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GOE 15 AIRFOIL (goe15-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 15 AIRFOIL (goe15-il)
Reynolds number: 200,000
Max Cl/Cd: 70.72 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe15-il-200000.txt
Download as CSV file: xf-goe15-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 15 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.1991   0.12519   0.12185  -0.0327   1.0000   0.0298
 -10.250  -0.2009   0.12277   0.11949  -0.0304   1.0000   0.0299
 -10.000  -0.2081   0.12130   0.11810  -0.0274   0.9999   0.0301
  -9.750  -0.1853   0.11694   0.11373  -0.0321   0.9963   0.0306
  -9.500  -0.1631   0.11299   0.10977  -0.0371   0.9917   0.0311
  -9.250  -0.1410   0.10916   0.10593  -0.0420   0.9862   0.0318
  -9.000  -0.1178   0.10533   0.10209  -0.0475   0.9811   0.0326
  -8.750  -0.0955   0.10227   0.09901  -0.0536   0.9726   0.0333
  -8.250  -0.0514   0.09483   0.09155  -0.0644   0.9574   0.0337
  -8.000  -0.0283   0.09061   0.08732  -0.0680   0.9505   0.0341
  -7.750  -0.0022   0.08680   0.08350  -0.0732   0.9428   0.0346
  -7.500   0.0237   0.08322   0.07988  -0.0787   0.9333   0.0353
  -7.250   0.0515   0.07967   0.07628  -0.0849   0.9239   0.0362
  -7.000   0.0748   0.07708   0.07362  -0.0910   0.9095   0.0372
  -6.750   0.0981   0.07569   0.07212  -0.0988   0.8928   0.0375
  -6.500   0.1150   0.07294   0.06931  -0.1015   0.8796   0.0376
  -6.250   0.1308   0.06904   0.06537  -0.1014   0.8705   0.0379
  -6.000   0.1420   0.06663   0.06292  -0.1014   0.8574   0.0382
  -5.750   0.1559   0.06441   0.06065  -0.1024   0.8460   0.0387
  -5.500   0.1725   0.06221   0.05837  -0.1038   0.8362   0.0394
  -5.250   0.1872   0.06026   0.05638  -0.1048   0.8249   0.0404
  -5.000   0.2067   0.05830   0.05431  -0.1068   0.8156   0.0412
  -4.750   0.2347   0.05736   0.05320  -0.1108   0.8050   0.0419
  -4.500   0.2598   0.05575   0.05144  -0.1136   0.7953   0.0421
  -4.250   0.2716   0.05246   0.04814  -0.1125   0.7866   0.0423
  -4.000   0.2867   0.05005   0.04569  -0.1122   0.7769   0.0427
  -3.750   0.3067   0.04796   0.04348  -0.1128   0.7681   0.0433
  -3.500   0.3267   0.04616   0.04163  -0.1133   0.7580   0.0443
  -3.250   0.3516   0.04442   0.03972  -0.1144   0.7494   0.0455
  -3.000   0.3840   0.04375   0.03884  -0.1162   0.7384   0.0469
  -2.750   0.4142   0.04260   0.03743  -0.1175   0.7288   0.0472
  -2.500   0.4286   0.03982   0.03466  -0.1167   0.7180   0.0475
  -2.250   0.4470   0.03786   0.03264  -0.1163   0.7069   0.0481
  -2.000   0.4700   0.03627   0.03089  -0.1163   0.6965   0.0490
  -1.750   0.4922   0.03490   0.02945  -0.1160   0.6834   0.0502
  -1.500   0.5315   0.03578   0.02989  -0.1164   0.6702   0.0529
  -1.250   0.5494   0.03321   0.02728  -0.1158   0.6573   0.0532
  -1.000   0.5677   0.03121   0.02520  -0.1151   0.6433   0.0539
  -0.750   0.5884   0.02984   0.02374  -0.1143   0.6271   0.0549
  -0.500   0.6112   0.02875   0.02250  -0.1136   0.6106   0.0565
  -0.250   0.6454   0.02965   0.02294  -0.1127   0.5942   0.0596
   0.000   0.6642   0.02741   0.02064  -0.1121   0.5796   0.0602
   0.250   0.6840   0.02596   0.01912  -0.1114   0.5658   0.0615
   0.500   0.7074   0.02518   0.01817  -0.1107   0.5535   0.0645
   0.750   0.7370   0.02535   0.01793  -0.1098   0.5426   0.0679
   1.000   0.7578   0.02386   0.01643  -0.1093   0.5326   0.0693
   1.250   0.7820   0.02319   0.01556  -0.1088   0.5246   0.0721
   1.500   0.8100   0.02331   0.01544  -0.1079   0.5159   0.0772
   1.750   0.8327   0.02215   0.01419  -0.1076   0.5089   0.0797
   2.000   0.8597   0.02232   0.01415  -0.1068   0.5017   0.0876
   2.250   0.8825   0.02126   0.01307  -0.1065   0.4953   0.0919
   2.500   0.9096   0.02110   0.01268  -0.1061   0.4900   0.1002
   2.750   0.9347   0.02103   0.01252  -0.1054   0.4841   0.1110
   3.000   0.9595   0.02068   0.01207  -0.1049   0.4785   0.1236
   3.250   0.9852   0.02004   0.01133  -0.1050   0.4736   0.1392
   3.500   1.0079   0.01954   0.01089  -0.1044   0.4686   0.1696
   3.750   1.0319   0.01912   0.01047  -0.1040   0.4637   0.2055
