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GOE 515 AIRFOIL (goe515-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 515 AIRFOIL (goe515-il)
Reynolds number: 50,000
Max Cl/Cd: 37.93 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe515-il-50000-n5.txt
Download as CSV file: xf-goe515-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 515 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4555   0.12058   0.11302  -0.0278   1.0000   0.0697
 -10.500  -0.4535   0.11670   0.10917  -0.0291   1.0000   0.0697
 -10.250  -0.4535   0.11277   0.10530  -0.0307   1.0000   0.0698
 -10.000  -0.4509   0.10884   0.10140  -0.0317   1.0000   0.0697
  -9.750  -0.4471   0.10500   0.09759  -0.0323   1.0000   0.0692
  -9.500  -0.4460   0.10116   0.09380  -0.0332   1.0000   0.0689
  -9.250  -0.4481   0.09731   0.09000  -0.0347   1.0000   0.0690
  -9.000  -0.4431   0.09464   0.08736  -0.0343   1.0000   0.0724
  -8.750  -0.4427   0.09154   0.08432  -0.0347   1.0000   0.0738
  -8.500  -0.4465   0.08822   0.08107  -0.0355   1.0000   0.0748
  -8.250  -0.4547   0.08472   0.07768  -0.0363   1.0000   0.0748
  -8.000  -0.4630   0.08076   0.07381  -0.0377   1.0000   0.0745
  -7.750  -0.4699   0.07656   0.06967  -0.0392   1.0000   0.0742
  -7.500  -0.4759   0.07219   0.06533  -0.0405   1.0000   0.0740
  -7.250  -0.4804   0.06791   0.06103  -0.0414   1.0000   0.0742
  -7.000  -0.4823   0.06406   0.05714  -0.0417   1.0000   0.0757
  -6.750  -0.4838   0.06003   0.05299  -0.0419   1.0000   0.0780
  -6.500  -0.4853   0.05533   0.04805  -0.0422   1.0000   0.0799
  -6.250  -0.4853   0.05028   0.04260  -0.0421   1.0000   0.0813
  -6.000  -0.4812   0.04562   0.03743  -0.0415   1.0000   0.0823
  -5.750  -0.4712   0.04285   0.03444  -0.0402   1.0000   0.0838
  -5.500  -0.4584   0.04093   0.03236  -0.0387   1.0000   0.0859
  -5.250  -0.4448   0.03905   0.03023  -0.0374   1.0000   0.0896
  -5.000  -0.4305   0.03622   0.02674  -0.0364   1.0000   0.0953
  -4.750  -0.4144   0.03428   0.02453  -0.0352   1.0000   0.0987
  -4.500  -0.3968   0.03272   0.02275  -0.0340   1.0000   0.1020
  -4.250  -0.3779   0.03099   0.02060  -0.0329   1.0000   0.1065
  -4.000  -0.3575   0.02922   0.01830  -0.0319   1.0000   0.1121
  -3.750  -0.3388   0.02855   0.01763  -0.0309   1.0000   0.1196
  -3.500  -0.3183   0.02761   0.01641  -0.0299   1.0000   0.1289
  -3.250  -0.2974   0.02682   0.01543  -0.0290   1.0000   0.1376
  -3.000  -0.2670   0.02624   0.01472  -0.0300   0.9957   0.1507
  -2.750  -0.2334   0.02569   0.01402  -0.0316   0.9899   0.1647
  -2.500  -0.1985   0.02527   0.01345  -0.0334   0.9843   0.1799
  -2.250  -0.1648   0.02484   0.01289  -0.0348   0.9781   0.1933
  -2.000  -0.1290   0.02451   0.01245  -0.0367   0.9725   0.2077
  -1.750  -0.0941   0.02417   0.01199  -0.0383   0.9662   0.2207
  -1.500  -0.0588   0.02392   0.01170  -0.0401   0.9604   0.2386
  -1.250  -0.0259   0.02363   0.01141  -0.0413   0.9533   0.2567
  -1.000   0.0100   0.02332   0.01119  -0.0433   0.9474   0.2826
  -0.750   0.0398   0.02293   0.01104  -0.0441   0.9395   0.3244
  -0.500   0.1048   0.02068   0.01101  -0.0511   0.9393   1.0000
  -0.250   0.1415   0.02096   0.01094  -0.0531   0.9317   1.0000
   0.000   0.1746   0.02120   0.01094  -0.0543   0.9224   1.0000
   0.250   0.2071   0.02144   0.01099  -0.0554   0.9126   1.0000
