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GOE 233 (MVA CA4) AIRFOIL (goe233-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 233 (MVA CA4) AIRFOIL (goe233-il)
Reynolds number: 1,000,000
Max Cl/Cd: 146.85 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe233-il-1000000.txt
Download as CSV file: xf-goe233-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 233 (MVA CA4) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.1488   0.09639   0.09444  -0.0690   0.9033   0.0217
  -9.500  -0.1398   0.09381   0.09182  -0.0702   0.8933   0.0222
  -8.750  -0.2095   0.03174   0.02886  -0.1492   0.8526   0.0227
  -8.500  -0.1494   0.02526   0.02198  -0.1695   0.8462   0.0233
  -8.250  -0.0961   0.02166   0.01801  -0.1821   0.8403   0.0240
  -8.000  -0.0525   0.02011   0.01617  -0.1887   0.8346   0.0244
  -7.750  -0.0163   0.01722   0.01301  -0.1934   0.8288   0.0250
  -7.500   0.0147   0.01610   0.01180  -0.1949   0.8229   0.0254
  -7.250   0.0463   0.01529   0.01093  -0.1964   0.8170   0.0258
  -7.000   0.0771   0.01468   0.01028  -0.1974   0.8105   0.0264
  -6.750   0.1084   0.01409   0.00959  -0.1986   0.8043   0.0270
  -6.500   0.1402   0.01344   0.00886  -0.1997   0.7981   0.0273
  -6.250   0.1714   0.01288   0.00819  -0.2007   0.7915   0.0276
  -6.000   0.2026   0.01238   0.00762  -0.2015   0.7846   0.0280
  -5.750   0.2336   0.01195   0.00710  -0.2023   0.7761   0.0283
  -5.500   0.2644   0.01158   0.00664  -0.2030   0.7676   0.0286
  -5.250   0.2950   0.01132   0.00629  -0.2035   0.7584   0.0289
  -5.000   0.3266   0.01078   0.00569  -0.2045   0.7507   0.0295
  -4.750   0.3584   0.01030   0.00515  -0.2055   0.7424   0.0300
  -4.500   0.3899   0.00993   0.00472  -0.2063   0.7346   0.0304
  -4.250   0.4211   0.00961   0.00433  -0.2071   0.7260   0.0308
  -4.000   0.4520   0.00934   0.00398  -0.2078   0.7177   0.0313
  -3.750   0.4828   0.00911   0.00367  -0.2083   0.7088   0.0318
  -3.500   0.5133   0.00890   0.00339  -0.2088   0.7009   0.0324
  -3.250   0.5437   0.00873   0.00314  -0.2093   0.6929   0.0330
  -3.000   0.5737   0.00860   0.00293  -0.2096   0.6856   0.0339
  -2.750   0.6037   0.00848   0.00276  -0.2099   0.6781   0.0344
  -2.500   0.6336   0.00837   0.00256  -0.2102   0.6704   0.0356
  -2.250   0.6634   0.00828   0.00242  -0.2105   0.6625   0.0372
  -2.000   0.6928   0.00824   0.00230  -0.2107   0.6547   0.0393
  -1.750   0.7230   0.00807   0.00219  -0.2111   0.6484   0.0633
  -1.500   0.7526   0.00798   0.00210  -0.2113   0.6422   0.0865
  -1.250   0.7829   0.00773   0.00199  -0.2119   0.6365   0.1502
  -1.000   0.8126   0.00759   0.00192  -0.2123   0.6306   0.1865
  -0.750   0.8419   0.00748   0.00192  -0.2126   0.6246   0.2483
  -0.500   0.8708   0.00750   0.00198  -0.2126   0.6192   0.2698
  -0.250   0.8995   0.00756   0.00202  -0.2126   0.6131   0.2806
   0.000   0.9279   0.00765   0.00210  -0.2125   0.6074   0.2888
   0.250   0.9566   0.00772   0.00216  -0.2125   0.6027   0.2960
   0.500   0.9852   0.00778   0.00225  -0.2124   0.5976   0.3028
   0.750   1.0135   0.00790   0.00234  -0.2123   0.5922   0.3091
   1.000   1.0417   0.00801   0.00242  -0.2122   0.5865   0.3128
   1.250   1.0702   0.00807   0.00251  -0.2122   0.5798   0.3179
   1.500   1.0980   0.00820   0.00261  -0.2120   0.5726   0.3212
   1.750   1.1264   0.00827   0.00269  -0.2120   0.5667   0.3243
   2.000   1.1545   0.00837   0.00277  -0.2119   0.5600   0.3270
   2.250   1.1824   0.00849   0.00286  -0.2117   0.5531   0.3286
   2.500   1.2106   0.00853   0.00291  -0.2117   0.5453   0.3319
   2.750   1.2381   0.00866   0.00304  -0.2115   0.5374   0.3349
   3.000   1.2658   0.00878   0.00316  -0.2114   0.5279   0.3380
