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GOE 416A AIRFOIL (goe416a-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 416A AIRFOIL (goe416a-il)
Reynolds number: 500,000
Max Cl/Cd: 71 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe416a-il-500000.txt
Download as CSV file: xf-goe416a-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 416A AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.4675   0.13663   0.13446  -0.0010   1.0000   0.0131
 -13.250  -0.4766   0.13206   0.12990  -0.0017   1.0000   0.0136
  -9.250  -0.7442   0.05164   0.04832  -0.0387   1.0000   0.0137
  -9.000  -0.7354   0.04815   0.04478  -0.0390   1.0000   0.0140
  -8.750  -0.7263   0.04514   0.04167  -0.0393   1.0000   0.0143
  -8.500  -0.7156   0.04234   0.03872  -0.0394   1.0000   0.0147
  -8.250  -0.7026   0.03969   0.03589  -0.0392   1.0000   0.0153
  -8.000  -0.6876   0.03717   0.03315  -0.0389   1.0000   0.0161
  -7.750  -0.6700   0.03509   0.03081  -0.0382   1.0000   0.0172
  -7.500  -0.6460   0.03611   0.03153  -0.0371   1.0000   0.0187
  -7.250  -0.6373   0.03060   0.02552  -0.0361   1.0000   0.0196
  -7.000  -0.6194   0.02764   0.02257  -0.0357   1.0000   0.0208
  -6.750  -0.6004   0.02597   0.02084  -0.0348   1.0000   0.0219
  -6.500  -0.5814   0.02458   0.01932  -0.0335   1.0000   0.0233
  -6.250  -0.5622   0.02371   0.01828  -0.0320   1.0000   0.0251
  -6.000  -0.5425   0.02554   0.01991  -0.0300   1.0000   0.0269
  -5.250  -0.4477   0.01665   0.01054  -0.0316   0.9950   0.0196
  -5.000  -0.4127   0.01534   0.00925  -0.0330   0.9919   0.0183
  -4.750  -0.3769   0.01434   0.00821  -0.0347   0.9882   0.0186
  -4.500  -0.3410   0.01303   0.00687  -0.0367   0.9850   0.0195
  -4.250  -0.3056   0.01203   0.00582  -0.0386   0.9803   0.0196
  -4.000  -0.2718   0.01107   0.00476  -0.0401   0.9736   0.0204
  -3.750  -0.2378   0.01044   0.00406  -0.0415   0.9672   0.0218
  -3.500  -0.2068   0.01002   0.00357  -0.0422   0.9580   0.0240
  -3.250  -0.1775   0.00973   0.00320  -0.0424   0.9473   0.0266
  -3.000  -0.1495   0.00946   0.00283  -0.0421   0.9352   0.0323
  -2.750  -0.1272   0.00727   0.00209  -0.0424   0.9220   0.4184
  -2.500  -0.1008   0.00737   0.00227  -0.0418   0.9078   0.4803
  -2.250  -0.0741   0.00745   0.00230  -0.0412   0.8925   0.4955
  -2.000  -0.0471   0.00757   0.00230  -0.0407   0.8758   0.5065
  -1.750  -0.0203   0.00768   0.00238  -0.0402   0.8579   0.5196
  -1.500   0.0067   0.00773   0.00239  -0.0398   0.8395   0.5278
  -1.250   0.0344   0.00784   0.00239  -0.0395   0.8192   0.5360
  -1.000   0.0618   0.00782   0.00231  -0.0393   0.7969   0.5396
  -0.750   0.0895   0.00786   0.00227  -0.0391   0.7733   0.5435
  -0.500   0.1174   0.00793   0.00222  -0.0390   0.7506   0.5472
  -0.250   0.1456   0.00800   0.00217  -0.0390   0.7280   0.5500
   0.000   0.1735   0.00801   0.00210  -0.0389   0.7055   0.5522
   0.250   0.2014   0.00807   0.00208  -0.0389   0.6832   0.5546
   0.500   0.2295   0.00814   0.00208  -0.0389   0.6641   0.5571
   0.750   0.2578   0.00820   0.00208  -0.0390   0.6459   0.5596
   1.000   0.2861   0.00828   0.00209  -0.0391   0.6284   0.5622
   1.250   0.3145   0.00837   0.00211  -0.0392   0.6111   0.5648
   1.500   0.3425   0.00841   0.00213  -0.0392   0.5934   0.5674
   1.750   0.3708   0.00846   0.00217  -0.0393   0.5760   0.5699
   2.000   0.3991   0.00853   0.00222  -0.0394   0.5566   0.5727
   2.250   0.4272   0.00863   0.00226  -0.0395   0.5353   0.5757
