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GOE 801 (MVA 301) AIRFOIL (goe801-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 801 (MVA 301) AIRFOIL (goe801-il)
Reynolds number: 1,000,000
Max Cl/Cd: 122.98 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe801-il-1000000-n5.txt
Download as CSV file: xf-goe801-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 801 (MVA 301) AIRFOIL                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2407   0.10683   0.10483  -0.0406   0.8863   0.0110
  -9.750  -0.2343   0.10375   0.10170  -0.0419   0.8785   0.0113
  -9.500  -0.2361   0.09807   0.09600  -0.0446   0.8709   0.0121
  -9.250  -0.2268   0.09579   0.09367  -0.0457   0.8633   0.0122
  -9.000  -0.2168   0.09355   0.09143  -0.0469   0.8563   0.0124
  -8.750  -0.2070   0.09125   0.08910  -0.0482   0.8488   0.0125
  -8.500  -0.1972   0.08889   0.08672  -0.0496   0.8420   0.0127
  -8.250  -0.1880   0.08631   0.08411  -0.0511   0.8345   0.0130
  -8.000  -0.1798   0.08342   0.08120  -0.0530   0.8276   0.0133
  -7.750  -0.1719   0.08034   0.07811  -0.0551   0.8200   0.0136
  -7.500  -0.1697   0.07370   0.07141  -0.0622   0.8127   0.0146
  -7.250  -0.1535   0.07142   0.06912  -0.0648   0.8059   0.0147
  -7.000  -0.1362   0.06913   0.06679  -0.0676   0.7988   0.0149
  -6.750  -0.1176   0.06663   0.06427  -0.0710   0.7919   0.0151
  -6.500  -0.0977   0.06384   0.06144  -0.0748   0.7844   0.0153
  -6.250  -0.0763   0.06047   0.05803  -0.0795   0.7774   0.0156
  -6.000  -0.0530   0.05686   0.05436  -0.0845   0.7692   0.0159
  -5.750  -0.0277   0.05297   0.05039  -0.0899   0.7615   0.0162
  -5.500   0.0066   0.04513   0.04236  -0.1004   0.7527   0.0175
  -5.250   0.0319   0.04299   0.04012  -0.1027   0.7403   0.0176
  -5.000   0.0580   0.04080   0.03782  -0.1050   0.7260   0.0178
  -4.750   0.0856   0.03824   0.03513  -0.1076   0.7114   0.0180
  -4.500   0.1143   0.03534   0.03207  -0.1104   0.6987   0.0182
  -4.250   0.1440   0.03220   0.02875  -0.1130   0.6862   0.0185
  -4.000   0.1740   0.02890   0.02525  -0.1152   0.6735   0.0188
  -3.750   0.2048   0.02504   0.02110  -0.1172   0.6616   0.0194
  -3.500   0.2363   0.01923   0.01471  -0.1190   0.6504   0.0200
  -3.250   0.2652   0.01580   0.01075  -0.1196   0.6369   0.0203
  -3.000   0.2931   0.01426   0.00887  -0.1200   0.6220   0.0206
  -2.750   0.3211   0.01348   0.00789  -0.1201   0.6071   0.0208
  -2.500   0.3492   0.01294   0.00720  -0.1203   0.5941   0.0209
  -2.250   0.3774   0.01250   0.00662  -0.1204   0.5815   0.0211
  -2.000   0.4055   0.01210   0.00608  -0.1204   0.5684   0.0213
  -1.500   0.4619   0.01136   0.00508  -0.1205   0.5437   0.0219
  -1.250   0.4901   0.01102   0.00462  -0.1206   0.5340   0.0221
  -1.000   0.5184   0.01070   0.00420  -0.1206   0.5242   0.0224
  -0.750   0.5467   0.01042   0.00384  -0.1206   0.5155   0.0226
  -0.250   0.6030   0.00999   0.00326  -0.1207   0.4964   0.0231
   0.000   0.6311   0.00989   0.00310  -0.1207   0.4872   0.0234
   0.250   0.6593   0.00979   0.00295  -0.1207   0.4783   0.0237
   0.500   0.6873   0.00969   0.00281  -0.1207   0.4702   0.0239
   0.750   0.7155   0.00956   0.00264  -0.1207   0.4615   0.0241
   1.000   0.7435   0.00943   0.00249  -0.1208   0.4534   0.0246
   1.250   0.7715   0.00939   0.00243  -0.1208   0.4440   0.0250
   1.500   0.7994   0.00939   0.00240  -0.1208   0.4348   0.0254
   1.750   0.8270   0.00943   0.00240  -0.1208   0.4241   0.0259
   2.000   0.8545   0.00948   0.00240  -0.1208   0.4105   0.0264
   2.250   0.8815   0.00959   0.00243  -0.1206   0.3941   0.0269
   2.500   0.9086   0.00969   0.00248  -0.1205   0.3794   0.0274
   2.750   0.9359   0.00979   0.00254  -0.1205   0.3688   0.0281
   3.000   0.9631   0.00987   0.00258  -0.1204   0.3593   0.0292
   3.250   0.9903   0.00997   0.00265  -0.1203   0.3491   0.0301
   3.500   1.0173   0.01009   0.00274  -0.1202   0.3399   0.0312