   3.250   1.2932   0.00891   0.00327  -0.2112   0.5182   0.3402
   3.500   1.3203   0.00907   0.00339  -0.2109   0.5071   0.3424
   3.750   1.3475   0.00921   0.00351  -0.2107   0.4961   0.3443
   4.000   1.3744   0.00936   0.00364  -0.2105   0.4848   0.3468
   4.250   1.4009   0.00954   0.00380  -0.2102   0.4735   0.3494
   4.500   1.4273   0.00973   0.00397  -0.2099   0.4606   0.3514
   4.750   1.4531   0.00998   0.00417  -0.2094   0.4452   0.3532
   5.000   1.4791   0.01019   0.00436  -0.2090   0.4330   0.3552
   5.250   1.5045   0.01045   0.00457  -0.2086   0.4192   0.3572
   5.500   1.5294   0.01075   0.00482  -0.2080   0.4030   0.3593
   5.750   1.5540   0.01107   0.00507  -0.2074   0.3857   0.3608
   6.000   1.5769   0.01151   0.00538  -0.2066   0.3581   0.3627
   6.250   1.5964   0.01222   0.00585  -0.2052   0.3111   0.3648
   6.500   1.6139   0.01309   0.00645  -0.2036   0.2663   0.3665
   6.750   1.6344   0.01366   0.00692  -0.2023   0.2452   0.3684
   7.000   1.6554   0.01415   0.00735  -0.2012   0.2305   0.3704
   7.250   1.6764   0.01462   0.00778  -0.2000   0.2193   0.3724
   7.500   1.6986   0.01497   0.00813  -0.1990   0.2114   0.3744
   7.750   1.7188   0.01544   0.00856  -0.1977   0.2022   0.3762
   8.000   1.7405   0.01576   0.00890  -0.1967   0.1946   0.3782
   8.250   1.7600   0.01621   0.00934  -0.1953   0.1847   0.3807
   8.500   1.7777   0.01673   0.00982  -0.1936   0.1712   0.3827
   8.750   1.7922   0.01739   0.01039  -0.1914   0.1503   0.3846
   9.000   1.7885   0.01872   0.01147  -0.1860   0.1125   0.3860
   9.250   1.7825   0.02050   0.01301  -0.1808   0.0770   0.3873
   9.500   1.7842   0.02194   0.01436  -0.1770   0.0587   0.3888
   9.750   1.7909   0.02315   0.01553  -0.1741   0.0484   0.3905
  10.000   1.7987   0.02433   0.01670  -0.1714   0.0424   0.3920
  10.250   1.8094   0.02536   0.01776  -0.1693   0.0392   0.3939
  10.500   1.8180   0.02658   0.01901  -0.1670   0.0362   0.3965
  10.750   1.8276   0.02777   0.02026  -0.1649   0.0340   0.3987
  11.000   1.8378   0.02895   0.02149  -0.1630   0.0323   0.4008
  11.250   1.8454   0.03037   0.02294  -0.1609   0.0306   0.4029
  11.500   1.8510   0.03200   0.02462  -0.1587   0.0286   0.4048
  11.750   1.8611   0.03328   0.02598  -0.1571   0.0277   0.4069
  12.000   1.8691   0.03479   0.02754  -0.1553   0.0265   0.4087
  12.250   1.8748   0.03653   0.02934  -0.1535   0.0253   0.4113
  12.500   1.8759   0.03875   0.03162  -0.1514   0.0238   0.4135
  12.750   1.8840   0.04034   0.03329  -0.1499   0.0231   0.4163
  13.000   1.8908   0.04208   0.03511  -0.1484   0.0222   0.4192
  13.250   1.8950   0.04411   0.03719  -0.1469   0.0213   0.4218
  13.500   1.8967   0.04646   0.03959  -0.1453   0.0203   0.4240
  13.750   1.8956   0.04922   0.04244  -0.1437   0.0194   0.4269
  14.000   1.9007   0.05135   0.04466  -0.1425   0.0189   0.4301
  14.250   1.9043   0.05369   0.04709  -0.1414   0.0183   0.4334
  14.500   1.9065   0.05622   0.04968  -0.1403   0.0177   0.4366
  14.750   1.9070   0.05901   0.05255  -0.1392   0.0171   0.4399
  15.000   1.9046   0.06222   0.05584  -0.1383   0.0165   0.4437
  15.250   1.8973   0.06611   0.05983  -0.1373   0.0159   0.4472
  15.500   1.8987   0.06894   0.06276  -0.1366   0.0156   0.4523
  15.750   1.8987   0.07200   0.06591  -0.1359   0.0152   0.4588
  16.000   1.8977   0.07520   0.06922  -0.1354   0.0148   0.4668
  16.250   1.8962   0.07853   0.07265  -0.1349   0.0144   0.4790
  16.750   1.8887   0.08563   0.08044  -0.1345   0.0137   1.0000
  17.000   1.8800   0.09006   0.08495  -0.1344   0.0133   1.0000
  17.250   1.8670   0.09523   0.09022  -0.1345   0.0129   1.0000
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