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GOE 458 AIRFOIL (goe458-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 458 AIRFOIL (goe458-il)
Reynolds number: 1,000,000
Max Cl/Cd: 140.9 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe458-il-1000000.txt
Download as CSV file: xf-goe458-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 458 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2472   0.11804   0.11652  -0.0348   1.0000   0.0049
 -11.000  -0.2463   0.11546   0.11395  -0.0345   1.0000   0.0050
 -10.750  -0.2464   0.11303   0.11155  -0.0339   1.0000   0.0051
 -10.500  -0.2415   0.10971   0.10823  -0.0349   0.9996   0.0051
 -10.250  -0.2327   0.10584   0.10436  -0.0372   0.9988   0.0053
 -10.000  -0.2239   0.10187   0.10039  -0.0394   0.9979   0.0055
  -9.750  -0.2151   0.09787   0.09639  -0.0417   0.9967   0.0057
  -9.500  -0.2061   0.09379   0.09231  -0.0442   0.9952   0.0060
  -9.250  -0.1975   0.08975   0.08827  -0.0464   0.9934   0.0062
  -9.000  -0.1890   0.08554   0.08407  -0.0488   0.9909   0.0069
  -8.750  -0.1799   0.08140   0.07993  -0.0517   0.9882   0.0073
  -8.500  -0.1701   0.07725   0.07578  -0.0546   0.9856   0.0074
  -8.250  -0.1593   0.07297   0.07150  -0.0578   0.9832   0.0076
  -8.000  -0.1511   0.06878   0.06732  -0.0603   0.9779   0.0076
  -7.750  -0.1404   0.06424   0.06278  -0.0638   0.9737   0.0077
  -7.500  -0.1266   0.05924   0.05777  -0.0685   0.9704   0.0077
  -7.250  -0.1139   0.05429   0.05282  -0.0733   0.9623   0.0077
  -7.000  -0.1112   0.04719   0.04570  -0.0796   0.9483   0.0080
  -6.750  -0.1012   0.04314   0.04161  -0.0837   0.9342   0.0084
  -6.500  -0.0912   0.03980   0.03820  -0.0867   0.9204   0.0086
  -6.250  -0.0808   0.03647   0.03481  -0.0896   0.9078   0.0088
  -6.000  -0.0682   0.03306   0.03134  -0.0928   0.8969   0.0091
  -5.750  -0.0533   0.02966   0.02787  -0.0962   0.8869   0.0098
  -5.500  -0.0359   0.02561   0.02373  -0.1002   0.8776   0.0105
  -5.250  -0.0153   0.02106   0.01907  -0.1047   0.8696   0.0110
  -5.000   0.0084   0.01620   0.01404  -0.1092   0.8628   0.0117
  -4.750   0.0354   0.01202   0.00962  -0.1124   0.8572   0.0126
  -4.500   0.0603   0.00954   0.00682  -0.1141   0.8505   0.0130
  -4.250   0.0842   0.00738   0.00432  -0.1151   0.8441   0.0130
  -4.000   0.1084   0.00573   0.00232  -0.1157   0.8373   0.0131
  -3.750   0.1396   0.01088   0.00618  -0.1214   0.8469   0.0084
  -3.500   0.1653   0.00972   0.00485  -0.1209   0.8392   0.0089
  -3.250   0.1918   0.00930   0.00433  -0.1207   0.8320   0.0102
  -3.000   0.2183   0.00877   0.00369  -0.1203   0.8241   0.0111
  -2.750   0.2449   0.00833   0.00316  -0.1199   0.8166   0.0118
  -2.500   0.2718   0.00811   0.00286  -0.1196   0.8082   0.0128
  -2.000   0.3247   0.00710   0.00155  -0.1187   0.7904   0.0163
  -1.750   0.3515   0.00692   0.00129  -0.1184   0.7805   0.0193
  -1.500   0.3781   0.00664   0.00105  -0.1180   0.7700   0.0526
  -1.250   0.4041   0.00639   0.00100  -0.1178   0.7585   0.1363
  -1.000   0.4307   0.00638   0.00096  -0.1175   0.7447   0.1514
  -0.750   0.4568   0.00639   0.00091  -0.1171   0.7271   0.1655
  -0.500   0.4827   0.00642   0.00088  -0.1166   0.7067   0.1784
  -0.250   0.5084   0.00645   0.00087  -0.1162   0.6869   0.1951
