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GOE 365 AIRFOIL (goe365-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 365 AIRFOIL (goe365-il)
Reynolds number: 200,000
Max Cl/Cd: 79.12 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe365-il-200000.txt
Download as CSV file: xf-goe365-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 365 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2694   0.11138   0.10799  -0.0388   1.0000   0.0341
  -9.750  -0.2751   0.10976   0.10645  -0.0368   1.0000   0.0344
  -9.500  -0.2929   0.10957   0.10637  -0.0323   1.0000   0.0346
  -9.250  -0.2750   0.10550   0.10230  -0.0368   0.9966   0.0355
  -9.000  -0.2563   0.10116   0.09795  -0.0422   0.9922   0.0370
  -8.750  -0.2389   0.09670   0.09349  -0.0494   0.9864   0.0386
  -8.500  -0.2281   0.09177   0.08857  -0.0639   0.9750   0.0396
  -8.250  -0.2096   0.08620   0.08300  -0.0672   0.9719   0.0403
  -8.000  -0.1900   0.08298   0.07978  -0.0672   0.9655   0.0412
  -7.750  -0.1686   0.07912   0.07590  -0.0718   0.9605   0.0427
  -7.500  -0.1536   0.07508   0.07184  -0.0775   0.9510   0.0442
  -7.250  -0.1254   0.06850   0.06513  -0.0935   0.9431   0.0474
  -7.000  -0.1080   0.06201   0.05836  -0.1038   0.9324   0.0485
  -6.750  -0.0836   0.05833   0.05477  -0.1049   0.9302   0.0496
  -6.500  -0.0672   0.05592   0.05235  -0.1053   0.9217   0.0511
  -6.250  -0.0414   0.05251   0.04882  -0.1093   0.9163   0.0545
  -6.000  -0.0282   0.04866   0.04437  -0.1128   0.9044   0.0592
  -5.750  -0.0047   0.04504   0.04086  -0.1142   0.9002   0.0607
  -5.500   0.0105   0.04310   0.03890  -0.1136   0.8919   0.0626
  -5.250   0.0329   0.04084   0.03646  -0.1144   0.8856   0.0666
  -5.000   0.0498   0.02200   0.01756  -0.1080   0.8607   0.0733
  -4.750   0.0678   0.03611   0.03130  -0.1136   0.8706   0.0753
  -4.250   0.1059   0.03255   0.02729  -0.1120   0.8563   0.0886
  -4.000   0.1316   0.03092   0.02556  -0.1123   0.8515   0.0946
  -3.750   0.1466   0.02950   0.02390  -0.1104   0.8433   0.1043
  -3.500   0.1702   0.02856   0.02267  -0.1098   0.8379   0.1186
  -3.250   0.1909   0.02682   0.02103  -0.1092   0.8319   0.1254
  -3.000   0.2114   0.02577   0.01988  -0.1083   0.8254   0.1430
  -2.000   0.3267   0.01998   0.01250  -0.1042   0.8037   0.0831
  -1.750   0.3498   0.01872   0.01111  -0.1029   0.7964   0.0774
  -1.500   0.3804   0.01854   0.01061  -0.1023   0.7909   0.0712
  -1.250   0.4063   0.01746   0.00949  -0.1016   0.7846   0.0696
  -1.000   0.4325   0.01676   0.00874  -0.1009   0.7778   0.0689
  -0.750   0.4625   0.01616   0.00806  -0.1009   0.7726   0.0690
  -0.500   0.4847   0.01591   0.00781  -0.0996   0.7641   0.0704
  -0.250   0.5133   0.01544   0.00730  -0.0993   0.7582   0.0713
   0.000   0.5346   0.01502   0.00692  -0.0979   0.7495   0.0723
   0.250   0.5618   0.01456   0.00642  -0.0974   0.7421   0.0745
   0.500   0.5834   0.01433   0.00619  -0.0958   0.7312   0.0773
   0.750   0.6088   0.01409   0.00586  -0.0949   0.7203   0.0827
   1.000   0.6356   0.01379   0.00549  -0.0941   0.7096   0.0956
   1.250   0.7340   0.01146   0.00535  -0.1087   0.6965   1.0000
   1.500   0.7554   0.01153   0.00532  -0.1073   0.6868   1.0000
   1.750   0.7795   0.01156   0.00522  -0.1063   0.6778   1.0000
   2.000   0.7991   0.01162   0.00524  -0.1045   0.6662   1.0000
   2.250   0.8205   0.01166   0.00522  -0.1030   0.6551   1.0000
   2.500   0.8426   0.01169   0.00516  -0.1016   0.6436   1.0000
   2.750   0.8639   0.01172   0.00512  -0.1001   0.6309   1.0000
   3.000   0.8841   0.01177   0.00513  -0.0984   0.6166   1.0000
   3.250   0.9047   0.01184   0.00513  -0.0968   0.6016   1.0000
