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GOE 182 (MVA H.27) AIRFOIL (goe182-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 182 (MVA H.27) AIRFOIL (goe182-il)
Reynolds number: 500,000
Max Cl/Cd: 97.98 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe182-il-500000.txt
Download as CSV file: xf-goe182-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 182 (MVA H.27) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3162   0.09266   0.09051  -0.0221   1.0000   0.0286
  -8.000  -0.3177   0.08905   0.08695  -0.0250   1.0000   0.0288
  -7.750  -0.3195   0.08495   0.08289  -0.0264   1.0000   0.0290
  -7.500  -0.3130   0.08289   0.08086  -0.0244   1.0000   0.0294
  -7.250  -0.3069   0.08119   0.07918  -0.0229   1.0000   0.0298
  -7.000  -0.3006   0.07914   0.07717  -0.0230   0.9993   0.0303
  -6.750  -0.2654   0.07469   0.07269  -0.0315   0.9933   0.0316
  -6.500  -0.2097   0.06427   0.06216  -0.0567   0.9829   0.0346
  -6.250  -0.1901   0.05989   0.05777  -0.0595   0.9711   0.0354
  -6.000  -0.1657   0.05797   0.05583  -0.0611   0.9556   0.0362
  -5.750  -0.1429   0.05528   0.05309  -0.0640   0.9339   0.0375
  -5.500  -0.0914   0.04200   0.03944  -0.0849   0.9092   0.0422
  -5.250  -0.0740   0.04077   0.03811  -0.0840   0.8689   0.0427
  -5.000  -0.0549   0.03984   0.03697  -0.0832   0.8216   0.0435
  -4.750  -0.0315   0.03822   0.03512  -0.0841   0.7861   0.0450
  -4.500   0.0108   0.02774   0.02378  -0.0941   0.7676   0.0511
  -4.250   0.0353   0.02651   0.02246  -0.0942   0.7473   0.0519
  -4.000   0.0610   0.02534   0.02113  -0.0945   0.7302   0.0531
  -3.750   0.0881   0.02399   0.01959  -0.0950   0.7148   0.0555
  -3.500   0.1222   0.01495   0.00888  -0.0968   0.7046   0.0413
  -3.250   0.1496   0.01361   0.00724  -0.0968   0.6901   0.0423
  -3.000   0.1772   0.01274   0.00621  -0.0966   0.6751   0.0430
  -2.750   0.2049   0.01221   0.00557  -0.0964   0.6590   0.0438
  -2.500   0.2326   0.01181   0.00505  -0.0962   0.6415   0.0447
  -2.250   0.2603   0.01147   0.00458  -0.0959   0.6220   0.0457
  -2.000   0.2880   0.01117   0.00417  -0.0956   0.6004   0.0469
  -1.750   0.3156   0.01101   0.00386  -0.0953   0.5780   0.0486
  -1.500   0.3432   0.01091   0.00362  -0.0950   0.5570   0.0498
  -1.250   0.3706   0.01045   0.00307  -0.0948   0.5378   0.0521
  -1.000   0.3983   0.01035   0.00288  -0.0946   0.5193   0.0546
  -0.750   0.4260   0.01029   0.00274  -0.0943   0.5014   0.0577
  -0.500   0.4536   0.01018   0.00253  -0.0941   0.4833   0.0620
  -0.250   0.4813   0.01012   0.00241  -0.0939   0.4645   0.0693
   0.000   0.5090   0.01001   0.00224  -0.0937   0.4438   0.0800
   0.250   0.5365   0.00998   0.00214  -0.0936   0.4211   0.0957
   0.500   0.5637   0.00995   0.00219  -0.0934   0.3982   0.1520
   0.750   0.5909   0.01001   0.00225  -0.0932   0.3761   0.1944
   1.000   0.6179   0.01007   0.00234  -0.0931   0.3574   0.2457
   1.250   0.6449   0.01006   0.00246  -0.0929   0.3421   0.3255
   1.500   0.6713   0.00986   0.00265  -0.0928   0.3298   0.5068
   1.750   0.6989   0.00899   0.00275  -0.0926   0.3197   1.0000
   2.000   0.7260   0.00922   0.00285  -0.0923   0.3108   1.0000
   2.250   0.7535   0.00939   0.00296  -0.0921   0.3038   1.0000
   2.500   0.7806   0.00960   0.00308  -0.0919   0.2975   1.0000
