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GOE 386 AIRFOIL (goe386-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 386 AIRFOIL (goe386-il)
Reynolds number: 50,000
Max Cl/Cd: 16.22 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe386-il-50000-n5.txt
Download as CSV file: xf-goe386-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 386 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.1981   0.16102   0.15332  -0.0444   1.0000   0.1551
 -13.250  -0.2035   0.15961   0.15199  -0.0440   1.0000   0.1553
 -13.000  -0.2102   0.15825   0.15073  -0.0433   1.0000   0.1555
 -12.750  -0.2135   0.15641   0.14899  -0.0422   1.0000   0.1558
 -12.500  -0.2012   0.15343   0.14610  -0.0400   1.0000   0.1573
 -12.250  -0.1964   0.15139   0.14414  -0.0392   0.9988   0.1588
 -11.750  -0.1790   0.13846   0.13104  -0.0510   0.9848   0.1207
 -11.500  -0.1609   0.13369   0.12625  -0.0558   0.9782   0.1175
 -11.000  -0.1490   0.12293   0.11541  -0.0667   0.9627   0.1132
 -10.750  -0.1332   0.11872   0.11119  -0.0703   0.9527   0.1127
 -10.500  -0.1146   0.11402   0.10646  -0.0752   0.9464   0.1118
 -10.250  -0.1053   0.10964   0.10206  -0.0787   0.9347   0.1115
 -10.000  -0.0963   0.10472   0.09712  -0.0833   0.9258   0.1120
  -9.750  -0.0921   0.09994   0.09231  -0.0871   0.9137   0.1123
  -9.500  -0.0890   0.09511   0.08747  -0.0907   0.9017   0.1124
  -9.250  -0.0859   0.09000   0.08231  -0.0946   0.8906   0.1122
  -9.000  -0.0935   0.08480   0.07710  -0.0976   0.8756   0.1124
  -8.750  -0.1147   0.07754   0.06978  -0.1025   0.8616   0.1128
  -8.500  -0.1681   0.06737   0.05942  -0.1089   0.8452   0.1127
  -8.250  -0.2157   0.06067   0.05239  -0.1095   0.8281   0.1128
  -8.000  -0.2453   0.05580   0.04711  -0.1083   0.8130   0.1133
  -7.750  -0.2357   0.05292   0.04400  -0.1085   0.8052   0.1143
  -7.500  -0.2317   0.05134   0.04229  -0.1067   0.7922   0.1153
  -7.250  -0.2142   0.04931   0.04006  -0.1067   0.7853   0.1171
  -7.000  -0.2096   0.04760   0.03811  -0.1050   0.7739   0.1188
  -6.750  -0.1968   0.04506   0.03515  -0.1046   0.7668   0.1211
  -6.500  -0.1840   0.04326   0.03301  -0.1036   0.7587   0.1230
  -6.250  -0.1653   0.04247   0.03216  -0.1026   0.7508   0.1247
  -6.000  -0.1403   0.04128   0.03082  -0.1027   0.7456   0.1272
  -5.750  -0.1233   0.04027   0.02956  -0.1016   0.7384   0.1301
  -5.500  -0.1058   0.03930   0.02835  -0.1006   0.7310   0.1331
  -5.250  -0.0784   0.03858   0.02760  -0.1006   0.7260   0.1360
  -5.000  -0.0529   0.03774   0.02658  -0.1004   0.7210   0.1394
  -4.750  -0.0390   0.03733   0.02595  -0.0987   0.7131   0.1432
  -4.500  -0.0148   0.03697   0.02563  -0.0983   0.7080   0.1470
  -4.250   0.0145   0.03627   0.02478  -0.0985   0.7042   0.1528
  -4.000   0.0360   0.03595   0.02438  -0.0977   0.6988   0.1577
  -3.750   0.0510   0.03604   0.02448  -0.0961   0.6917   0.1629
  -3.500   0.0768   0.03563   0.02399  -0.0958   0.6869   0.1713
