0.01678  -0.0931   0.7125   0.1282
  -0.250   0.4308   0.02426   0.01591  -0.0940   0.7083   0.3149
   0.000   0.5857   0.02151   0.01467  -0.1167   0.7044   1.0000
   0.250   0.5972   0.02199   0.01503  -0.1138   0.6940   1.0000
   0.500   0.6331   0.02167   0.01444  -0.1144   0.6888   1.0000
   0.750   0.6418   0.02229   0.01498  -0.1112   0.6778   1.0000
   1.000   0.6761   0.02199   0.01446  -0.1115   0.6718   1.0000
   1.250   0.6888   0.02250   0.01489  -0.1088   0.6614   1.0000
   1.500   0.7204   0.02232   0.01452  -0.1089   0.6547   1.0000
   1.750   0.7368   0.02275   0.01488  -0.1068   0.6454   1.0000
   2.000   0.7643   0.02274   0.01473  -0.1062   0.6379   1.0000
   2.250   0.7866   0.02297   0.01485  -0.1050   0.6296   1.0000
   2.500   0.8094   0.02312   0.01491  -0.1038   0.6208   1.0000
   2.750   0.8387   0.02312   0.01478  -0.1036   0.6139   1.0000
   3.000   0.8541   0.02355   0.01518  -0.1013   0.6040   1.0000
   3.250   0.8924   0.02330   0.01473  -0.1025   0.5988   1.0000
   3.500   0.8970   0.02417   0.01567  -0.0988   0.5878   1.0000
   3.750   0.9327   0.02400   0.01535  -0.0996   0.5822   1.0000
   4.000   0.9403   0.02483   0.01622  -0.0964   0.5724   1.0000
   4.250   0.9721   0.02476   0.01603  -0.0966   0.5661   1.0000
   4.500   0.9869   0.02537   0.01665  -0.0945   0.5580   1.0000
   4.750   1.0102   0.02561   0.01684  -0.0935   0.5507   1.0000
   5.000   1.0457   0.02551   0.01660  -0.0944   0.5454   1.0000
   5.250   1.0480   0.02653   0.01773  -0.0905   0.5362   1.0000
   5.500   1.0865   0.02615   0.01722  -0.0917   0.5304   1.0000
   5.750   1.0917   0.02705   0.01820  -0.0882   0.5216   1.0000
   6.000   1.1224   0.02696   0.01802  -0.0884   0.5152   1.0000
   6.250   1.1423   0.02740   0.01846  -0.0870   0.5086   1.0000
   6.500   1.1568   0.02793   0.01903  -0.0849   0.5010   1.0000
   6.750   1.1995   0.02751   0.01844  -0.0868   0.4956   1.0000
   7.000   1.1955   0.02873   0.01984  -0.0821   0.4874   1.0000
   7.250   1.2246   0.02882   0.01989  -0.0822   0.4817   1.0000
   7.500   1.2503   0.02920   0.02023  -0.0818   0.4764   1.0000
   7.750   1.2508   0.03035   0.02152  -0.0779   0.4694   1.0000
   8.000   1.2859   0.03026   0.02138  -0.0788   0.4639   1.0000
   8.250   1.2968   0.03113   0.02232  -0.0765   0.4578   1.0000
   8.500   1.3054   0.03194   0.02320  -0.0737   0.4510   1.0000
   8.750   1.3542   0.03146   0.02260  -0.0766   0.4455   1.0000
   9.000   1.3385   0.03314   0.02449  -0.0705   0.4386   1.0000
   9.250   1.3612   0.03348   0.02484  -0.0698   0.4323   1.0000
   9.500   1.3976   0.03354   0.02485  -0.0710   0.4265   1.0000
   9.750   1.3758   0.03531   0.02682  -0.0642   0.4196   1.0000
  10.000   1.4253   0.03483   0.02627  -0.0671   0.4130   1.0000
  10.250   1.4123   0.03638   0.02795  -0.0616   0.4066   1.0000
  10.500   1.4196   0.03716   0.02879  -0.0588   0.3994   1.0000
  10.750   1.4576   0.03708   0.02869  -0.0601   0.3920   1.0000
  11.000   1.4301   0.03908   0.03085  -0.0532   0.3848   1.0000
  11.250   1.4912   0.03800   0.02962  -0.0570   0.3762   1.0000
  11.500   1.4479   0.04074   0.03259  -0.0488   0.3692   1.0000
  11.750   1.5122   0.03921   0.03089  -0.0525   0.3597   1.0000
  12.000   1.4645   0.04243   0.03437  -0.0446   0.3529   1.0000
  12.250   1.5257   0.04068   0.03241  -0.0475   0.3430   1.0000
  12.500   1.4769   0.04430   0.03630  -0.0404   0.3364   1.0000
  12.750   1.5398   0.04228   0.03407  -0.0431   0.3269   1.0000
  13.000   1.4843   0.04668   0.03876  -0.0364   0.3209   1.0000
  13.250   1.5458   0.04457   0.03646  -0.0385   0.3124   1.0000
  13.500   1.4966   0.04916   0.04134  -0.0332   0.3069   1.0000
  13.750   1.4807   0.05205   0.04435  -0.0308   0.3006   1.0000
  14.000   1.5287   0.05048   0.04268  -0.0314   0.2938   1.0000
  14.250   1.4315   0.06044   0.05302  -0.0269   0.2889   1.0000
  14.500   1.2466   0.08562   0.07842  -0.0283   0.2788   1.0000
  14.750   1.3524   0.07392   0.06674  -0.0254   0.2769   1.0000
  15.250   1.5341   0.05933   0.05189  -0.0246   0.2641   1.0000
  15.500   1.0061   0.14224   0.13519  -0.0461   0.2350   1.0000
  15.750   0.9644   0.15361   0.14659  -0.0512   0.2240   1.0000
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