   2.500   0.4555   0.00874   0.00231  -0.0396   0.5133   0.5788
   2.750   0.4832   0.00883   0.00237  -0.0396   0.4920   0.5820
   3.000   0.5111   0.00894   0.00248  -0.0397   0.4722   0.5851
   3.250   0.5390   0.00908   0.00259  -0.0397   0.4548   0.5886
   3.500   0.5670   0.00922   0.00271  -0.0398   0.4402   0.5923
   3.750   0.5947   0.00934   0.00284  -0.0399   0.4247   0.5960
   4.000   0.6220   0.00952   0.00300  -0.0399   0.4006   0.6003
   4.250   0.6494   0.00972   0.00315  -0.0399   0.3744   0.6052
   4.500   0.6769   0.00989   0.00330  -0.0399   0.3451   0.6100
   4.750   0.7037   0.01014   0.00348  -0.0399   0.3060   0.6153
   5.000   0.7300   0.01050   0.00372  -0.0398   0.2691   0.6214
   5.250   0.7562   0.01084   0.00402  -0.0397   0.2455   0.6279
   5.500   0.7825   0.01118   0.00433  -0.0396   0.2248   0.6361
   5.750   0.8087   0.01149   0.00465  -0.0395   0.2039   0.6459
   6.000   0.8350   0.01176   0.00494  -0.0395   0.1792   0.6588
   6.250   0.8598   0.01225   0.00529  -0.0393   0.1277   0.6771
   6.500   0.8833   0.01284   0.00583  -0.0389   0.0937   0.7078
   6.750   0.9046   0.01312   0.00638  -0.0378   0.0674   0.8118
   7.000   0.9267   0.01347   0.00689  -0.0368   0.0498   1.0000
   7.250   0.9509   0.01416   0.00754  -0.0364   0.0368   1.0000
   7.500   0.9742   0.01496   0.00833  -0.0358   0.0268   1.0000
   7.750   0.9977   0.01569   0.00907  -0.0353   0.0218   1.0000
   8.000   1.0201   0.01655   0.01001  -0.0346   0.0190   1.0000
   8.250   1.0436   0.01718   0.01070  -0.0341   0.0170   1.0000
   8.500   1.0639   0.01822   0.01179  -0.0332   0.0153   1.0000
   8.750   1.0809   0.01964   0.01334  -0.0318   0.0143   1.0000
   9.000   1.1014   0.02055   0.01436  -0.0309   0.0136   1.0000
   9.250   1.1203   0.02162   0.01553  -0.0298   0.0129   1.0000
   9.500   1.1385   0.02272   0.01672  -0.0287   0.0123   1.0000
   9.750   1.1565   0.02375   0.01783  -0.0276   0.0116   1.0000
  10.000   1.1714   0.02510   0.01924  -0.0263   0.0109   1.0000
  10.250   1.1753   0.02811   0.02247  -0.0237   0.0103   1.0000
  10.500   1.1893   0.02949   0.02401  -0.0222   0.0100   1.0000
  10.750   1.2013   0.03099   0.02568  -0.0206   0.0098   1.0000
  11.000   1.2087   0.03266   0.02752  -0.0184   0.0096   1.0000
  11.250   1.2127   0.03456   0.02961  -0.0160   0.0094   1.0000
  11.500   1.2142   0.03672   0.03196  -0.0139   0.0092   1.0000
  11.750   1.2133   0.03917   0.03461  -0.0120   0.0091   1.0000
  12.000   1.2100   0.04195   0.03760  -0.0106   0.0090   1.0000
  12.250   1.2045   0.04512   0.04098  -0.0098   0.0088   1.0000
  12.500   1.1959   0.04890   0.04497  -0.0097   0.0088   1.0000
  12.750   1.1851   0.05322   0.04951  -0.0104   0.0087   1.0000
  13.000   1.1717   0.05826   0.05477  -0.0120   0.0087   1.0000
  13.250   1.1560   0.06402   0.06075  -0.0145   0.0087   1.0000
  13.500   1.1381   0.07051   0.06744  -0.0179   0.0088   1.0000
  13.750   1.1176   0.07789   0.07502  -0.0220   0.0088   1.0000
  14.000   1.0957   0.08596   0.08327  -0.0268   0.0089   1.0000
  14.250   1.0723   0.09485   0.09233  -0.0322   0.0090   1.0000
  14.500   1.0479   0.10451   0.10214  -0.0381   0.0091   1.0000
  14.750   1.0221   0.11533   0.11311  -0.0447   0.0093   1.0000
  15.000   0.9935   0.12761   0.12551  -0.0519   0.0095   1.0000
  15.250   0.9572   0.14282   0.14083  -0.0604   0.0098   1.0000
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