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GOE 442 AIRFOIL (goe442-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 442 AIRFOIL (goe442-il)
Reynolds number: 100,000
Max Cl/Cd: 54.28 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe442-il-100000.txt
Download as CSV file: xf-goe442-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 442 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3613   0.09889   0.09406  -0.0242   1.0000   0.0694
  -7.750  -0.3750   0.09808   0.09338  -0.0254   1.0000   0.0700
  -7.500  -0.3793   0.09637   0.09174  -0.0295   1.0000   0.0704
  -7.250  -0.3792   0.09409   0.08951  -0.0340   1.0000   0.0707
  -7.000  -0.3653   0.08743   0.08289  -0.0219   1.0000   0.0740
  -6.750  -0.3626   0.08484   0.08034  -0.0210   1.0000   0.0770
  -6.500  -0.3619   0.08229   0.07784  -0.0215   1.0000   0.0795
  -6.250  -0.3605   0.07974   0.07533  -0.0248   1.0000   0.0827
  -6.000  -0.3509   0.07710   0.07254  -0.0363   1.0000   0.0849
  -5.750  -0.3507   0.07270   0.06832  -0.0299   1.0000   0.0863
  -5.500  -0.3459   0.06998   0.06565  -0.0268   1.0000   0.0886
  -5.250  -0.3381   0.06725   0.06293  -0.0266   1.0000   0.0924
  -5.000  -0.3166   0.06308   0.05851  -0.0357   1.0000   0.1000
  -4.750  -0.3129   0.06021   0.05578  -0.0316   1.0000   0.1023
  -4.500  -0.3018   0.05773   0.05330  -0.0309   1.0000   0.1077
  -4.250  -0.2833   0.05410   0.04954  -0.0341   1.0000   0.1165
  -4.000  -0.2649   0.05135   0.04663  -0.0359   1.0000   0.1300
  -3.750  -0.2481   0.04897   0.04415  -0.0365   1.0000   0.1444
  -3.500  -0.2378   0.04671   0.04200  -0.0341   1.0000   0.1516
  -3.250  -0.2198   0.04434   0.03955  -0.0345   1.0000   0.1676
  -3.000  -0.2001   0.04209   0.03716  -0.0355   1.0000   0.1907
  -2.750  -0.1855   0.04018   0.03530  -0.0342   1.0000   0.2093
  -2.250  -0.0949   0.02919   0.02246  -0.0424   1.0000   0.1174
  -2.000  -0.0557   0.02607   0.01827  -0.0433   0.9981   0.1000
  -1.750  -0.0053   0.02387   0.01556  -0.0472   0.9895   0.1002
  -1.500   0.0439   0.02239   0.01394  -0.0514   0.9797   0.1084
  -1.250   0.0959   0.02113   0.01234  -0.0556   0.9701   0.1159
  -1.000   0.1448   0.02011   0.01127  -0.0593   0.9580   0.1246
  -0.750   0.1921   0.01916   0.01038  -0.0627   0.9448   0.1389
  -0.500   0.2391   0.01824   0.00955  -0.0658   0.9311   0.1550
  -0.250   0.2864   0.01726   0.00885  -0.0690   0.9169   0.1993
   0.000   0.3569   0.01462   0.00816  -0.0764   0.9101   1.0000
   0.250   0.4057   0.01423   0.00754  -0.0796   0.8924   1.0000
   0.500   0.4523   0.01378   0.00692  -0.0822   0.8732   1.0000
   0.750   0.4945   0.01338   0.00637  -0.0838   0.8498   1.0000
   1.000   0.5347   0.01304   0.00588  -0.0851   0.8232   1.0000
   1.250   0.5698   0.01289   0.00555  -0.0855   0.7919   1.0000
   1.500   0.6014   0.01291   0.00537  -0.0854   0.7600   1.0000
   1.750   0.6303   0.01308   0.00532  -0.0848   0.7301   1.0000
   2.000   0.6574   0.01333   0.00538  -0.0841   0.7028   1.0000
   2.250   0.6835   0.01363   0.00547  -0.0832   0.6776   1.0000
   2.500   0.7078   0.01396   0.00564  -0.0821   0.6524   1.0000
   2.750   0.7323   0.01428   0.00581  -0.0810   0.6292   1.0000
   3.000   0.7562   0.01461   0.00598  -0.0799   0.6060   1.0000
