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GOE 510 AIRFOIL (goe510-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 510 AIRFOIL (goe510-il)
Reynolds number: 200,000
Max Cl/Cd: 65.91 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe510-il-200000.txt
Download as CSV file: xf-goe510-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 510 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.1570   0.09719   0.09372  -0.0658   0.9616   0.0691
  -8.000  -0.1794   0.09339   0.08994  -0.0774   0.9496   0.0720
  -7.750  -0.1757   0.08805   0.08457  -0.0824   0.9432   0.0727
  -7.500  -0.1390   0.08452   0.08104  -0.0826   0.9426   0.0737
  -7.250  -0.1223   0.08219   0.07872  -0.0821   0.9357   0.0749
  -7.000  -0.1057   0.07925   0.07576  -0.0845   0.9298   0.0769
  -6.750  -0.0974   0.07592   0.07241  -0.0875   0.9214   0.0799
  -6.500  -0.0969   0.06907   0.06537  -0.0978   0.9115   0.0843
  -6.250  -0.0868   0.06693   0.06326  -0.0955   0.9021   0.0851
  -6.000  -0.0596   0.06430   0.06063  -0.0969   0.8987   0.0867
  -5.750  -0.0308   0.06122   0.05749  -0.1002   0.8962   0.0900
  -5.500  -0.0336   0.05640   0.05239  -0.1029   0.8831   0.0969
  -5.250  -0.0028   0.05388   0.04990  -0.1043   0.8813   0.0984
  -5.000   0.0319   0.05162   0.04762  -0.1068   0.8797   0.1020
  -4.750   0.0341   0.04818   0.04389  -0.1063   0.8672   0.1110
  -4.500   0.0695   0.04591   0.04166  -0.1085   0.8651   0.1132
  -4.250   0.0899   0.04422   0.03992  -0.1080   0.8573   0.1170
  -4.000   0.1154   0.04098   0.03643  -0.1100   0.8507   0.1269
  -3.750   0.1555   0.03895   0.03437  -0.1131   0.8477   0.1314
  -3.500   0.1395   0.02820   0.02226  -0.1071   0.8348   0.0977
  -3.250   0.1743   0.02375   0.01691  -0.1079   0.8309   0.0826
  -3.000   0.1916   0.02223   0.01518  -0.1056   0.8202   0.0818
  -2.750   0.2335   0.02050   0.01312  -0.1081   0.8147   0.0815
  -2.500   0.2565   0.01974   0.01215  -0.1067   0.8037   0.0824
  -2.250   0.2998   0.01886   0.01097  -0.1094   0.7967   0.0834
  -2.000   0.3211   0.01790   0.00989  -0.1078   0.7844   0.0841
  -1.750   0.3530   0.01698   0.00889  -0.1084   0.7743   0.0853
  -1.500   0.3864   0.01630   0.00814  -0.1092   0.7637   0.0870
  -1.250   0.4091   0.01590   0.00773  -0.1079   0.7504   0.0890
  -1.000   0.4353   0.01555   0.00732  -0.1073   0.7377   0.0920
  -0.750   0.4635   0.01521   0.00689  -0.1070   0.7251   0.0947
  -0.500   0.4903   0.01483   0.00643  -0.1065   0.7119   0.0972
  -0.250   0.5105   0.01455   0.00616  -0.1046   0.6970   0.1004
   0.000   0.5319   0.01439   0.00596  -0.1030   0.6818   0.1056
   0.250   0.5531   0.01425   0.00577  -0.1014   0.6665   0.1124
   0.500   0.5740   0.01415   0.00563  -0.0998   0.6510   0.1237
   0.750   0.5930   0.01394   0.00561  -0.0978   0.6354   0.1705
   1.000   0.6137   0.01403   0.00581  -0.0961   0.6198   0.2583
   1.250   0.6349   0.01424   0.00593  -0.0946   0.6045   0.2906
   1.500   0.6560   0.01440   0.00600  -0.0931   0.5902   0.3129
   1.750   0.6745   0.01450   0.00606  -0.0911   0.5760   0.3310
   2.000   0.6920   0.01457   0.00611  -0.0889   0.5626   0.3471
   2.250   0.7106   0.01463   0.00614  -0.0870   0.5508   0.3637
   2.500   0.7299   0.01466   0.00613  -0.0853   0.5403   0.3851
   3.000   0.7566   0.01413   0.00615  -0.0794   0.5211   0.5825
   3.250   0.9860   0.01509   0.00757  -0.1217   0.4968   1.0000
   3.500   1.0056   0.01536   0.00767  -0.1201   0.4894   1.0000
   3.750   1.0207   0.01556   0.00786  -0.1177   0.4819   1.0000