   3.500   0.9252   0.01193   0.00515  -0.0952   0.5862   1.0000
   3.750   0.9455   0.01206   0.00519  -0.0936   0.5700   1.0000
   4.000   0.9652   0.01223   0.00527  -0.0918   0.5530   1.0000
   4.250   0.9843   0.01244   0.00539  -0.0900   0.5348   1.0000
   4.500   1.0030   0.01269   0.00553  -0.0882   0.5161   1.0000
   4.750   1.0211   0.01298   0.00572  -0.0862   0.4971   1.0000
   5.000   1.0388   0.01331   0.00592  -0.0843   0.4783   1.0000
   5.250   1.0559   0.01365   0.00617  -0.0822   0.4592   1.0000
   5.500   1.0727   0.01400   0.00645  -0.0801   0.4403   1.0000
   5.750   1.0887   0.01438   0.00675  -0.0780   0.4213   1.0000
   6.000   1.1038   0.01479   0.00706  -0.0756   0.4023   1.0000
   6.250   1.1180   0.01524   0.00741  -0.0732   0.3831   1.0000
   6.500   1.1320   0.01567   0.00779  -0.0707   0.3637   1.0000
   6.750   1.1450   0.01616   0.00820  -0.0682   0.3453   1.0000
   7.000   1.1572   0.01666   0.00862  -0.0655   0.3291   1.0000
   7.250   1.1689   0.01718   0.00907  -0.0627   0.3151   1.0000
   7.500   1.1813   0.01774   0.00955  -0.0602   0.3035   1.0000
   7.750   1.1942   0.01832   0.01007  -0.0578   0.2933   1.0000
   8.000   1.2090   0.01885   0.01060  -0.0558   0.2835   1.0000
   8.250   1.2236   0.01947   0.01115  -0.0538   0.2760   1.0000
   8.500   1.2400   0.01999   0.01172  -0.0522   0.2687   1.0000
   8.750   1.2565   0.02065   0.01231  -0.0507   0.2629   1.0000
   9.000   1.2733   0.02118   0.01292  -0.0492   0.2570   1.0000
   9.250   1.2898   0.02177   0.01353  -0.0477   0.2515   1.0000
   9.500   1.3090   0.02246   0.01416  -0.0467   0.2469   1.0000
   9.750   1.3246   0.02301   0.01485  -0.0452   0.2419   1.0000
  10.000   1.3389   0.02363   0.01550  -0.0435   0.2363   1.0000
  10.250   1.3536   0.02434   0.01621  -0.0420   0.2303   1.0000
  10.500   1.3643   0.02498   0.01696  -0.0400   0.2241   1.0000
  10.750   1.3787   0.02577   0.01767  -0.0386   0.2179   1.0000
  11.000   1.3885   0.02648   0.01857  -0.0366   0.2128   1.0000
  11.250   1.3988   0.02727   0.01943  -0.0348   0.2072   1.0000
  11.500   1.4100   0.02816   0.02033  -0.0333   0.2015   1.0000
  11.750   1.4186   0.02904   0.02137  -0.0315   0.1959   1.0000
  12.000   1.4280   0.03002   0.02238  -0.0299   0.1907   1.0000
  12.250   1.4364   0.03107   0.02355  -0.0283   0.1852   1.0000
  12.500   1.4428   0.03220   0.02481  -0.0268   0.1790   1.0000
  12.750   1.4485   0.03350   0.02613  -0.0253   0.1730   1.0000
  13.000   1.4546   0.03478   0.02760  -0.0240   0.1664   1.0000
  13.250   1.4579   0.03635   0.02917  -0.0226   0.1602   1.0000
  13.500   1.4639   0.03781   0.03086  -0.0217   0.1518   1.0000
  13.750   1.4673   0.03955   0.03268  -0.0207   0.1425   1.0000
  14.000   1.4700   0.04147   0.03469  -0.0199   0.1270   1.0000
  14.250   1.4673   0.04401   0.03716  -0.0190   0.1061   1.0000
  14.500   1.4550   0.04761   0.04061  -0.0181   0.0890   1.0000
  14.750   1.4441   0.05126   0.04423  -0.0173   0.0777   1.0000
  15.000   1.4360   0.05483   0.04784  -0.0169   0.0605   1.0000
  15.250   1.4176   0.05973   0.05263  -0.0168   0.0438   1.0000
  15.500   1.4038   0.06437   0.05729  -0.0171   0.0396   1.0000
  15.750   1.3898   0.06929   0.06230  -0.0178   0.0372   1.0000
  16.000   1.3742   0.07464   0.06777  -0.0188   0.0355   1.0000
  16.250   1.3593   0.08017   0.07343  -0.0202   0.0345   1.0000
  16.500   1.3447   0.08582   0.07923  -0.0218   0.0335   1.0000
  16.750   1.3323   0.09128   0.08486  -0.0235   0.0331   1.0000
  17.000   1.3169   0.09736   0.09111  -0.0256   0.0324   1.0000
  17.250   1.3033   0.10327   0.09716  -0.0278   0.0321   1.0000
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