   0.000   0.5342   0.00647   0.00087  -0.1158   0.6699   0.2148
   0.250   0.5602   0.00647   0.00089  -0.1155   0.6545   0.2513
   0.500   0.5862   0.00646   0.00093  -0.1151   0.6402   0.2966
   0.750   0.6121   0.00644   0.00097  -0.1148   0.6270   0.3499
   1.000   0.6362   0.00610   0.00107  -0.1143   0.6149   0.5501
   1.250   0.6745   0.00528   0.00119  -0.1169   0.6019   1.0000
   1.500   0.7007   0.00538   0.00123  -0.1165   0.5913   1.0000
   1.750   0.7270   0.00547   0.00128  -0.1162   0.5831   1.0000
   2.250   0.7794   0.00567   0.00140  -0.1156   0.5659   1.0000
   2.500   0.8055   0.00577   0.00149  -0.1152   0.5575   1.0000
   2.750   0.8313   0.00590   0.00157  -0.1148   0.5454   1.0000
   3.000   0.8560   0.00608   0.00166  -0.1142   0.5213   1.0000
   3.250   0.8809   0.00627   0.00176  -0.1137   0.4972   1.0000
   3.500   0.9053   0.00649   0.00188  -0.1131   0.4697   1.0000
   3.750   0.9259   0.00701   0.00211  -0.1118   0.4013   1.0000
   4.000   0.9375   0.00837   0.00272  -0.1091   0.2528   1.0000
   4.250   0.9524   0.00949   0.00326  -0.1071   0.1478   1.0000
   4.500   0.9642   0.01093   0.00412  -0.1044   0.0180   1.0000
   4.750   0.9877   0.01129   0.00454  -0.1035   0.0138   1.0000
   5.000   1.0106   0.01170   0.00504  -0.1025   0.0116   1.0000
   5.250   1.0336   0.01208   0.00547  -0.1017   0.0106   1.0000
   5.500   1.0558   0.01253   0.00598  -0.1006   0.0098   1.0000
   5.750   1.0772   0.01305   0.00656  -0.0995   0.0087   1.0000
   6.000   1.0968   0.01372   0.00729  -0.0980   0.0079   1.0000
   6.250   1.1131   0.01466   0.00833  -0.0959   0.0074   1.0000
   6.500   1.1195   0.01642   0.01022  -0.0921   0.0068   1.0000
   6.750   1.1350   0.01739   0.01126  -0.0900   0.0065   1.0000
   7.000   1.1526   0.01820   0.01212  -0.0882   0.0063   1.0000
   7.250   1.1707   0.01896   0.01294  -0.0866   0.0060   1.0000
   7.500   1.1883   0.01983   0.01387  -0.0849   0.0056   1.0000
   7.750   1.2054   0.02099   0.01509  -0.0831   0.0052   1.0000
   8.000   1.2243   0.02257   0.01674  -0.0816   0.0049   1.0000
   8.750   1.2636   0.02921   0.02437  -0.0765   0.0066   1.0000
   9.000   1.2721   0.03236   0.02775  -0.0740   0.0066   1.0000
   9.250   1.2775   0.03550   0.03112  -0.0712   0.0066   1.0000
   9.500   1.2792   0.03859   0.03443  -0.0680   0.0065   1.0000
   9.750   1.2780   0.04125   0.03730  -0.0645   0.0065   1.0000
  10.000   1.2735   0.04338   0.03962  -0.0607   0.0064   1.0000
  10.250   1.2781   0.04149   0.03781  -0.0566   0.0059   1.0000
  10.500   1.2707   0.04316   0.03963  -0.0525   0.0056   1.0000
  10.750   1.2569   0.04571   0.04234  -0.0485   0.0054   1.0000
  11.000   1.2412   0.04876   0.04556  -0.0452   0.0053   1.0000
  11.250   1.2226   0.05256   0.04953  -0.0425   0.0052   1.0000
  11.500   1.2033   0.05680   0.05394  -0.0406   0.0051   1.0000
  11.750   1.1820   0.06176   0.05906  -0.0394   0.0051   1.0000
  12.000   1.1593   0.06727   0.06473  -0.0391   0.0051   1.0000
  12.250   1.1344   0.07348   0.07110  -0.0396   0.0052   1.0000
  12.500   1.1087   0.08002   0.07778  -0.0410   0.0052   1.0000
  12.750   1.0815   0.08691   0.08482  -0.0434   0.0053   1.0000
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