   4.000   1.0389   0.01580   0.00800  -0.1158   0.4750   1.0000
   4.250   1.0568   0.01607   0.00820  -0.1139   0.4682   1.0000
   4.500   1.0726   0.01629   0.00840  -0.1116   0.4615   1.0000
   4.750   1.0961   0.01663   0.00859  -0.1109   0.4554   1.0000
   5.000   1.1094   0.01686   0.00886  -0.1081   0.4495   1.0000
   5.250   1.1260   0.01711   0.00908  -0.1059   0.4435   1.0000
   5.500   1.1505   0.01748   0.00932  -0.1055   0.4376   1.0000
   5.750   1.1614   0.01771   0.00962  -0.1022   0.4319   1.0000
   6.000   1.1777   0.01799   0.00987  -0.1000   0.4261   1.0000
   6.250   1.2048   0.01840   0.01016  -0.1002   0.4207   1.0000
   6.500   1.2135   0.01865   0.01051  -0.0965   0.4155   1.0000
   6.750   1.2285   0.01893   0.01079  -0.0941   0.4100   1.0000
   7.000   1.2536   0.01933   0.01108  -0.0938   0.4044   1.0000
   7.250   1.2629   0.01962   0.01146  -0.0903   0.3993   1.0000
   7.500   1.2747   0.01990   0.01179  -0.0873   0.3939   1.0000
   7.750   1.2947   0.02024   0.01207  -0.0860   0.3889   1.0000
   8.000   1.3095   0.02061   0.01247  -0.0836   0.3837   1.0000
   8.250   1.3150   0.02086   0.01279  -0.0794   0.3783   1.0000
   8.500   1.3280   0.02110   0.01301  -0.0767   0.3727   1.0000
   8.750   1.3388   0.02142   0.01333  -0.0737   0.3666   1.0000
   9.000   1.3414   0.02165   0.01364  -0.0691   0.3604   1.0000
   9.250   1.3537   0.02189   0.01379  -0.0664   0.3538   1.0000
   9.500   1.3545   0.02220   0.01421  -0.0617   0.3470   1.0000
   9.750   1.3601   0.02248   0.01452  -0.0580   0.3403   1.0000
  10.000   1.3699   0.02286   0.01489  -0.0552   0.3338   1.0000
  10.250   1.3732   0.02328   0.01541  -0.0513   0.3268   1.0000
  10.500   1.3833   0.02369   0.01573  -0.0487   0.3202   1.0000
  10.750   1.3876   0.02426   0.01645  -0.0453   0.3135   1.0000
  11.000   1.3945   0.02480   0.01701  -0.0425   0.3067   1.0000
  11.250   1.4013   0.02544   0.01772  -0.0397   0.2998   1.0000
  11.500   1.4069   0.02615   0.01848  -0.0370   0.2924   1.0000
  11.750   1.4129   0.02693   0.01928  -0.0344   0.2851   1.0000
  12.000   1.4188   0.02779   0.02022  -0.0319   0.2775   1.0000
  12.250   1.4240   0.02875   0.02120  -0.0295   0.2701   1.0000
  12.500   1.4276   0.02984   0.02236  -0.0272   0.2611   1.0000
  12.750   1.4301   0.03109   0.02364  -0.0249   0.2517   1.0000
  13.000   1.4310   0.03253   0.02507  -0.0226   0.2425   1.0000
  13.250   1.4331   0.03403   0.02665  -0.0206   0.2317   1.0000
  13.500   1.4329   0.03580   0.02844  -0.0187   0.2205   1.0000
  13.750   1.4316   0.03775   0.03039  -0.0169   0.2112   1.0000
  14.000   1.4272   0.04010   0.03273  -0.0152   0.1974   1.0000
  14.250   1.4240   0.04250   0.03515  -0.0138   0.1840   1.0000
  14.500   1.4174   0.04535   0.03798  -0.0125   0.1697   1.0000
  14.750   1.4117   0.04825   0.04089  -0.0114   0.1568   1.0000
  15.000   1.3983   0.05206   0.04464  -0.0105   0.1407   1.0000
  15.250   1.3824   0.05634   0.04887  -0.0098   0.1242   1.0000
  15.500   1.3690   0.06051   0.05304  -0.0094   0.1126   1.0000
  15.750   1.3542   0.06499   0.05752  -0.0093   0.1013   1.0000
  16.000   1.3376   0.06986   0.06240  -0.0094   0.0894   1.0000
  16.250   1.3167   0.07545   0.06798  -0.0099   0.0742   1.0000
  16.500   1.2939   0.08145   0.07396  -0.0107   0.0520   1.0000
  16.750   1.2692   0.08792   0.08040  -0.0118   0.0422   1.0000
  17.000   1.2518   0.09350   0.08603  -0.0128   0.0393   1.0000
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