   3.250   0.7800   0.01497   0.00618  -0.0787   0.5842   1.0000
   3.500   0.8036   0.01533   0.00643  -0.0776   0.5635   1.0000
   3.750   0.8280   0.01574   0.00676  -0.0767   0.5459   1.0000
   4.000   0.8526   0.01617   0.00712  -0.0759   0.5303   1.0000
   4.250   0.8770   0.01661   0.00751  -0.0751   0.5148   1.0000
   4.500   0.9011   0.01703   0.00790  -0.0742   0.4991   1.0000
   4.750   0.9248   0.01744   0.00829  -0.0732   0.4830   1.0000
   5.000   0.9478   0.01780   0.00867  -0.0721   0.4660   1.0000
   5.250   0.9701   0.01813   0.00904  -0.0709   0.4476   1.0000
   5.500   0.9922   0.01844   0.00939  -0.0696   0.4285   1.0000
   5.750   1.0141   0.01875   0.00968  -0.0683   0.4083   1.0000
   6.000   1.0341   0.01905   0.01004  -0.0666   0.3827   1.0000
   6.250   1.0533   0.01945   0.01038  -0.0648   0.3531   1.0000
   6.500   1.0717   0.02004   0.01082  -0.0630   0.3214   1.0000
   6.750   1.0908   0.02078   0.01147  -0.0614   0.2935   1.0000
   7.000   1.1116   0.02163   0.01219  -0.0601   0.2737   1.0000
   7.250   1.1337   0.02251   0.01304  -0.0591   0.2589   1.0000
   7.500   1.1567   0.02341   0.01391  -0.0583   0.2476   1.0000
   7.750   1.1794   0.02431   0.01496  -0.0574   0.2376   1.0000
   8.000   1.2027   0.02530   0.01598  -0.0567   0.2294   1.0000
   8.250   1.2262   0.02631   0.01710  -0.0560   0.2222   1.0000
   8.500   1.2498   0.02745   0.01833  -0.0553   0.2156   1.0000
   8.750   1.2713   0.02835   0.01936  -0.0544   0.2072   1.0000
   9.000   1.2892   0.02917   0.02035  -0.0529   0.1967   1.0000
   9.250   1.3052   0.02978   0.02102  -0.0513   0.1842   1.0000
   9.500   1.3203   0.03046   0.02176  -0.0497   0.1719   1.0000
   9.750   1.3359   0.03129   0.02262  -0.0481   0.1604   1.0000
  10.000   1.3497   0.03217   0.02355  -0.0464   0.1482   1.0000
  10.250   1.3584   0.03304   0.02457  -0.0439   0.1344   1.0000
  10.500   1.3592   0.03400   0.02581  -0.0403   0.1180   1.0000
  10.750   1.3545   0.03520   0.02715  -0.0361   0.0989   1.0000
  11.000   1.3485   0.03652   0.02852  -0.0317   0.0844   1.0000
  11.250   1.3460   0.03818   0.03026  -0.0282   0.0739   1.0000
  11.500   1.3451   0.04007   0.03221  -0.0253   0.0668   1.0000
  11.750   1.3437   0.04188   0.03404  -0.0229   0.0613   1.0000
  12.000   1.3442   0.04437   0.03666  -0.0208   0.0571   1.0000
  12.250   1.3457   0.04690   0.03938  -0.0190   0.0539   1.0000
  12.500   1.3471   0.04945   0.04196  -0.0175   0.0513   1.0000
  12.750   1.3499   0.05280   0.04539  -0.0162   0.0491   1.0000
  13.000   1.3453   0.05613   0.04905  -0.0151   0.0477   1.0000
  13.250   1.3388   0.05978   0.05298  -0.0144   0.0465   1.0000
  13.500   1.3297   0.06379   0.05724  -0.0143   0.0454   1.0000
  13.750   1.3192   0.06815   0.06185  -0.0148   0.0446   1.0000
  14.000   1.3077   0.07271   0.06660  -0.0158   0.0435   1.0000
  14.250   1.2926   0.07823   0.07237  -0.0176   0.0434   1.0000
  14.500   1.2718   0.08497   0.07938  -0.0206   0.0436   1.0000
  14.750   1.2470   0.09276   0.08743  -0.0247   0.0439   1.0000
  15.000   1.2105   0.10349   0.09847  -0.0313   0.0453   1.0000
  15.250   1.1701   0.11611   0.11131  -0.0395   0.0475   1.0000
  15.500   1.1390   0.12775   0.12302  -0.0467   0.0490   1.0000
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