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GOE 802 AIRFOIL (goe802-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 802 AIRFOIL (goe802-il)
Reynolds number: 100,000
Max Cl/Cd: 60.24 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe802-il-100000-n5.txt
Download as CSV file: xf-goe802-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2513   0.11516   0.11032  -0.0336   1.0000   0.0447
  -9.000  -0.2624   0.11451   0.10975  -0.0319   1.0000   0.0457
  -8.750  -0.2661   0.11338   0.10867  -0.0352   0.9960   0.0463
  -8.500  -0.2581   0.11093   0.10623  -0.0429   0.9872   0.0466
  -8.250  -0.2329   0.10476   0.10005  -0.0411   0.9868   0.0475
  -8.000  -0.2137   0.10088   0.09616  -0.0437   0.9825   0.0487
  -7.750  -0.1967   0.09742   0.09269  -0.0473   0.9760   0.0501
  -7.500  -0.1799   0.09406   0.08932  -0.0518   0.9691   0.0521
  -7.250  -0.1609   0.09138   0.08661  -0.0656   0.9567   0.0549
  -7.000  -0.1441   0.08707   0.08231  -0.0685   0.9496   0.0556
  -6.750  -0.1244   0.08318   0.07842  -0.0680   0.9461   0.0570
  -6.500  -0.1074   0.08011   0.07534  -0.0704   0.9384   0.0586
  -6.250  -0.0860   0.07682   0.07201  -0.0749   0.9313   0.0609
  -6.000  -0.0544   0.07380   0.06884  -0.0883   0.9201   0.0648
  -5.750  -0.0294   0.06948   0.06446  -0.0937   0.9138   0.0658
  -5.500  -0.0176   0.06646   0.06149  -0.0912   0.9075   0.0672
  -5.250   0.0007   0.06387   0.05889  -0.0919   0.9000   0.0700
  -5.000   0.0521   0.06154   0.05607  -0.1066   0.8911   0.0774
  -4.750   0.0638   0.05722   0.05189  -0.1054   0.8839   0.0785
  -4.500   0.0842   0.05422   0.04891  -0.1054   0.8790   0.0803
  -4.250   0.1026   0.05200   0.04666  -0.1058   0.8693   0.0829
  -4.000   0.1511   0.04945   0.04359  -0.1145   0.8632   0.0923
  -3.750   0.1653   0.04638   0.04062  -0.1135   0.8538   0.0939
  -3.500   0.1885   0.04409   0.03834  -0.1137   0.8476   0.0976
  -3.250   0.2201   0.04199   0.03595  -0.1168   0.8380   0.1095
  -3.000   0.2445   0.03972   0.03368  -0.1171   0.8313   0.1133
  -2.750   0.2922   0.03446   0.02751  -0.1210   0.8225   0.0644
  -2.500   0.3258   0.03105   0.02362  -0.1223   0.8155   0.0557
  -2.250   0.3520   0.02943   0.02185  -0.1223   0.8052   0.0538
  -2.000   0.3828   0.02762   0.01976  -0.1229   0.7975   0.0530
  -1.750   0.4105   0.02624   0.01806  -0.1227   0.7859   0.0534
  -1.500   0.4393   0.02494   0.01645  -0.1227   0.7754   0.0534
  -1.250   0.4691   0.02366   0.01489  -0.1227   0.7658   0.0527
  -1.000   0.4966   0.02267   0.01366  -0.1223   0.7536   0.0521
  -0.750   0.5249   0.02176   0.01252  -0.1220   0.7426   0.0517
  -0.500   0.5541   0.02092   0.01145  -0.1217   0.7324   0.0515
  -0.250   0.5813   0.02027   0.01065  -0.1213   0.7199   0.0516
   0.000   0.6087   0.01971   0.00995  -0.1208   0.7077   0.0521
   0.250   0.6364   0.01926   0.00937  -0.1204   0.6960   0.0538
   0.500   0.6642   0.01885   0.00883  -0.1200   0.6846   0.0553
   0.750   0.6907   0.01840   0.00838  -0.1195   0.6716   0.0562
   1.000   0.7172   0.01808   0.00803  -0.1190   0.6589   0.0572
   1.250   0.7438   0.01786   0.00773  -0.1185   0.6466   0.0585
   1.500   0.7708   0.01771   0.00747  -0.1180   0.6348   0.0603
   1.750   0.7978   0.01765   0.00730  -0.1176   0.6223   0.0630
   2.000   0.8247   0.01762   0.00720  -0.1173   0.6099   0.0686
   2.250   0.8516   0.01764   0.00712  -0.1169   0.5979   0.0766
   2.500   0.8788   0.01758   0.00709  -0.1166   0.5866   0.1046
   3.000   0.9283   0.01633   0.00733  -0.1152   0.5640   1.0000
   3.250   0.9545   0.01660   0.00741  -0.1148   0.5535   1.0000
   3.500   0.9800   0.01689   0.00759  -0.1143   0.5421   1.0000