   0.500   0.2486   0.02162   0.01102  -0.0581   0.9046   1.0000
   0.750   0.2797   0.02179   0.01109  -0.0588   0.8928   1.0000
   1.000   0.3132   0.02194   0.01115  -0.0599   0.8814   1.0000
   1.250   0.3498   0.02203   0.01120  -0.0614   0.8709   1.0000
   1.500   0.3889   0.02206   0.01120  -0.0632   0.8614   1.0000
   1.750   0.4180   0.02218   0.01132  -0.0633   0.8489   1.0000
   2.000   0.4472   0.02231   0.01146  -0.0633   0.8367   1.0000
   2.250   0.4771   0.02242   0.01160  -0.0634   0.8248   1.0000
   2.500   0.5087   0.02248   0.01171  -0.0637   0.8134   1.0000
   2.750   0.5428   0.02247   0.01178  -0.0643   0.8027   1.0000
   3.000   0.5691   0.02260   0.01199  -0.0637   0.7890   1.0000
   3.250   0.5957   0.02272   0.01220  -0.0630   0.7750   1.0000
   3.500   0.6224   0.02282   0.01242  -0.0623   0.7607   1.0000
   3.750   0.6492   0.02290   0.01262  -0.0615   0.7458   1.0000
   4.000   0.6763   0.02295   0.01280  -0.0608   0.7304   1.0000
   4.250   0.7052   0.02282   0.01282  -0.0599   0.7131   1.0000
   4.500   0.7273   0.02276   0.01287  -0.0579   0.6889   1.0000
   4.750   0.7524   0.02246   0.01265  -0.0560   0.6608   1.0000
   5.000   0.7767   0.02223   0.01249  -0.0540   0.6294   1.0000
   5.250   0.8003   0.02222   0.01254  -0.0522   0.5991   1.0000
   5.500   0.8229   0.02236   0.01276  -0.0504   0.5692   1.0000
   5.750   0.8450   0.02255   0.01300  -0.0486   0.5363   1.0000
   6.000   0.8647   0.02288   0.01339  -0.0465   0.4996   1.0000
   6.250   0.8830   0.02328   0.01372  -0.0441   0.4565   1.0000
   6.500   0.8977   0.02392   0.01415  -0.0414   0.4055   1.0000
   6.750   0.9090   0.02482   0.01481  -0.0384   0.3496   1.0000
   7.000   0.9193   0.02588   0.01566  -0.0356   0.2962   1.0000
   7.250   0.9293   0.02708   0.01665  -0.0330   0.2466   1.0000
   7.500   0.9386   0.02845   0.01782  -0.0304   0.2059   1.0000
   7.750   0.9480   0.03000   0.01914  -0.0280   0.1748   1.0000
   8.000   0.9581   0.03170   0.02069  -0.0258   0.1490   1.0000
   8.250   0.9678   0.03345   0.02231  -0.0237   0.1265   1.0000
   8.500   0.9796   0.03506   0.02398  -0.0217   0.1061   1.0000
   8.750   0.9907   0.03669   0.02567  -0.0197   0.0902   1.0000
   9.000   1.0021   0.03834   0.02738  -0.0177   0.0782   1.0000
   9.250   1.0149   0.04015   0.02924  -0.0160   0.0700   1.0000
   9.500   1.0307   0.04209   0.03135  -0.0145   0.0625   1.0000
   9.750   1.0453   0.04424   0.03360  -0.0131   0.0567   1.0000
  10.000   1.0639   0.04677   0.03645  -0.0120   0.0524   1.0000
  10.250   1.0764   0.04914   0.03897  -0.0106   0.0493   1.0000
  10.500   1.0870   0.05193   0.04182  -0.0093   0.0465   1.0000
  10.750   1.0892   0.05490   0.04528  -0.0070   0.0446   1.0000
  11.000   1.0879   0.05805   0.04880  -0.0049   0.0431   1.0000
  11.250   1.0828   0.06145   0.05252  -0.0030   0.0421   1.0000
  11.500   1.0740   0.06513   0.05650  -0.0015   0.0415   1.0000
  11.750   1.0613   0.06916   0.06082  -0.0005   0.0412   1.0000
  12.000   1.0451   0.07366   0.06559  -0.0003   0.0411   1.0000
  12.250   1.0251   0.07888   0.07105  -0.0011   0.0410   1.0000
  12.500   1.0019   0.08502   0.07742  -0.0032   0.0413   1.0000
  12.750   0.9754   0.09243   0.08502  -0.0070   0.0418   1.0000
  13.000   0.9467   0.10146   0.09419  -0.0125   0.0425   1.0000
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