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GOE 408 AIRFOIL (goe408-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 408 AIRFOIL (goe408-il)
Reynolds number: 100,000
Max Cl/Cd: 59.16 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe408-il-100000-n5.txt
Download as CSV file: xf-goe408-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 408 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3857   0.10426   0.09943  -0.0259   1.0000   0.0382
  -8.000  -0.3908   0.10177   0.09700  -0.0260   1.0000   0.0382
  -7.750  -0.3943   0.09909   0.09439  -0.0263   1.0000   0.0383
  -7.500  -0.3939   0.09578   0.09113  -0.0273   1.0000   0.0383
  -7.250  -0.3829   0.09151   0.08689  -0.0218   1.0000   0.0402
  -7.000  -0.3836   0.08857   0.08400  -0.0218   1.0000   0.0405
  -6.750  -0.3834   0.08555   0.08104  -0.0221   1.0000   0.0406
  -6.500  -0.3830   0.08229   0.07783  -0.0230   1.0000   0.0402
  -6.000  -0.3790   0.07549   0.07106  -0.0233   1.0000   0.0354
  -5.750  -0.3763   0.07207   0.06764  -0.0236   1.0000   0.0340
  -5.500  -0.3727   0.06791   0.06344  -0.0246   1.0000   0.0322
  -5.250  -0.3560   0.06491   0.06040  -0.0265   0.9975   0.0344
  -5.000  -0.3207   0.05948   0.05473  -0.0336   0.9904   0.0369
  -4.750  -0.2901   0.05449   0.04952  -0.0382   0.9831   0.0368
  -4.500  -0.2572   0.04868   0.04327  -0.0424   0.9745   0.0380
  -4.250  -0.2317   0.04706   0.04166  -0.0441   0.9673   0.0426
  -4.000  -0.2030   0.04303   0.03729  -0.0460   0.9577   0.0445
  -3.750  -0.1758   0.03854   0.03217  -0.0464   0.9465   0.0482
  -3.500  -0.1528   0.03727   0.03098  -0.0470   0.9358   0.0525
  -3.250  -0.1260   0.03428   0.02759  -0.0471   0.9255   0.0544
  -3.000  -0.0937   0.03135   0.02389  -0.0474   0.9176   0.0600
  -2.750  -0.0684   0.02924   0.02162  -0.0473   0.9067   0.0615
  -2.500  -0.0391   0.02739   0.01949  -0.0475   0.8975   0.0629
  -2.250  -0.0066   0.02602   0.01786  -0.0483   0.8893   0.0674
  -2.000   0.0231   0.02442   0.01588  -0.0482   0.8788   0.0679
  -1.750   0.0588   0.02288   0.01397  -0.0493   0.8714   0.0681
  -1.500   0.0915   0.02166   0.01245  -0.0498   0.8607   0.0687
  -1.250   0.1265   0.02058   0.01108  -0.0509   0.8506   0.0698
  -1.000   0.1675   0.01965   0.00987  -0.0532   0.8423   0.0733
  -0.750   0.2037   0.01878   0.00891  -0.0548   0.8303   0.0746
  -0.500   0.2432   0.01801   0.00803  -0.0570   0.8186   0.0755
  -0.250   0.2851   0.01734   0.00728  -0.0598   0.8068   0.0768
   0.000   0.3269   0.01676   0.00664  -0.0626   0.7945   0.0788
   0.250   0.3670   0.01629   0.00612  -0.0650   0.7814   0.0812
   0.500   0.4041   0.01600   0.00573  -0.0668   0.7675   0.0850
   0.750   0.4415   0.01575   0.00547  -0.0688   0.7531   0.0914
   1.000   0.4799   0.01561   0.00522  -0.0709   0.7387   0.0969
   1.250   0.5168   0.01548   0.00504  -0.0728   0.7244   0.1041
   1.500   0.5521   0.01540   0.00492  -0.0743   0.7099   0.1188
   2.000   0.7293   0.01394   0.00517  -0.1019   0.6750   1.0000
   2.250   0.7547   0.01414   0.00529  -0.1013   0.6599   1.0000
   2.500   0.7792   0.01435   0.00542  -0.1004   0.6448   1.0000
   2.750   0.8032   0.01456   0.00557  -0.0995   0.6296   1.0000
   3.000   0.8264   0.01477   0.00576  -0.0984   0.6136   1.0000
   3.250   0.8481   0.01499   0.00592  -0.0969   0.5947   1.0000
   3.500   0.8691   0.01521   0.00606  -0.0953   0.5734   1.0000