  -3.250   0.1072   0.03514   0.02341  -0.0960   0.6834   0.1824
  -3.000   0.1309   0.03498   0.02330  -0.0955   0.6791   0.1937
  -2.750   0.1400   0.03549   0.02385  -0.0932   0.6715   0.2049
  -2.500   0.1642   0.03539   0.02375  -0.0927   0.6666   0.2224
  -2.250   0.1951   0.03506   0.02340  -0.0930   0.6629   0.2428
  -2.000   0.2304   0.03465   0.02294  -0.0939   0.6599   0.2645
  -1.750   0.2272   0.03587   0.02422  -0.0901   0.6498   0.2751
  -1.500   0.2556   0.03564   0.02398  -0.0899   0.6439   0.2970
  -1.250   0.2944   0.03497   0.02324  -0.0908   0.6397   0.3226
  -1.000   0.2988   0.03579   0.02418  -0.0878   0.6298   0.3355
  -0.750   0.3244   0.03565   0.02406  -0.0872   0.6230   0.3561
  -0.500   0.3616   0.03502   0.02342  -0.0880   0.6186   0.3823
  -0.250   0.3741   0.03556   0.02407  -0.0860   0.6112   0.4039
   0.000   0.3853   0.03613   0.02478  -0.0838   0.6032   0.4290
   0.250   0.4162   0.03567   0.02448  -0.0838   0.5984   0.4712
   0.500   0.4525   0.03480   0.02389  -0.0840   0.5950   0.5367
   0.750   0.4384   0.03648   0.02592  -0.0789   0.5839   0.5788
   1.000   0.4584   0.03616   0.02613  -0.0763   0.5782   0.7049
   1.250   0.5393   0.03523   0.02537  -0.0829   0.5743   0.9549
   1.500   0.5434   0.03670   0.02676  -0.0809   0.5645   1.0000
   1.750   0.5546   0.03736   0.02726  -0.0787   0.5569   1.0000
   2.000   0.5918   0.03703   0.02666  -0.0795   0.5527   1.0000
   2.250   0.5704   0.03908   0.02870  -0.0737   0.5415   1.0000
   2.500   0.5880   0.03955   0.02901  -0.0723   0.5345   1.0000
   2.750   0.6299   0.03903   0.02826  -0.0736   0.5307   1.0000
   3.250   0.6251   0.04196   0.03107  -0.0669   0.5117   1.0000
   3.500   0.6683   0.04121   0.03011  -0.0679   0.5087   1.0000
   4.000   0.6671   0.04447   0.03328  -0.0626   0.4895   1.0000
   4.500   0.6688   0.04831   0.03705  -0.0587   0.4706   1.0000
   4.750   0.7071   0.04752   0.03609  -0.0588   0.4683   1.0000
   5.250   0.6949   0.05307   0.04162  -0.0552   0.4480   1.0000
   5.750   0.7041   0.05740   0.04587  -0.0533   0.4323   1.0000
   6.750   0.6909   0.07109   0.05954  -0.0510   0.3996   1.0000
   7.000   0.7166   0.07121   0.05958  -0.0505   0.3975   1.0000
   7.500   0.6985   0.08011   0.06852  -0.0502   0.3826   1.0000
   7.750   0.7227   0.08044   0.06879  -0.0497   0.3805   1.0000
   8.250   0.6983   0.09044   0.07886  -0.0500   0.3666   1.0000
   8.500   0.7188   0.09137   0.07975  -0.0497   0.3643   1.0000
   8.750   0.7434   0.09176   0.08008  -0.0492   0.3626   1.0000
   9.000   0.6993   0.10091   0.08937  -0.0504   0.3522   1.0000
   9.250   0.7113   0.10300   0.09145  -0.0503   0.3491   1.0000
   9.500   0.7299   0.10425   0.09266  -0.0501   0.3469   1.0000
   9.750   0.7506   0.10523   0.09360  -0.0498   0.3449   1.0000
  10.000   0.7123   0.11373   0.10224  -0.0514   0.3360   1.0000
  10.250   0.7215   0.11623   0.10474  -0.0515   0.3327   1.0000
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