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GOE 182 (MVA H.27) AIRFOIL (goe182-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 182 (MVA H.27) AIRFOIL (goe182-il)
Reynolds number: 500,000
Max Cl/Cd: 97.95 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe182-il-500000-n5.txt
Download as CSV file: xf-goe182-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3287   0.08861   0.08643  -0.0220   1.0000   0.0151
  -8.250  -0.3276   0.08488   0.08273  -0.0238   1.0000   0.0158
  -8.000  -0.3291   0.07785   0.07573  -0.0304   0.9879   0.0171
  -7.750  -0.3068   0.07507   0.07294  -0.0350   0.9766   0.0175
  -7.500  -0.2849   0.07178   0.06963  -0.0401   0.9619   0.0179
  -7.250  -0.2662   0.06779   0.06560  -0.0455   0.9406   0.0186
  -6.750  -0.2095   0.02013   0.01609  -0.1023   0.9014   0.0256
  -6.500  -0.1864   0.01799   0.01349  -0.1023   0.8564   0.0263
  -6.250  -0.1635   0.01756   0.01270  -0.1012   0.7924   0.0267
  -6.000  -0.1385   0.01725   0.01209  -0.1007   0.7496   0.0272
  -5.750  -0.1123   0.01669   0.01124  -0.1005   0.7220   0.0278
  -5.500  -0.0856   0.01591   0.01019  -0.1004   0.7012   0.0283
  -5.250  -0.0584   0.01516   0.00919  -0.1004   0.6833   0.0288
  -5.000  -0.0310   0.01447   0.00827  -0.1003   0.6680   0.0294
  -4.750  -0.0034   0.01396   0.00756  -0.1002   0.6523   0.0301
  -4.500   0.0243   0.01349   0.00690  -0.1001   0.6356   0.0307
  -4.250   0.0520   0.01303   0.00625  -0.0999   0.6178   0.0310
  -4.000   0.0796   0.01266   0.00569  -0.0997   0.5981   0.0314
  -3.750   0.1072   0.01224   0.00510  -0.0996   0.5773   0.0317
  -3.500   0.1347   0.01178   0.00448  -0.0994   0.5576   0.0324
  -3.250   0.1623   0.01152   0.00409  -0.0992   0.5395   0.0330
  -3.000   0.1901   0.01134   0.00380  -0.0991   0.5231   0.0337
  -2.750   0.2179   0.01120   0.00356  -0.0989   0.5072   0.0344
  -2.500   0.2458   0.01109   0.00335  -0.0987   0.4914   0.0355
  -2.250   0.2736   0.01098   0.00314  -0.0986   0.4749   0.0364
  -2.000   0.3015   0.01088   0.00293  -0.0984   0.4579   0.0373
  -1.750   0.3294   0.01080   0.00274  -0.0982   0.4404   0.0381
  -1.500   0.3572   0.01074   0.00258  -0.0981   0.4221   0.0389
  -1.250   0.3850   0.01067   0.00242  -0.0979   0.4028   0.0408
  -1.000   0.4127   0.01068   0.00234  -0.0978   0.3834   0.0429
  -0.750   0.4404   0.01071   0.00228  -0.0976   0.3656   0.0455
  -0.500   0.4681   0.01074   0.00223  -0.0974   0.3500   0.0494
  -0.250   0.4958   0.01079   0.00223  -0.0973   0.3365   0.0555
   0.000   0.5235   0.01082   0.00223  -0.0971   0.3253   0.0624
   0.250   0.5512   0.01090   0.00223  -0.0970   0.3154   0.0685
   0.500   0.5789   0.01092   0.00223  -0.0968   0.3064   0.0762
   0.750   0.6066   0.01097   0.00225  -0.0967   0.2990   0.0846
   1.000   0.6343   0.01093   0.00232  -0.0966   0.2918   0.1235
   1.250   0.6618   0.01098   0.00240  -0.0964   0.2855   0.1579
   1.500   0.6895   0.01099   0.00248  -0.0963   0.2801   0.1887
   1.750   0.7170   0.01102   0.00258  -0.0962   0.2747   0.2250
   2.000   0.7443   0.01105   0.00269  -0.0961   0.2699   0.2770
   2.250   0.7719   0.01103   0.00281  -0.0960   0.2662   0.3346
   2.500   0.7991   0.01096   0.00298  -0.0959   0.2624   0.4437
   2.750   0.8260   0.01092   0.00312  -0.0957   0.2588   0.5344
