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GOE 375 AIRFOIL (goe375-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 375 AIRFOIL (goe375-il)
Reynolds number: 200,000
Max Cl/Cd: 62.91 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe375-il-200000.txt
Download as CSV file: xf-goe375-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 375 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3494   0.09222   0.08883  -0.0115   1.0000   0.0203
  -7.500  -0.3468   0.08967   0.08632  -0.0122   1.0000   0.0205
  -7.250  -0.3456   0.08719   0.08391  -0.0126   1.0000   0.0207
  -7.000  -0.3412   0.08435   0.08110  -0.0143   1.0000   0.0212
  -6.750  -0.3340   0.08155   0.07835  -0.0166   1.0000   0.0216
  -6.500  -0.3249   0.07875   0.07557  -0.0191   1.0000   0.0218
  -6.250  -0.3104   0.07612   0.07293  -0.0237   1.0000   0.0221
  -6.000  -0.2928   0.07345   0.07020  -0.0284   1.0000   0.0222
  -5.750  -0.2763   0.07072   0.06740  -0.0311   1.0000   0.0223
  -5.250  -0.2616   0.06343   0.06015  -0.0301   1.0000   0.0226
  -5.000  -0.2630   0.06031   0.05713  -0.0273   1.0000   0.0230
  -4.750  -0.2609   0.05799   0.05482  -0.0255   1.0000   0.0234
  -4.500  -0.2571   0.05581   0.05263  -0.0242   1.0000   0.0240
  -4.250  -0.2248   0.05211   0.04882  -0.0287   0.9963   0.0251
  -4.000  -0.1813   0.04815   0.04468  -0.0346   0.9907   0.0265
  -3.750  -0.1218   0.04593   0.04198  -0.0409   0.9848   0.0279
  -3.500  -0.0827   0.04207   0.03784  -0.0446   0.9779   0.0283
  -3.250  -0.0528   0.03726   0.03310  -0.0483   0.9722   0.0292
  -3.000  -0.0171   0.03420   0.02991  -0.0513   0.9647   0.0306
  -2.750   0.0394   0.03415   0.02911  -0.0542   0.9575   0.0352
  -2.500   0.0716   0.02868   0.02376  -0.0575   0.9477   0.0366
  -2.250   0.1096   0.02613   0.02104  -0.0600   0.9368   0.0397
  -2.000   0.1511   0.02480   0.01919  -0.0612   0.9263   0.0450
  -1.750   0.1814   0.02221   0.01660  -0.0625   0.9127   0.0493
  -1.500   0.2133   0.02063   0.01477  -0.0630   0.8976   0.0594
  -1.250   0.2416   0.01926   0.01317  -0.0629   0.8794   0.0731
  -1.000   0.2677   0.01810   0.01181  -0.0626   0.8599   0.0999
  -0.750  -0.0860   0.01702   0.01387  -0.0395   1.0000   0.0349
  -0.500   0.3152   0.01581   0.00933  -0.0614   0.8186   0.1724
  -0.250   0.3390   0.01481   0.00828  -0.0604   0.7957   0.2070
   0.000   0.3669   0.01433   0.00750  -0.0589   0.7702   0.1965
   0.250   0.2227   0.02956   0.02636  -0.0648   0.8178   0.1708
   0.500   0.4246   0.01342   0.00597  -0.0556   0.7109   0.1195
   0.750   0.4504   0.01311   0.00541  -0.0541   0.6721   0.1050
   1.000   0.4753   0.01294   0.00495  -0.0526   0.6298   0.0915
   1.250   0.5001   0.01315   0.00482  -0.0512   0.5893   0.0821
   1.500   0.5234   0.01276   0.00431  -0.0499   0.5549   0.0778
   1.750   0.5471   0.01269   0.00407  -0.0488   0.5238   0.0742
   2.000   0.5708   0.01268   0.00392  -0.0478   0.4948   0.0746
   2.250   0.5948   0.01275   0.00382  -0.0469   0.4677   0.0749
   2.500   0.6191   0.01288   0.00376  -0.0461   0.4415   0.0735
   2.750   0.6438   0.01303   0.00376  -0.0453   0.4165   0.0728
   3.000   0.6684   0.01324   0.00380  -0.0446   0.3940   0.0731
   3.250   0.6933   0.01344   0.00387  -0.0439   0.3725   0.0749
   3.500   0.7181   0.01368   0.00398  -0.0432   0.3542   0.0791
   3.750   0.7634   0.01230   0.00430  -0.0474   0.3339   1.0000
   4.000   0.7879   0.01264   0.00453  -0.0467   0.3199   1.0000
   4.250   0.8122   0.01301   0.00475  -0.0460   0.3072   1.0000
   4.500   0.8367   0.01336   0.00499  -0.0454   0.2951   1.0000
