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GOE 366 AIRFOIL (goe366-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 366 AIRFOIL (goe366-il)
Reynolds number: 200,000
Max Cl/Cd: 82.6 at α=-0.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe366-il-200000.txt
Download as CSV file: xf-goe366-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 366 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500   0.1181   0.08855   0.08500  -0.1060   0.9337   0.0337
  -9.250   0.1317   0.08509   0.08152  -0.1081   0.9302   0.0343
  -9.000   0.0386   0.09762   0.09392  -0.1026   0.9475   0.0331
  -8.750   0.0607   0.09371   0.09000  -0.1052   0.9448   0.0335
  -8.500   0.0719   0.09107   0.08736  -0.1063   0.9356   0.0340
  -8.250   0.0889   0.08794   0.08421  -0.1092   0.9306   0.0348
  -8.000   0.0975   0.08555   0.08181  -0.1103   0.9206   0.0354
  -7.750   0.1103   0.08274   0.07898  -0.1126   0.9140   0.0361
  -7.500   0.1155   0.08069   0.07693  -0.1137   0.9034   0.0366
  -7.250   0.1212   0.07862   0.07482  -0.1177   0.8954   0.0371
  -7.000   0.1294   0.07640   0.07256  -0.1259   0.8836   0.0373
  -6.750   0.1424   0.07321   0.06938  -0.1229   0.8797   0.0376
  -6.500   0.1523   0.07086   0.06704  -0.1220   0.8725   0.0379
  -6.250   0.1652   0.06842   0.06458  -0.1230   0.8658   0.0385
  -6.000   0.1828   0.06572   0.06182  -0.1257   0.8610   0.0392
  -5.750   0.1951   0.06350   0.05960  -0.1276   0.8522   0.0401
  -5.500   0.2160   0.06066   0.05668  -0.1317   0.8463   0.0413
  -5.250   0.2467   0.05730   0.05313  -0.1408   0.8392   0.0426
  -5.000   0.2577   0.05497   0.05084  -0.1391   0.8327   0.0431
  -4.750   0.2778   0.05256   0.04837  -0.1400   0.8278   0.0441
  -4.500   0.2971   0.05041   0.04617  -0.1414   0.8204   0.0455
  -4.250   0.3406   0.04772   0.04303  -0.1490   0.8138   0.0484
  -4.000   0.3582   0.04473   0.04009  -0.1489   0.8092   0.0489
  -3.750   0.3734   0.04290   0.03829  -0.1482   0.8007   0.0498
  -3.500   0.3996   0.04078   0.03605  -0.1496   0.7949   0.0517
  -3.250   0.4352   0.03875   0.03361  -0.1524   0.7877   0.0556
  -3.000   0.4547   0.03651   0.03142  -0.1524   0.7803   0.0566
  -2.750   0.4805   0.03477   0.02957  -0.1531   0.7738   0.0591
  -2.500   0.5113   0.03315   0.02761  -0.1541   0.7651   0.0642
  -2.000   0.5655   0.03035   0.02441  -0.1548   0.7487   0.0738
  -1.750   0.5911   0.02841   0.02248  -0.1555   0.7415   0.0769
  -1.500   0.6173   0.02748   0.02129  -0.1552   0.7307   0.0858
  -1.250   0.6434   0.02605   0.01981  -0.1556   0.7221   0.0904
  -1.000   0.6404   0.01048   0.00437  -0.1462   0.6916   0.1019
  -0.750   0.6651   0.00986   0.00357  -0.1460   0.6803   0.1149
  -0.500   0.6918   0.00915   0.00268  -0.1463   0.6704   0.1311
  -0.250   0.7137   0.00864   0.00214  -0.1458   0.6575   0.1496
   0.000   0.7693   0.02137   0.01452  -0.1545   0.6650   0.1716
   0.250   0.7938   0.02049   0.01352  -0.1545   0.6535   0.2173
   0.500   0.8156   0.01947   0.01254  -0.1538   0.6396   0.2555
   0.750   0.8398   0.01860   0.01161  -0.1532   0.6261   0.2896
   1.000   0.8671   0.01806   0.01090  -0.1526   0.6131   0.2991
   1.500   0.9363   0.01749   0.00897  -0.1493   0.5896   0.0819
   1.750   0.9622   0.01741   0.00864  -0.1483   0.5779   0.0729
   2.000   0.9876   0.01685   0.00802  -0.1477   0.5676   0.0699
   2.250   1.0127   0.01666   0.00773  -0.1470   0.5569   0.0674
   2.500   1.0376   0.01658   0.00758  -0.1464   0.5470   0.0661
   2.750   1.0637   0.01657   0.00748  -0.1461   0.5381   0.0667
   3.000   1.0883   0.01663   0.00755  -0.1456   0.5293   0.0698
   3.250   1.1148   0.01675   0.00756  -0.1454   0.5215   0.0712
