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GOE 15 AIRFOIL (goe15-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 15 AIRFOIL (goe15-il)
Reynolds number: 100,000
Max Cl/Cd: 46.59 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe15-il-100000.txt
Download as CSV file: xf-goe15-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 15 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.1114   0.10041   0.09612  -0.0545   0.9481   0.0473
  -7.000  -0.0879   0.09533   0.09103  -0.0568   0.9430   0.0480
  -6.750  -0.0643   0.09158   0.08727  -0.0612   0.9363   0.0489
  -6.500  -0.0438   0.08846   0.08412  -0.0651   0.9273   0.0498
  -6.250  -0.0094   0.08463   0.08024  -0.0725   0.9228   0.0512
  -6.000   0.0072   0.08298   0.07855  -0.0764   0.9107   0.0523
  -5.750   0.0536   0.08002   0.07546  -0.0879   0.9060   0.0531
  -5.500   0.0608   0.07660   0.07207  -0.0862   0.8953   0.0536
  -5.250   0.0925   0.07245   0.06788  -0.0904   0.8906   0.0547
  -5.000   0.1100   0.07013   0.06553  -0.0920   0.8804   0.0558
  -4.750   0.1437   0.06708   0.06240  -0.0970   0.8736   0.0575
  -4.500   0.1727   0.06598   0.06115  -0.1013   0.8624   0.0592
  -4.250   0.2071   0.06273   0.05779  -0.1058   0.8555   0.0602
  -4.000   0.2197   0.05991   0.05498  -0.1049   0.8446   0.0611
  -3.750   0.2510   0.05687   0.05186  -0.1077   0.8376   0.0629
  -3.500   0.2707   0.05511   0.05002  -0.1082   0.8255   0.0646
  -3.000   0.3371   0.05154   0.04608  -0.1135   0.8055   0.0681
  -2.750   0.3546   0.04874   0.04327  -0.1130   0.7942   0.0694
  -2.500   0.3855   0.04632   0.04070  -0.1145   0.7852   0.0726
  -2.250   0.4251   0.04705   0.04101  -0.1165   0.7712   0.0767
  -2.000   0.4394   0.04348   0.03750  -0.1156   0.7588   0.0779
  -1.750   0.4652   0.04118   0.03508  -0.1160   0.7479   0.0805
  -1.500   0.4935   0.04006   0.03374  -0.1162   0.7340   0.0849
  -1.250   0.5215   0.03925   0.03267  -0.1162   0.7190   0.0877
  -1.000   0.5407   0.03720   0.03057  -0.1155   0.7048   0.0905
  -0.750   0.5762   0.03810   0.03100  -0.1157   0.6909   0.0982
  -0.500   0.5947   0.03485   0.02778  -0.1155   0.6796   0.1014
  -0.250   0.6228   0.03535   0.02795  -0.1148   0.6650   0.1103
   0.000   0.6401   0.03299   0.02563  -0.1140   0.6527   0.1139
   0.250   0.6708   0.03229   0.02460  -0.1142   0.6433   0.1241
   0.500   0.6935   0.03216   0.02430  -0.1131   0.6307   0.1362
   0.750   0.7168   0.03111   0.02312  -0.1126   0.6212   0.1501
   1.000   0.7388   0.02949   0.02145  -0.1122   0.6121   0.1667
   1.250   0.7591   0.02842   0.02033  -0.1115   0.6030   0.2002
   2.000   0.8254   0.02551   0.01724  -0.1094   0.5798   0.3249
   2.250   0.8537   0.02503   0.01656  -0.1092   0.5734   0.3463
   2.500   0.8764   0.02457   0.01612  -0.1083   0.5654   0.3577
   2.750   0.9081   0.02432   0.01561  -0.1084   0.5596   0.3643
   3.000   0.9325   0.02433   0.01561  -0.1076   0.5526   0.3618
   3.250   0.9623   0.02449   0.01561  -0.1074   0.5462   0.3356
   3.500   0.9973   0.02510   0.01581  -0.1074   0.5410   0.2780
   3.750   1.0194   0.02561   0.01631  -0.1059   0.5338   0.2420
   4.000   1.0487   0.02580   0.01632  -0.1055   0.5283   0.2146
   4.250   1.0785   0.02609   0.01641  -0.1052   0.5234   0.1940
   4.500   1.0979   0.02661   0.01697  -0.1036   0.5167   0.1785
   4.750   1.1277   0.02662   0.01688  -0.1035   0.5112   0.1657
   5.000   1.1566   0.02682   0.01700  -0.1035   0.5059   0.1611
   5.250   1.1752   0.02722   0.01749  -0.1020   0.4989   0.1605
   5.500   1.2045   0.02713   0.01726  -0.1018   0.4927   0.1568
   5.750   1.2227   0.02763   0.01778  -0.1002   0.4858   0.1547
   6.000   1.2451   0.02787   0.01799  -0.0992   0.4788   0.1549
   6.250   1.2759   0.02802   0.01795  -0.0995   0.4733   0.1611
   6.500   1.2871   0.02885   0.01894  -0.0970   0.4664   0.1634
   6.750   1.3123   0.02917   0.01920  -0.0965   0.4605   0.1680
   7.000   1.3389   0.02964   0.01960  -0.0963   0.4551   0.1788
   7.250   1.3674   0.02958   0.02087  -0.0977   0.4474   1.0000
   7.500   1.3954   0.02995   0.02107  -0.0975   0.4416   1.0000
   7.750   1.4107   0.03086   0.02201  -0.0956   0.4353   1.0000
   8.000   1.4262   0.03162   0.02279  -0.0938   0.4284   1.0000
   8.250   1.4587   0.03191   0.02287  -0.0944   0.4228   1.0000
   8.500   1.4624   0.03320   0.02437  -0.0910   0.4159   1.0000
   8.750   1.4823   0.03378   0.02494  -0.0899   0.4091   1.0000
   9.000   1.5100   0.03427   0.02533  -0.0899   0.4030   1.0000
   9.250   1.5103   0.03550   0.02680  -0.0861   0.3951   1.0000
   9.500   1.5437   0.03553   0.02670  -0.0868   0.3886   1.0000
   9.750   1.5429   0.03693   0.02831  -0.0830   0.3812   1.0000
  10.000   1.5610   0.03748   0.02890  -0.0816   0.3741   1.0000
  10.250   1.5837   0.03804   0.02947  -0.0810   0.3677   1.0000
  10.500   1.5780   0.03943   0.03107  -0.0766   0.3600   1.0000
  10.750   1.6240   0.03887   0.03032  -0.0789   0.3534   1.0000
  11.000   1.5983   0.04104   0.03283  -0.0720   0.3462   1.0000
  11.250   1.6229   0.04115   0.03292  -0.0715   0.3394   1.0000
  11.500   1.6290   0.04223   0.03410  -0.0688   0.3334   1.0000
  11.750   1.6072   0.04416   0.03622  -0.0627   0.3273   1.0000
  12.000   1.6765   0.04261   0.03445  -0.0676   0.3201   1.0000
  12.250   1.6203   0.04611   0.03830  -0.0580   0.3156   1.0000
  12.500   1.6062   0.04817   0.04051  -0.0541   0.3099   1.0000
  12.750   1.6624   0.04628   0.03849  -0.0562   0.3029   1.0000
  13.000   1.5974   0.05194   0.04448  -0.0491   0.2994   1.0000
  13.250   1.0514   0.13479   0.12776  -0.0678   0.2683   1.0000
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