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GOE 81 AIRFOIL (goe81-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 81 AIRFOIL (goe81-il)
Reynolds number: 100,000
Max Cl/Cd: 65.07 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe81-il-100000-n5.txt
Download as CSV file: xf-goe81-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 81 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2608   0.11274   0.10801  -0.0339   1.0000   0.0334
  -8.500  -0.2729   0.11238   0.10777  -0.0319   1.0000   0.0335
  -8.250  -0.2814   0.11172   0.10721  -0.0315   0.9972   0.0335
  -8.000  -0.2612   0.10459   0.10008  -0.0298   0.9974   0.0342
  -7.750  -0.2427   0.10034   0.09582  -0.0323   0.9920   0.0354
  -7.500  -0.2244   0.09681   0.09228  -0.0364   0.9838   0.0370
  -7.250  -0.2041   0.09326   0.08872  -0.0417   0.9745   0.0387
  -7.000  -0.1800   0.08994   0.08538  -0.0493   0.9639   0.0404
  -6.750  -0.1450   0.08737   0.08272  -0.0635   0.9517   0.0412
  -6.500  -0.1226   0.08297   0.07831  -0.0682   0.9436   0.0417
  -6.250  -0.1098   0.07839   0.07376  -0.0658   0.9388   0.0429
  -6.000  -0.0870   0.07493   0.07025  -0.0691   0.9316   0.0451
  -5.750  -0.0594   0.07154   0.06681  -0.0748   0.9233   0.0475
  -5.500  -0.0135   0.06886   0.06394  -0.0876   0.9132   0.0506
  -5.250   0.0228   0.06503   0.05997  -0.0952   0.9063   0.0513
  -5.000   0.0335   0.06129   0.05629  -0.0934   0.8985   0.0525
  -4.750   0.0569   0.05835   0.05330  -0.0953   0.8914   0.0554
  -4.500   0.1024   0.05635   0.05104  -0.1040   0.8817   0.0613
  -4.250   0.1337   0.03522   0.03019  -0.0995   0.8448   0.0635
  -4.000   0.1505   0.03261   0.02755  -0.0997   0.8346   0.0655
  -3.750   0.1759   0.03000   0.02482  -0.1019   0.8263   0.0689
  -3.500   0.2168   0.02802   0.02247  -0.1080   0.8160   0.0751
  -3.250   0.2309   0.02518   0.01969  -0.1072   0.8070   0.0776
  -3.000   0.2558   0.02309   0.01749  -0.1084   0.7985   0.0823
  -2.750   0.2928   0.02152   0.01555  -0.1121   0.7893   0.0894
  -2.500   0.3141   0.01919   0.01321  -0.1125   0.7828   0.0921
  -2.250   0.3446   0.01821   0.01199  -0.1140   0.7743   0.1016
  -2.000   0.3716   0.01615   0.00980  -0.1153   0.7677   0.1059
  -1.750   0.3970   0.01488   0.00844  -0.1159   0.7597   0.1124
  -1.500   0.4247   0.01361   0.00702  -0.1168   0.7525   0.1261
  -1.000   0.5233   0.02611   0.01797  -0.1269   0.7559   0.0626
  -0.750   0.5514   0.02466   0.01642  -0.1272   0.7483   0.0590
  -0.500   0.5807   0.02344   0.01498  -0.1273   0.7394   0.0561
  -0.250   0.6114   0.02229   0.01346  -0.1273   0.7316   0.0532
   0.000   0.6407   0.02147   0.01230  -0.1271   0.7227   0.0520
   0.250   0.6683   0.02077   0.01152  -0.1270   0.7140   0.0536
   0.500   0.6964   0.02016   0.01076  -0.1268   0.7053   0.0548
   0.750   0.7240   0.01959   0.01003  -0.1264   0.6956   0.0543
   1.000   0.7521   0.01906   0.00931  -0.1260   0.6871   0.0539
   1.250   0.7788   0.01866   0.00885  -0.1255   0.6766   0.0539
   1.500   0.8056   0.01831   0.00843  -0.1251   0.6666   0.0543
   1.750   0.8323   0.01800   0.00805  -0.1246   0.6568   0.0549
   2.000   0.8578   0.01780   0.00783  -0.1239   0.6452   0.0562
   2.250   0.8840   0.01769   0.00764  -0.1233   0.6333   0.0597
   2.500   0.9104   0.01760   0.00745  -0.1228   0.6211   0.0625
