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GOE 802 AIRFOIL (goe802-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 802 AIRFOIL (goe802-il)
Reynolds number: 200,000
Max Cl/Cd: 79.55 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe802-il-200000-n5.txt
Download as CSV file: xf-goe802-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 802 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.1489   0.09242   0.08884  -0.0591   0.9596   0.0299
  -8.000  -0.1369   0.08945   0.08586  -0.0616   0.9493   0.0310
  -7.750  -0.1259   0.08643   0.08283  -0.0644   0.9396   0.0320
  -7.500  -0.1184   0.08354   0.07993  -0.0688   0.9284   0.0328
  -7.250  -0.1068   0.08017   0.07653  -0.0763   0.9162   0.0331
  -7.000  -0.0891   0.07629   0.07259  -0.0834   0.9072   0.0332
  -6.750  -0.0801   0.07335   0.06967  -0.0810   0.9004   0.0335
  -6.500  -0.0676   0.07085   0.06715  -0.0801   0.8943   0.0341
  -6.250  -0.0530   0.06835   0.06464  -0.0814   0.8858   0.0349
  -6.000  -0.0352   0.06550   0.06173  -0.0843   0.8791   0.0362
  -5.750  -0.0143   0.06230   0.05848  -0.0888   0.8703   0.0376
  -5.500   0.0294   0.05694   0.05282  -0.1028   0.8629   0.0393
  -5.250   0.0470   0.05353   0.04939  -0.1042   0.8549   0.0396
  -5.000   0.0630   0.05117   0.04702  -0.1039   0.8483   0.0401
  -4.750   0.0830   0.04893   0.04473  -0.1048   0.8406   0.0409
  -4.500   0.1066   0.04662   0.04234  -0.1066   0.8332   0.0426
  -4.250   0.1530   0.04194   0.03717  -0.1147   0.8259   0.0468
  -4.000   0.1717   0.03958   0.03483  -0.1148   0.8179   0.0474
  -3.750   0.1942   0.03768   0.03287  -0.1153   0.8100   0.0483
  -3.500   0.2199   0.03572   0.03081  -0.1163   0.8012   0.0498
  -3.250   0.2590   0.03277   0.02725  -0.1195   0.7926   0.0555
  -3.000   0.2817   0.03059   0.02508  -0.1198   0.7828   0.0565
  -2.750   0.3064   0.02914   0.02357  -0.1201   0.7713   0.0581
  -2.500   0.3379   0.02751   0.02151  -0.1211   0.7607   0.0664
  -2.250   0.3730   0.02273   0.01597  -0.1214   0.7512   0.0390
  -2.000   0.4002   0.02128   0.01438  -0.1216   0.7400   0.0382
  -1.750   0.4284   0.01996   0.01280  -0.1217   0.7291   0.0375
  -1.500   0.4569   0.01881   0.01135  -0.1216   0.7176   0.0370
  -1.250   0.4852   0.01784   0.01012  -0.1215   0.7051   0.0368
  -1.000   0.5134   0.01715   0.00918  -0.1213   0.6926   0.0377
  -0.750   0.5414   0.01657   0.00835  -0.1211   0.6800   0.0383
  -0.500   0.5691   0.01598   0.00756  -0.1209   0.6670   0.0382
  -0.250   0.5965   0.01548   0.00690  -0.1206   0.6533   0.0381
   0.000   0.6239   0.01506   0.00635  -0.1203   0.6396   0.0382
   0.250   0.6512   0.01472   0.00590  -0.1200   0.6266   0.0384
   0.500   0.6782   0.01445   0.00552  -0.1197   0.6138   0.0386
   0.750   0.7051   0.01424   0.00523  -0.1193   0.6010   0.0390
   1.000   0.7318   0.01405   0.00498  -0.1190   0.5882   0.0396
   1.250   0.7584   0.01385   0.00479  -0.1188   0.5757   0.0414
   1.500   0.7852   0.01378   0.00469  -0.1186   0.5643   0.0431
   1.750   0.8119   0.01375   0.00460  -0.1183   0.5535   0.0441
   2.000   0.8387   0.01376   0.00456  -0.1181   0.5422   0.0451
   2.250   0.8653   0.01381   0.00454  -0.1178   0.5311   0.0463
   2.500   0.8917   0.01388   0.00454  -0.1175   0.5206   0.0484
   2.750   0.9182   0.01396   0.00459  -0.1172   0.5102   0.0524
   3.250   0.9669   0.01253   0.00494  -0.1160   0.4915   1.0000
   3.500   0.9930   0.01275   0.00507  -0.1157   0.4817   1.0000
   3.750   1.0185   0.01301   0.00521  -0.1152   0.4716   1.0000