   2.750   0.8077   0.00983   0.00323  -0.0916   0.2922   1.0000
   3.000   0.8351   0.00999   0.00336  -0.0914   0.2878   1.0000
   3.250   0.8622   0.01020   0.00351  -0.0912   0.2837   1.0000
   3.500   0.8889   0.01046   0.00370  -0.0909   0.2797   1.0000
   3.750   0.9159   0.01066   0.00387  -0.0906   0.2764   1.0000
   4.000   0.9432   0.01081   0.00402  -0.0904   0.2732   1.0000
   4.250   0.9702   0.01100   0.00419  -0.0902   0.2698   1.0000
   4.500   0.9968   0.01123   0.00438  -0.0899   0.2667   1.0000
   4.750   1.0230   0.01154   0.00464  -0.0896   0.2640   1.0000
   5.000   1.0496   0.01178   0.00489  -0.0893   0.2623   1.0000
   5.250   1.0765   0.01197   0.00511  -0.0891   0.2609   1.0000
   5.500   1.1031   0.01219   0.00535  -0.0888   0.2594   1.0000
   5.750   1.1298   0.01239   0.00557  -0.0885   0.2575   1.0000
   6.000   1.1563   0.01259   0.00579  -0.0883   0.2551   1.0000
   6.250   1.1825   0.01282   0.00603  -0.0880   0.2530   1.0000
   6.500   1.2083   0.01311   0.00630  -0.0877   0.2505   1.0000
   6.750   1.2337   0.01349   0.00668  -0.0873   0.2478   1.0000
   7.000   1.2602   0.01364   0.00690  -0.0870   0.2462   1.0000
   7.250   1.2867   0.01376   0.00709  -0.0868   0.2432   1.0000
   7.500   1.3129   0.01389   0.00725  -0.0865   0.2390   1.0000
   7.750   1.3377   0.01420   0.00753  -0.0861   0.2341   1.0000
   8.000   1.3637   0.01435   0.00776  -0.0858   0.2309   1.0000
   8.250   1.3899   0.01447   0.00796  -0.0856   0.2270   1.0000
   8.500   1.4152   0.01467   0.00817  -0.0853   0.2215   1.0000
   8.750   1.4405   0.01488   0.00843  -0.0849   0.2161   1.0000
   9.000   1.4661   0.01502   0.00863  -0.0846   0.2085   1.0000
   9.250   1.4913   0.01522   0.00885  -0.0843   0.1972   1.0000
   9.500   1.5129   0.01580   0.00920  -0.0836   0.1476   1.0000
   9.750   1.5149   0.01857   0.01136  -0.0807   0.0635   1.0000
  10.000   1.5281   0.01996   0.01269  -0.0789   0.0454   1.0000
  10.250   1.5430   0.02109   0.01385  -0.0773   0.0368   1.0000
  10.500   1.5563   0.02226   0.01505  -0.0755   0.0310   1.0000
  10.750   1.5715   0.02316   0.01600  -0.0740   0.0276   1.0000
  11.000   1.5811   0.02443   0.01733  -0.0718   0.0250   1.0000
  11.250   1.5913   0.02538   0.01837  -0.0696   0.0235   1.0000
  11.500   1.5982   0.02654   0.01960  -0.0672   0.0223   1.0000
  11.750   1.5993   0.02816   0.02130  -0.0645   0.0212   1.0000
  12.000   1.5946   0.03040   0.02368  -0.0619   0.0203   1.0000
  12.250   1.5981   0.03222   0.02561  -0.0604   0.0197   1.0000
  12.500   1.5989   0.03451   0.02803  -0.0594   0.0191   1.0000
  12.750   1.5977   0.03732   0.03096  -0.0590   0.0185   1.0000
  13.000   1.5944   0.04070   0.03446  -0.0592   0.0180   1.0000
  13.250   1.5881   0.04467   0.03856  -0.0598   0.0176   1.0000
  13.500   1.5775   0.04941   0.04343  -0.0609   0.0172   1.0000
  13.750   1.5628   0.05493   0.04908  -0.0623   0.0170   1.0000
  14.000   1.5455   0.06094   0.05524  -0.0640   0.0169   1.0000
  14.250   1.5267   0.06719   0.06162  -0.0657   0.0167   1.0000
  14.500   1.5070   0.07358   0.06813  -0.0674   0.0166   1.0000
  14.750   1.4877   0.07988   0.07455  -0.0690   0.0165   1.0000
  15.000   1.4697   0.08607   0.08085  -0.0706   0.0163   1.0000
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