   3.750   1.0440   0.01024   0.00285  -0.1201   0.3303   0.0325
   4.000   1.0708   0.01038   0.00296  -0.1199   0.3200   0.0344
   4.250   1.0971   0.01055   0.00310  -0.1197   0.3083   0.0458
   5.250   1.1987   0.00977   0.00396  -0.1187   0.2786   1.0000
   5.500   1.2249   0.00996   0.00413  -0.1185   0.2706   1.0000
   5.750   1.2508   0.01019   0.00431  -0.1182   0.2626   1.0000
   6.000   1.2761   0.01045   0.00451  -0.1179   0.2518   1.0000
   6.250   1.3009   0.01074   0.00474  -0.1175   0.2381   1.0000
   6.500   1.3244   0.01114   0.00503  -0.1169   0.2187   1.0000
   6.750   1.3449   0.01178   0.00547  -0.1159   0.1862   1.0000
   7.000   1.3650   0.01243   0.00595  -0.1148   0.1599   1.0000
   7.250   1.3867   0.01292   0.00634  -0.1140   0.1442   1.0000
   7.500   1.4090   0.01333   0.00670  -0.1132   0.1344   1.0000
   7.750   1.4316   0.01371   0.00703  -0.1125   0.1258   1.0000
   8.000   1.4535   0.01411   0.00740  -0.1117   0.1172   1.0000
   8.250   1.4745   0.01456   0.00779  -0.1108   0.1084   1.0000
   8.500   1.4948   0.01503   0.00821  -0.1097   0.0979   1.0000
   8.750   1.5120   0.01568   0.00876  -0.1082   0.0819   1.0000
   9.000   1.5261   0.01647   0.00943  -0.1062   0.0647   1.0000
   9.250   1.5422   0.01700   0.00994  -0.1044   0.0589   1.0000
   9.500   1.5568   0.01757   0.01050  -0.1024   0.0543   1.0000
   9.750   1.5725   0.01811   0.01104  -0.1007   0.0503   1.0000
  10.000   1.5857   0.01881   0.01173  -0.0986   0.0450   1.0000
  10.250   1.5997   0.01949   0.01242  -0.0968   0.0397   1.0000
  10.500   1.5998   0.02109   0.01387  -0.0932   0.0178   1.0000
  10.750   1.6103   0.02206   0.01488  -0.0912   0.0144   1.0000
  11.000   1.6222   0.02298   0.01585  -0.0894   0.0130   1.0000
  11.250   1.6349   0.02387   0.01678  -0.0879   0.0121   1.0000
  11.500   1.6471   0.02481   0.01778  -0.0863   0.0114   1.0000
  11.750   1.6581   0.02588   0.01890  -0.0847   0.0107   1.0000
  12.000   1.6676   0.02708   0.02015  -0.0831   0.0101   1.0000
  12.250   1.6774   0.02831   0.02143  -0.0816   0.0096   1.0000
  12.500   1.6874   0.02954   0.02273  -0.0802   0.0093   1.0000
  12.750   1.6965   0.03089   0.02414  -0.0789   0.0090   1.0000
  13.000   1.7043   0.03236   0.02567  -0.0775   0.0086   1.0000
  13.250   1.7113   0.03397   0.02735  -0.0762   0.0083   1.0000
  13.500   1.7170   0.03574   0.02918  -0.0750   0.0080   1.0000
  13.750   1.7211   0.03769   0.03120  -0.0737   0.0077   1.0000
  14.000   1.7231   0.03992   0.03350  -0.0725   0.0074   1.0000
  14.250   1.7276   0.04196   0.03562  -0.0716   0.0073   1.0000
  14.500   1.7310   0.04418   0.03792  -0.0708   0.0071   1.0000
  14.750   1.7335   0.04656   0.04038  -0.0700   0.0069   1.0000
  15.000   1.7350   0.04915   0.04304  -0.0694   0.0067   1.0000
  15.250   1.7356   0.05192   0.04590  -0.0690   0.0066   1.0000
  15.500   1.7351   0.05490   0.04897  -0.0686   0.0064   1.0000
  15.750   1.7335   0.05808   0.05224  -0.0684   0.0063   1.0000
  16.000   1.7308   0.06148   0.05572  -0.0683   0.0061   1.0000
  16.250   1.7269   0.06512   0.05945  -0.0684   0.0060   1.0000
  16.500   1.7217   0.06900   0.06342  -0.0687   0.0059   1.0000
  16.750   1.7150   0.07312   0.06764  -0.0690   0.0058   1.0000
  17.000   1.7068   0.07752   0.07215  -0.0695   0.0056   1.0000
  17.250   1.6971   0.08223   0.07696  -0.0702   0.0055   1.0000
  17.500   1.6863   0.08716   0.08201  -0.0710   0.0055   1.0000
  17.750   1.6774   0.09184   0.08679  -0.0719   0.0054   1.0000
  18.000   1.6681   0.09666   0.09171  -0.0729   0.0054   1.0000
  18.250   1.6581   0.10163   0.09679  -0.0741   0.0053   1.0000
  18.500   1.6480   0.10669   0.10196  -0.0754   0.0053   1.0000
  18.750   1.6368   0.11194   0.10732  -0.0769   0.0052   1.0000
  19.000   1.6259   0.11724   0.11272  -0.0785   0.0052   1.0000
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