   3.250   0.8800   0.01033   0.00336  -0.0952   0.2516   1.0000
   3.500   0.9073   0.01048   0.00348  -0.0950   0.2482   1.0000
   3.750   0.9345   0.01065   0.00362  -0.0948   0.2451   1.0000
   4.000   0.9615   0.01084   0.00377  -0.0946   0.2423   1.0000
   4.250   0.9883   0.01104   0.00394  -0.0943   0.2397   1.0000
   4.500   1.0150   0.01124   0.00413  -0.0941   0.2374   1.0000
   4.750   1.0421   0.01140   0.00429  -0.0939   0.2361   1.0000
   5.000   1.0690   0.01157   0.00448  -0.0936   0.2347   1.0000
   5.250   1.0957   0.01175   0.00467  -0.0934   0.2334   1.0000
   5.500   1.1224   0.01194   0.00488  -0.0932   0.2321   1.0000
   5.750   1.1489   0.01213   0.00508  -0.0929   0.2302   1.0000
   6.000   1.1752   0.01235   0.00529  -0.0926   0.2267   1.0000
   6.250   1.2011   0.01259   0.00553  -0.0923   0.2237   1.0000
   6.500   1.2270   0.01285   0.00579  -0.0920   0.2218   1.0000
   6.750   1.2533   0.01304   0.00603  -0.0917   0.2202   1.0000
   7.000   1.2796   0.01322   0.00627  -0.0915   0.2184   1.0000
   7.250   1.3056   0.01343   0.00652  -0.0912   0.2168   1.0000
   7.500   1.3314   0.01364   0.00678  -0.0909   0.2138   1.0000
   7.750   1.3567   0.01390   0.00704  -0.0905   0.2091   1.0000
   8.000   1.3821   0.01415   0.00730  -0.0902   0.2034   1.0000
   8.250   1.4075   0.01437   0.00755  -0.0898   0.1966   1.0000
   8.500   1.4322   0.01467   0.00786  -0.0894   0.1889   1.0000
   9.000   1.4680   0.01677   0.00945  -0.0872   0.1021   1.0000
   9.250   1.4828   0.01811   0.01059  -0.0856   0.0621   1.0000
   9.500   1.5006   0.01905   0.01149  -0.0844   0.0490   1.0000
   9.750   1.5203   0.01973   0.01221  -0.0834   0.0424   1.0000
  10.000   1.5386   0.02051   0.01302  -0.0822   0.0362   1.0000
  10.250   1.5562   0.02130   0.01381  -0.0810   0.0301   1.0000
  10.500   1.5727   0.02212   0.01464  -0.0796   0.0245   1.0000
  10.750   1.5877   0.02300   0.01555  -0.0781   0.0200   1.0000
  11.000   1.6014   0.02391   0.01650  -0.0764   0.0173   1.0000
  11.250   1.6112   0.02487   0.01751  -0.0742   0.0155   1.0000
  11.500   1.6195   0.02593   0.01864  -0.0718   0.0143   1.0000
  11.750   1.6276   0.02704   0.01984  -0.0697   0.0134   1.0000
  12.000   1.6337   0.02835   0.02124  -0.0676   0.0127   1.0000
  12.250   1.6377   0.02992   0.02290  -0.0657   0.0121   1.0000
  12.500   1.6391   0.03187   0.02497  -0.0641   0.0115   1.0000
  12.750   1.6389   0.03421   0.02742  -0.0629   0.0111   1.0000
  13.000   1.6403   0.03664   0.02997  -0.0623   0.0107   1.0000
  13.250   1.6395   0.03956   0.03303  -0.0622   0.0104   1.0000
  13.500   1.6364   0.04296   0.03656  -0.0624   0.0101   1.0000
  13.750   1.6306   0.04686   0.04059  -0.0630   0.0098   1.0000
  14.000   1.6217   0.05133   0.04520  -0.0638   0.0096   1.0000
  14.250   1.6099   0.05641   0.05042  -0.0651   0.0094   1.0000
  14.500   1.5949   0.06203   0.05619  -0.0665   0.0093   1.0000
  14.750   1.5773   0.06815   0.06246  -0.0682   0.0092   1.0000
  15.000   1.5577   0.07459   0.06904  -0.0699   0.0091   1.0000
  15.250   1.5375   0.08125   0.07583  -0.0718   0.0091   1.0000
  15.500   1.5179   0.08793   0.08265  -0.0737   0.0090   1.0000
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