   3.750   0.8892   0.01544   0.00622  -0.0935   0.5508   1.0000
   4.000   0.9099   0.01569   0.00642  -0.0919   0.5302   1.0000
   4.250   0.9315   0.01596   0.00666  -0.0905   0.5136   1.0000
   4.500   0.9531   0.01624   0.00693  -0.0891   0.4976   1.0000
   4.750   0.9745   0.01654   0.00722  -0.0877   0.4821   1.0000
   5.000   0.9956   0.01685   0.00757  -0.0863   0.4667   1.0000
   5.250   1.0163   0.01718   0.00791  -0.0848   0.4507   1.0000
   5.500   1.0367   0.01753   0.00829  -0.0832   0.4345   1.0000
   5.750   1.0566   0.01790   0.00870  -0.0816   0.4177   1.0000
   6.000   1.0756   0.01829   0.00915  -0.0798   0.3987   1.0000
   6.250   1.0937   0.01870   0.00958  -0.0778   0.3784   1.0000
   6.500   1.1108   0.01914   0.01004  -0.0757   0.3552   1.0000
   6.750   1.1273   0.01962   0.01052  -0.0735   0.3320   1.0000
   7.000   1.1441   0.02012   0.01109  -0.0714   0.3087   1.0000
   7.250   1.1599   0.02068   0.01166  -0.0692   0.2876   1.0000
   7.500   1.1758   0.02127   0.01229  -0.0670   0.2664   1.0000
   7.750   1.1889   0.02198   0.01296  -0.0644   0.2427   1.0000
   8.000   1.2017   0.02275   0.01369  -0.0618   0.2180   1.0000
   8.250   1.2126   0.02362   0.01450  -0.0589   0.1923   1.0000
   8.500   1.2214   0.02462   0.01539  -0.0559   0.1638   1.0000
   8.750   1.2298   0.02567   0.01640  -0.0528   0.1356   1.0000
   9.000   1.2367   0.02674   0.01740  -0.0495   0.1052   1.0000
   9.250   1.2378   0.02815   0.01856  -0.0454   0.0690   1.0000
   9.500   1.2344   0.02991   0.02014  -0.0408   0.0537   1.0000
   9.750   1.2340   0.03152   0.02185  -0.0366   0.0452   1.0000
  10.000   1.2315   0.03333   0.02374  -0.0326   0.0394   1.0000
  10.250   1.2318   0.03500   0.02557  -0.0290   0.0352   1.0000
  10.500   1.2320   0.03674   0.02742  -0.0259   0.0314   1.0000
  10.750   1.2287   0.03880   0.02957  -0.0229   0.0296   1.0000
  11.000   1.2293   0.04072   0.03170  -0.0204   0.0274   1.0000
  11.250   1.2284   0.04286   0.03400  -0.0182   0.0258   1.0000
  11.500   1.2266   0.04521   0.03650  -0.0163   0.0249   1.0000
  11.750   1.2237   0.04783   0.03928  -0.0148   0.0237   1.0000
  12.000   1.2197   0.05068   0.04224  -0.0136   0.0227   1.0000
  12.250   1.2150   0.05378   0.04539  -0.0124   0.0220   1.0000
  12.500   1.2153   0.05655   0.04839  -0.0114   0.0210   1.0000
  12.750   1.2149   0.05942   0.05148  -0.0108   0.0200   1.0000
  13.000   1.2133   0.06255   0.05479  -0.0103   0.0192   1.0000
  13.250   1.2119   0.06574   0.05817  -0.0098   0.0188   1.0000
  13.500   1.2097   0.06914   0.06174  -0.0095   0.0184   1.0000
  13.750   1.2054   0.07294   0.06574  -0.0094   0.0180   1.0000
  14.000   1.1987   0.07710   0.07010  -0.0098   0.0175   1.0000
  14.250   1.1918   0.08141   0.07461  -0.0104   0.0173   1.0000
  14.500   1.1829   0.08616   0.07957  -0.0115   0.0171   1.0000
  14.750   1.1722   0.09136   0.08498  -0.0130   0.0171   1.0000
  15.000   1.1598   0.09706   0.09089  -0.0151   0.0171   1.0000
  15.250   1.1454   0.10332   0.09734  -0.0178   0.0168   1.0000
  15.500   1.1308   0.10995   0.10418  -0.0209   0.0169   1.0000
  15.750   1.1129   0.11772   0.11216  -0.0248   0.0172   1.0000
  16.000   1.0941   0.12609   0.12072  -0.0295   0.0173   1.0000
  16.250   1.0711   0.13612   0.13091  -0.0353   0.0173   1.0000
  16.500   1.0459   0.14767   0.14263  -0.0420   0.0179   1.0000
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