   4.000   1.0439   0.01326   0.00537  -0.1148   0.4598   1.0000
   4.250   1.0691   0.01352   0.00556  -0.1143   0.4478   1.0000
   4.500   1.0938   0.01380   0.00576  -0.1138   0.4357   1.0000
   4.750   1.1182   0.01410   0.00597  -0.1132   0.4238   1.0000
   5.000   1.1426   0.01438   0.00621  -0.1127   0.4116   1.0000
   5.250   1.1670   0.01467   0.00646  -0.1122   0.4006   1.0000
   5.500   1.1909   0.01499   0.00672  -0.1116   0.3910   1.0000
   5.750   1.2153   0.01529   0.00702  -0.1111   0.3823   1.0000
   6.000   1.2391   0.01562   0.00732  -0.1105   0.3747   1.0000
   6.250   1.2628   0.01594   0.00764  -0.1099   0.3657   1.0000
   6.500   1.2857   0.01630   0.00799  -0.1091   0.3561   1.0000
   6.750   1.3077   0.01669   0.00835  -0.1083   0.3456   1.0000
   7.000   1.3301   0.01705   0.00872  -0.1075   0.3349   1.0000
   7.250   1.3517   0.01746   0.00911  -0.1066   0.3255   1.0000
   7.500   1.3731   0.01786   0.00954  -0.1057   0.3159   1.0000
   7.750   1.3943   0.01827   0.00997  -0.1047   0.3065   1.0000
   8.000   1.4137   0.01875   0.01044  -0.1035   0.2965   1.0000
   8.250   1.4334   0.01919   0.01093  -0.1024   0.2844   1.0000
   8.500   1.4518   0.01969   0.01143  -0.1010   0.2715   1.0000
   8.750   1.4691   0.02023   0.01198  -0.0995   0.2588   1.0000
   9.000   1.4837   0.02081   0.01257  -0.0976   0.2446   1.0000
   9.250   1.4952   0.02154   0.01326  -0.0953   0.2261   1.0000
   9.500   1.5042   0.02247   0.01409  -0.0928   0.2063   1.0000
   9.750   1.5128   0.02350   0.01504  -0.0903   0.1885   1.0000
  10.000   1.5211   0.02460   0.01609  -0.0880   0.1747   1.0000
  10.500   1.5396   0.02683   0.01834  -0.0840   0.1552   1.0000
  10.750   1.5479   0.02806   0.01959  -0.0821   0.1475   1.0000
  11.000   1.5571   0.02927   0.02085  -0.0803   0.1393   1.0000
  11.250   1.5647   0.03064   0.02224  -0.0786   0.1313   1.0000
  11.500   1.5715   0.03212   0.02376  -0.0769   0.1229   1.0000
  11.750   1.5792   0.03356   0.02526  -0.0754   0.1159   1.0000
  12.000   1.5846   0.03524   0.02698  -0.0738   0.1086   1.0000
  12.250   1.5908   0.03690   0.02870  -0.0725   0.1010   1.0000
  12.500   1.5943   0.03886   0.03069  -0.0711   0.0934   1.0000
  12.750   1.5974   0.04092   0.03279  -0.0698   0.0849   1.0000
  13.000   1.5990   0.04318   0.03509  -0.0686   0.0774   1.0000
  13.250   1.5991   0.04567   0.03762  -0.0675   0.0715   1.0000
  13.500   1.5975   0.04841   0.04039  -0.0666   0.0655   1.0000
  13.750   1.5948   0.05136   0.04340  -0.0658   0.0604   1.0000
  14.000   1.5925   0.05440   0.04651  -0.0652   0.0557   1.0000
  14.250   1.5890   0.05768   0.04986  -0.0647   0.0514   1.0000
  14.500   1.5866   0.06094   0.05322  -0.0645   0.0456   1.0000
  14.750   1.5825   0.06451   0.05687  -0.0644   0.0368   1.0000
  15.000   1.5639   0.07008   0.06236  -0.0647   0.0224   1.0000
  15.250   1.5512   0.07506   0.06739  -0.0652   0.0206   1.0000
  15.500   1.5404   0.07993   0.07237  -0.0658   0.0192   1.0000
  15.750   1.5318   0.08458   0.07716  -0.0666   0.0185   1.0000
  16.000   1.5230   0.08933   0.08205  -0.0675   0.0179   1.0000
  16.250   1.5137   0.09426   0.08712  -0.0685   0.0174   1.0000
  16.500   1.5038   0.09936   0.09237  -0.0698   0.0170   1.0000
  16.750   1.4933   0.10466   0.09783  -0.0712   0.0167   1.0000
  17.000   1.4821   0.11015   0.10347  -0.0729   0.0163   1.0000
  17.250   1.4705   0.11581   0.10928  -0.0748   0.0161   1.0000
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