   3.500   1.1396   0.01692   0.00768  -0.1449   0.5135   0.0728
   3.750   1.1652   0.01709   0.00777  -0.1445   0.5059   0.0772
   4.000   1.1911   0.01734   0.00796  -0.1443   0.4989   0.0882
   4.250   1.2104   0.01613   0.00833  -0.1427   0.4923   1.0000
   4.500   1.2375   0.01653   0.00852  -0.1426   0.4862   1.0000
   4.750   1.2613   0.01689   0.00884  -0.1420   0.4800   1.0000
   5.000   1.2852   0.01722   0.00911  -0.1415   0.4736   1.0000
   5.250   1.3127   0.01765   0.00937  -0.1416   0.4681   1.0000
   5.500   1.3345   0.01800   0.00976  -0.1408   0.4622   1.0000
   5.750   1.3582   0.01835   0.01009  -0.1402   0.4566   1.0000
   6.000   1.3848   0.01876   0.01040  -0.1403   0.4518   1.0000
   6.250   1.4084   0.01919   0.01084  -0.1398   0.4468   1.0000
   6.500   1.4302   0.01956   0.01125  -0.1390   0.4415   1.0000
   6.750   1.4547   0.01993   0.01159  -0.1386   0.4367   1.0000
   7.000   1.4821   0.02041   0.01199  -0.1389   0.4322   1.0000
   7.250   1.5004   0.02080   0.01249  -0.1375   0.4271   1.0000
   7.500   1.5222   0.02118   0.01288  -0.1367   0.4221   1.0000
   7.750   1.5477   0.02157   0.01321  -0.1366   0.4175   1.0000
   8.000   1.5678   0.02204   0.01374  -0.1356   0.4126   1.0000
   8.250   1.5860   0.02244   0.01422  -0.1342   0.4075   1.0000
   8.500   1.6083   0.02282   0.01462  -0.1335   0.4031   1.0000
   8.750   1.6375   0.02332   0.01502  -0.1342   0.3990   1.0000
   9.000   1.6500   0.02380   0.01567  -0.1319   0.3946   1.0000
   9.250   1.6665   0.02423   0.01618  -0.1303   0.3898   1.0000
   9.500   1.6878   0.02460   0.01656  -0.1295   0.3854   1.0000
   9.750   1.7129   0.02513   0.01706  -0.1295   0.3813   1.0000
  10.000   1.7215   0.02566   0.01777  -0.1266   0.3772   1.0000
  10.250   1.7349   0.02614   0.01833  -0.1245   0.3728   1.0000
  10.500   1.7544   0.02653   0.01873  -0.1235   0.3685   1.0000
  10.750   1.7724   0.02708   0.01930  -0.1223   0.3640   1.0000
  11.000   1.7755   0.02773   0.02012  -0.1187   0.3592   1.0000
  11.250   1.7867   0.02823   0.02067  -0.1164   0.3542   1.0000
  11.500   1.8086   0.02862   0.02100  -0.1159   0.3490   1.0000
  11.750   1.8057   0.02955   0.02215  -0.1118   0.3443   1.0000
  12.000   1.8118   0.03028   0.02297  -0.1091   0.3389   1.0000
  12.250   1.8302   0.03070   0.02331  -0.1082   0.3334   1.0000
  12.500   1.8258   0.03194   0.02479  -0.1044   0.3283   1.0000
  12.750   1.8289   0.03295   0.02590  -0.1018   0.3226   1.0000
  13.000   1.8429   0.03358   0.02647  -0.1005   0.3170   1.0000
  13.250   1.8371   0.03522   0.02835  -0.0972   0.3114   1.0000
  13.500   1.8392   0.03651   0.02974  -0.0949   0.3055   1.0000
  13.750   1.8445   0.03773   0.03099  -0.0930   0.2996   1.0000
  14.000   1.8395   0.03969   0.03313  -0.0905   0.2929   1.0000
  14.250   1.8439   0.04102   0.03444  -0.0888   0.2863   1.0000
  14.500   1.8367   0.04348   0.03712  -0.0866   0.2792   1.0000
  14.750   1.8363   0.04544   0.03911  -0.0850   0.2720   1.0000
  15.000   1.8310   0.04807   0.04192  -0.0834   0.2642   1.0000
  15.250   1.8280   0.05051   0.04437  -0.0820   0.2564   1.0000
  15.500   1.8203   0.05370   0.04774  -0.0808   0.2472   1.0000
  15.750   1.8131   0.05689   0.05099  -0.0797   0.2383   1.0000
  16.000   1.8027   0.06059   0.05475  -0.0787   0.2283   1.0000
  16.250   1.7907   0.06465   0.05891  -0.0780   0.2176   1.0000
  16.500   1.7767   0.06907   0.06338  -0.0774   0.2069   1.0000
  16.750   1.7603   0.07394   0.06827  -0.0771   0.1963   1.0000
  17.000   1.7427   0.07910   0.07344  -0.0770   0.1861   1.0000
  17.250   1.7270   0.08415   0.07855  -0.0771   0.1767   1.0000
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