   2.750   0.9367   0.01754   0.00730  -0.1223   0.6081   0.0650
   3.000   0.9624   0.01756   0.00727  -0.1217   0.5935   0.0688
   3.500   1.0136   0.01764   0.00735  -0.1206   0.5635   0.1005
   3.750   1.0351   0.01642   0.00752  -0.1193   0.5492   1.0000
   4.000   1.0599   0.01665   0.00762  -0.1187   0.5341   1.0000
   4.250   1.0845   0.01690   0.00776  -0.1180   0.5189   1.0000
   4.500   1.1089   0.01717   0.00795  -0.1173   0.5038   1.0000
   4.750   1.1331   0.01747   0.00815  -0.1166   0.4894   1.0000
   5.000   1.1571   0.01779   0.00839  -0.1158   0.4761   1.0000
   5.250   1.1810   0.01815   0.00869  -0.1151   0.4640   1.0000
   5.500   1.2047   0.01854   0.00899  -0.1144   0.4527   1.0000
   5.750   1.2281   0.01896   0.00938  -0.1137   0.4407   1.0000
   6.000   1.2508   0.01940   0.00981  -0.1128   0.4277   1.0000
   6.250   1.2730   0.01987   0.01024  -0.1119   0.4143   1.0000
   6.500   1.2948   0.02036   0.01070  -0.1110   0.4012   1.0000
   6.750   1.3161   0.02086   0.01119  -0.1100   0.3877   1.0000
   7.000   1.3373   0.02136   0.01173  -0.1090   0.3751   1.0000
   7.250   1.3587   0.02184   0.01230  -0.1081   0.3633   1.0000
   7.500   1.3797   0.02234   0.01287  -0.1071   0.3526   1.0000
   7.750   1.4000   0.02287   0.01347  -0.1060   0.3421   1.0000
   8.000   1.4199   0.02339   0.01411  -0.1049   0.3301   1.0000
   8.250   1.4389   0.02395   0.01478  -0.1036   0.3176   1.0000
   8.500   1.4566   0.02455   0.01546  -0.1022   0.3036   1.0000
   8.750   1.4727   0.02522   0.01621  -0.1006   0.2883   1.0000
   9.000   1.4873   0.02595   0.01699  -0.0987   0.2722   1.0000
   9.250   1.4994   0.02680   0.01785  -0.0966   0.2544   1.0000
   9.500   1.5079   0.02779   0.01880  -0.0941   0.2354   1.0000
   9.750   1.5146   0.02887   0.01986  -0.0913   0.2160   1.0000
  10.000   1.5201   0.03010   0.02108  -0.0886   0.1973   1.0000
  10.250   1.5250   0.03146   0.02246  -0.0861   0.1810   1.0000
  10.500   1.5298   0.03292   0.02393  -0.0838   0.1675   1.0000
  10.750   1.5332   0.03456   0.02559  -0.0815   0.1552   1.0000
  11.000   1.5351   0.03639   0.02744  -0.0794   0.1443   1.0000
  11.250   1.5350   0.03848   0.02953  -0.0774   0.1354   1.0000
  11.500   1.5382   0.04040   0.03157  -0.0757   0.1276   1.0000
  11.750   1.5368   0.04281   0.03405  -0.0741   0.1210   1.0000
  12.000   1.5402   0.04488   0.03629  -0.0728   0.1134   1.0000
  12.250   1.5377   0.04760   0.03909  -0.0715   0.1063   1.0000
  12.500   1.5406   0.04991   0.04160  -0.0706   0.0945   1.0000
  12.750   1.5410   0.05254   0.04438  -0.0698   0.0763   1.0000
  13.000   1.5313   0.05642   0.04818  -0.0692   0.0657   1.0000
  13.250   1.5190   0.06076   0.05248  -0.0689   0.0591   1.0000
  13.500   1.5086   0.06504   0.05685  -0.0687   0.0532   1.0000
  13.750   1.4951   0.06988   0.06177  -0.0689   0.0490   1.0000
  14.000   1.4874   0.07414   0.06624  -0.0691   0.0434   1.0000
  14.500   1.4670   0.08385   0.07626  -0.0705   0.0344   1.0000
  14.750   1.4552   0.08919   0.08172  -0.0716   0.0317   1.0000
  15.000   1.4441   0.09461   0.08729  -0.0730   0.0296   1.0000
  15.250   1.4323   0.10031   0.09312  -0.0747   0.0282   1.0000
  15.500   1.4199   0.10623   0.09916  -0.0766   0.0271   1.0000
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