   4.000   1.0582   0.01916   0.01038  -0.1036   0.4591   0.2285
   4.250   1.0839   0.01879   0.01004  -0.1033   0.4543   0.2417
   4.500   1.1083   0.01870   0.00997  -0.1024   0.4485   0.2414
   4.750   1.1353   0.01897   0.01006  -0.1016   0.4427   0.2101
   5.000   1.1624   0.01950   0.01037  -0.1007   0.4370   0.1643
   5.250   1.1859   0.01950   0.01040  -0.0995   0.4314   0.1325
   5.500   1.2111   0.01954   0.01041  -0.0988   0.4267   0.1167
   5.750   1.2385   0.01984   0.01055  -0.0986   0.4225   0.1110
   6.000   1.2599   0.01996   0.01078  -0.0974   0.4180   0.1103
   6.250   1.2818   0.01998   0.01090  -0.0963   0.4132   0.1087
   6.500   1.3055   0.02007   0.01100  -0.0956   0.4085   0.1082
   6.750   1.3319   0.02039   0.01123  -0.0955   0.4042   0.1097
   7.000   1.3507   0.02049   0.01149  -0.0940   0.3997   0.1142
   7.250   1.3727   0.02071   0.01173  -0.0930   0.3949   0.1171
   7.500   1.3971   0.02097   0.01193  -0.0925   0.3905   0.1214
   7.750   1.4222   0.02136   0.01226  -0.0922   0.3859   0.1320
   8.000   1.4397   0.02157   0.01265  -0.0905   0.3806   0.1567
   8.250   1.4845   0.02099   0.01310  -0.0947   0.3742   1.0000
   8.500   1.5092   0.02142   0.01340  -0.0943   0.3695   1.0000
   8.750   1.5231   0.02172   0.01386  -0.0920   0.3641   1.0000
   9.000   1.5417   0.02200   0.01418  -0.0905   0.3587   1.0000
   9.250   1.5646   0.02232   0.01442  -0.0899   0.3538   1.0000
   9.500   1.5773   0.02269   0.01494  -0.0874   0.3479   1.0000
   9.750   1.5924   0.02295   0.01526  -0.0854   0.3418   1.0000
  10.000   1.6130   0.02326   0.01549  -0.0844   0.3362   1.0000
  10.250   1.6189   0.02360   0.01602  -0.0808   0.3293   1.0000
  10.500   1.6299   0.02383   0.01626  -0.0781   0.3230   1.0000
  10.750   1.6360   0.02421   0.01669  -0.0746   0.3160   1.0000
  11.000   1.6399   0.02456   0.01713  -0.0709   0.3086   1.0000
  11.250   1.6464   0.02504   0.01761  -0.0678   0.3012   1.0000
  11.500   1.6496   0.02563   0.01829  -0.0645   0.2932   1.0000
  11.750   1.6557   0.02631   0.01897  -0.0618   0.2858   1.0000
  12.000   1.6589   0.02715   0.01989  -0.0590   0.2776   1.0000
  12.250   1.6638   0.02808   0.02083  -0.0565   0.2700   1.0000
  12.500   1.6667   0.02917   0.02200  -0.0541   0.2619   1.0000
  12.750   1.6704   0.03035   0.02321  -0.0519   0.2544   1.0000
  13.000   1.6725   0.03170   0.02461  -0.0498   0.2465   1.0000
  13.250   1.6753   0.03314   0.02607  -0.0479   0.2396   1.0000
  13.500   1.6774   0.03471   0.02773  -0.0462   0.2325   1.0000
  13.750   1.6791   0.03639   0.02939  -0.0446   0.2261   1.0000
  14.000   1.6795   0.03828   0.03142  -0.0432   0.2192   1.0000
  14.250   1.6803   0.04018   0.03329  -0.0418   0.2135   1.0000
  14.500   1.6802   0.04229   0.03555  -0.0407   0.2074   1.0000
  14.750   1.6789   0.04455   0.03785  -0.0397   0.2016   1.0000
  15.000   1.6771   0.04693   0.04027  -0.0387   0.1960   1.0000
  15.250   1.6744   0.04955   0.04303  -0.0380   0.1901   1.0000
  15.500   1.6707   0.05227   0.04574  -0.0373   0.1848   1.0000
  15.750   1.6671   0.05518   0.04880  -0.0369   0.1795   1.0000
  16.000   1.6618   0.05837   0.05210  -0.0367   0.1741   1.0000
  16.250   1.6567   0.06151   0.05522  -0.0364   0.1691   1.0000
  16.500   1.6492   0.06530   0.05921  -0.0367   0.1635   1.0000
  16.750   1.6411   0.06919   0.06318  -0.0371   0.1581   1.0000
  17.000   1.6333   0.07311   0.06714  -0.0375   0.1532   1.0000
  17.250   1.6244   0.07746   0.07168  -0.0384   0.1475   1.0000
  17.500   1.6121   0.08225   0.07650  -0.0394   0.1417   1.0000
  17.750   1.6021   0.08698   0.08141  -0.0406   0.1358   1.0000
  18.000   1.5882   0.09230   0.08679  -0.0421   0.1292   1.0000
  18.250   1.5749   0.09765   0.09227  -0.0437   0.1217   1.0000
  18.500   1.5585   0.10353   0.09819  -0.0456   0.1147   1.0000
  18.750   1.5421   0.10958   0.10432  -0.0477   0.1046   1.0000
  19.000   1.5266   0.11549   0.11028  -0.0498   0.0956   1.0000
  19.250   1.5069   0.12218   0.11697  -0.0525   0.0852   1.0000
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