   4.750   0.8613   0.01369   0.00527  -0.0448   0.2837   1.0000
   5.000   0.8856   0.01409   0.00562  -0.0441   0.2735   1.0000
   5.250   0.9096   0.01456   0.00595  -0.0435   0.2645   1.0000
   5.500   0.9342   0.01490   0.00632  -0.0429   0.2550   1.0000
   5.750   0.9583   0.01539   0.00675  -0.0423   0.2467   1.0000
   6.000   0.9825   0.01582   0.00719  -0.0417   0.2385   1.0000
   6.250   1.0067   0.01634   0.00771  -0.0411   0.2307   1.0000
   6.500   1.0308   0.01683   0.00818  -0.0406   0.2236   1.0000
   6.750   1.0548   0.01737   0.00876  -0.0400   0.2165   1.0000
   7.000   1.0787   0.01785   0.00928  -0.0394   0.2101   1.0000
   7.250   1.1028   0.01853   0.00999  -0.0389   0.2047   1.0000
   7.500   1.1266   0.01902   0.01059  -0.0382   0.1991   1.0000
   7.750   1.1502   0.01961   0.01111  -0.0377   0.1932   1.0000
   8.000   1.1728   0.01989   0.01160  -0.0369   0.1863   1.0000
   8.250   1.1952   0.02024   0.01192  -0.0363   0.1792   1.0000
   8.500   1.2172   0.02044   0.01234  -0.0354   0.1719   1.0000
   8.750   1.2391   0.02077   0.01267  -0.0347   0.1655   1.0000
   9.000   1.2609   0.02096   0.01307  -0.0338   0.1580   1.0000
   9.250   1.2818   0.02127   0.01342  -0.0330   0.1508   1.0000
   9.500   1.3035   0.02125   0.01362  -0.0322   0.1401   1.0000
   9.750   1.3243   0.02140   0.01384  -0.0313   0.1243   1.0000
  10.000   1.3458   0.02181   0.01428  -0.0305   0.0925   1.0000
  10.500   1.3585   0.02603   0.01807  -0.0258   0.0289   1.0000
  10.750   1.3664   0.02771   0.01993  -0.0234   0.0259   1.0000
  11.000   1.3741   0.02918   0.02162  -0.0212   0.0242   1.0000
  11.250   1.3760   0.03078   0.02341  -0.0183   0.0229   1.0000
  11.500   1.3732   0.03255   0.02536  -0.0151   0.0222   1.0000
  11.750   1.3674   0.03466   0.02764  -0.0123   0.0216   1.0000
  12.000   1.3602   0.03713   0.03027  -0.0104   0.0213   1.0000
  12.250   1.3497   0.04029   0.03357  -0.0093   0.0209   1.0000
  12.500   1.3397   0.04383   0.03725  -0.0091   0.0206   1.0000
  12.750   1.3296   0.04779   0.04138  -0.0096   0.0205   1.0000
  13.000   1.3201   0.05208   0.04579  -0.0107   0.0203   1.0000
  13.250   1.3095   0.05674   0.05057  -0.0121   0.0201   1.0000
  13.500   1.3022   0.06108   0.05502  -0.0133   0.0200   1.0000
  13.750   1.2946   0.06538   0.05942  -0.0141   0.0198   1.0000
  14.000   1.2896   0.06923   0.06335  -0.0142   0.0195   1.0000
  14.250   1.2862   0.07319   0.06742  -0.0151   0.0194   1.0000
  14.500   1.2815   0.07754   0.07192  -0.0167   0.0192   1.0000
  14.750   1.2761   0.08205   0.07658  -0.0183   0.0191   1.0000
  15.000   1.2687   0.08710   0.08179  -0.0206   0.0188   1.0000
  15.250   1.2605   0.09246   0.08731  -0.0232   0.0186   1.0000
  15.500   1.2537   0.09757   0.09258  -0.0253   0.0185   1.0000
  15.750   1.2442   0.10344   0.09861  -0.0283   0.0183   1.0000
  16.000   1.2357   0.10920   0.10452  -0.0311   0.0184   1.0000
  16.250   1.2254   0.11552   0.11100  -0.0345   0.0184   1.0000
  16.500   1.2139   0.12232   0.11796  -0.0383   0.0184   1.0000
  16.750   1.2023   0.12935   0.12514  -0.0423   0.0185   1.0000
  17.000   1.1893   0.13694   0.13288  -0.0468   0.0186   1.0000
  17.250   1.1757   0.14489   0.14098  -0.0517   0.0188   1.0000
  17.500   1.1617   0.15323   0.14945  -0.0569   0.0189   1.0000
  17.750   1.1463   0.16226   0.15860  -0.0625   0.0191   1.0000
  18.000   1.1300   0.17187   0.16832  -0.0684   0.0194   1.0000
  18.250   1.1197   0.18038   0.17694  -0.0738   0.0197   1.0000
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