   3.750   1.0055   0.01719   0.00779  -0.1138   0.5314   1.0000
   4.250   1.0564   0.01783   0.00827  -0.1129   0.5114   1.0000
   4.500   1.0816   0.01817   0.00853  -0.1124   0.5018   1.0000
   4.750   1.1065   0.01851   0.00881  -0.1119   0.4919   1.0000
   5.000   1.1308   0.01887   0.00915  -0.1113   0.4811   1.0000
   5.250   1.1548   0.01922   0.00943  -0.1107   0.4700   1.0000
   5.500   1.1780   0.01957   0.00972  -0.1099   0.4576   1.0000
   5.750   1.2005   0.01993   0.01009  -0.1090   0.4445   1.0000
   6.000   1.2233   0.02032   0.01047  -0.1082   0.4333   1.0000
   6.250   1.2464   0.02071   0.01081  -0.1075   0.4240   1.0000
   6.500   1.2688   0.02113   0.01128  -0.1067   0.4137   1.0000
   6.750   1.2913   0.02155   0.01173  -0.1059   0.4047   1.0000
   7.000   1.3131   0.02199   0.01219  -0.1050   0.3953   1.0000
   7.250   1.3348   0.02245   0.01270  -0.1041   0.3862   1.0000
   7.500   1.3560   0.02293   0.01319  -0.1032   0.3777   1.0000
   7.750   1.3764   0.02342   0.01378  -0.1021   0.3679   1.0000
   8.000   1.3959   0.02394   0.01430  -0.1009   0.3581   1.0000
   8.250   1.4142   0.02448   0.01489  -0.0995   0.3472   1.0000
   8.500   1.4318   0.02505   0.01555  -0.0981   0.3362   1.0000
   8.750   1.4484   0.02565   0.01618  -0.0965   0.3257   1.0000
   9.000   1.4632   0.02630   0.01687  -0.0947   0.3140   1.0000
   9.250   1.4763   0.02699   0.01764  -0.0927   0.3011   1.0000
   9.500   1.4869   0.02772   0.01845  -0.0903   0.2884   1.0000
   9.750   1.4961   0.02854   0.01932  -0.0878   0.2759   1.0000
  10.000   1.5046   0.02945   0.02028  -0.0853   0.2635   1.0000
  10.250   1.5123   0.03048   0.02134  -0.0829   0.2510   1.0000
  10.500   1.5200   0.03159   0.02255  -0.0807   0.2384   1.0000
  10.750   1.5266   0.03283   0.02385  -0.0786   0.2263   1.0000
  11.000   1.5314   0.03425   0.02529  -0.0764   0.2143   1.0000
  11.250   1.5344   0.03585   0.02691  -0.0742   0.2028   1.0000
  11.500   1.5354   0.03770   0.02874  -0.0721   0.1924   1.0000
  11.750   1.5374   0.03959   0.03068  -0.0703   0.1821   1.0000
  12.000   1.5381   0.04167   0.03281  -0.0686   0.1733   1.0000
  12.250   1.5372   0.04396   0.03513  -0.0670   0.1655   1.0000
  12.500   1.5385   0.04618   0.03745  -0.0657   0.1585   1.0000
  12.750   1.5372   0.04870   0.04004  -0.0644   0.1521   1.0000
  13.000   1.5364   0.05128   0.04271  -0.0634   0.1460   1.0000
  13.250   1.5350   0.05402   0.04557  -0.0625   0.1397   1.0000
  13.500   1.5303   0.05713   0.04874  -0.0618   0.1348   1.0000
  13.750   1.5305   0.05991   0.05171  -0.0613   0.1294   1.0000
  14.000   1.5272   0.06316   0.05509  -0.0610   0.1246   1.0000
  14.250   1.5218   0.06673   0.05872  -0.0609   0.1206   1.0000
  14.500   1.5205   0.06998   0.06218  -0.0609   0.1159   1.0000
  14.750   1.5162   0.07369   0.06603  -0.0611   0.1118   1.0000
  15.000   1.5098   0.07775   0.07018  -0.0615   0.1082   1.0000
  15.250   1.5056   0.08165   0.07427  -0.0621   0.1040   1.0000
  15.500   1.4990   0.08599   0.07877  -0.0629   0.0995   1.0000
  15.750   1.4898   0.09078   0.08365  -0.0640   0.0956   1.0000
  16.000   1.4836   0.09524   0.08828  -0.0650   0.0916   1.0000
  16.250   1.4756   0.10006   0.09326  -0.0664   0.0875   1.0000
  16.500   1.4653   0.10530   0.09859  -0.0680   0.0840   1.0000
  16.750   1.4575   0.11026   0.10371  -0.0696   0.0802   1.0000
  17.000   1.4486   0.11548   0.10906  -0.0714   0.0765   1.0000
  17.250   1.4382   0.12103   0.11469  -0.0736   0.0732   1.0000
  17.500   1.4297   0.12637   0.12017  -0.0758   0.0694   1.0000
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