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GOE 234 (MVA CA5) AIRFOIL (goe234-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 234 (MVA CA5) AIRFOIL (goe234-il)
Reynolds number: 100,000
Max Cl/Cd: 56.61 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe234-il-100000-n5.txt
Download as CSV file: xf-goe234-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 234 (MVA CA5) AIRFOIL                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.0342   0.09908   0.09372  -0.1013   0.9297   0.0546
  -9.250  -0.0213   0.09508   0.08967  -0.1045   0.9257   0.0539
  -9.000  -0.0251   0.09102   0.08562  -0.1065   0.9157   0.0543
  -8.750   0.0027   0.09099   0.08558  -0.1057   0.9121   0.0568
  -8.500   0.0082   0.08791   0.08250  -0.1071   0.9048   0.0570
  -8.250   0.0094   0.08368   0.07826  -0.1095   0.8972   0.0562
  -8.000  -0.0187   0.07510   0.06969  -0.1141   0.8856   0.0544
  -7.750   0.0001   0.07413   0.06870  -0.1143   0.8806   0.0552
  -7.500   0.0137   0.07193   0.06649  -0.1159   0.8753   0.0563
  -7.000   0.0461   0.04005   0.03361  -0.1746   0.8563   0.0571
  -6.750   0.1014   0.03557   0.02869  -0.1883   0.8517   0.0586
  -6.500   0.1573   0.03235   0.02501  -0.1992   0.8484   0.0613
  -6.250   0.2070   0.03015   0.02239  -0.2065   0.8455   0.0631
  -6.000   0.2295   0.02968   0.02198  -0.2048   0.8401   0.0643
  -5.750   0.2531   0.02939   0.02171  -0.2035   0.8337   0.0657
  -5.500   0.2819   0.02900   0.02128  -0.2031   0.8294   0.0677
  -5.250   0.3148   0.02851   0.02067  -0.2037   0.8262   0.0708
  -5.000   0.3395   0.02841   0.02051  -0.2032   0.8183   0.0731
  -4.750   0.3619   0.02864   0.02083  -0.2008   0.8129   0.0754
  -4.500   0.3939   0.02843   0.02060  -0.2012   0.8091   0.0785
  -4.250   0.4239   0.02823   0.02036  -0.2021   0.8024   0.0827
  -4.000   0.4601   0.02772   0.01990  -0.2048   0.7964   0.0893
  -3.750   0.5057   0.02671   0.01893  -0.2099   0.7921   0.0998
  -3.500   0.5551   0.02555   0.01810  -0.2165   0.7880   0.1553
  -3.250   0.5629   0.02721   0.02015  -0.2103   0.7794   0.1888
  -3.000   0.5977   0.02726   0.02005  -0.2119   0.7743   0.2312
  -2.750   0.6390   0.02689   0.01942  -0.2155   0.7699   0.2563
  -2.500   0.6679   0.02708   0.01950  -0.2164   0.7618   0.2698
  -2.000   0.7227   0.02774   0.01999  -0.2151   0.7516   0.2873
  -1.750   0.7538   0.02775   0.01989  -0.2167   0.7436   0.2993
  -1.500   0.7735   0.02830   0.02047  -0.2138   0.7381   0.3035
  -1.250   0.8094   0.02810   0.02011  -0.2160   0.7331   0.3152
  -1.000   0.8303   0.02834   0.02038  -0.2145   0.7254   0.3179
  -0.750   0.8611   0.02808   0.02004  -0.2152   0.7202   0.3215
  -0.500   0.9026   0.02750   0.01924  -0.2192   0.7147   0.3303
  -0.250   0.9253   0.02761   0.01938  -0.2182   0.7075   0.3323
   0.000   0.9533   0.02752   0.01925  -0.2179   0.7024   0.3359
   0.250   0.9830   0.02747   0.01914  -0.2187   0.6961   0.3425
   0.500   1.0140   0.02731   0.01892  -0.2198   0.6894   0.3477
   0.750   1.0442   0.02707   0.01862  -0.2202   0.6843   0.3501
   1.000   1.0700   0.02706   0.01861  -0.2201   0.6759   0.3529
   1.250   1.1033   0.02662   0.01804  -0.2212   0.6677   0.3555
   1.500   1.1321   0.02639   0.01773  -0.2218   0.6559   0.3578
   1.750   1.1671   0.02596   0.01710  -0.2236   0.6454   0.3617
   2.000   1.1928   0.02587   0.01700  -0.2231   0.6353   0.3632
   2.250   1.2200   0.02584   0.01695  -0.2230   0.6276   0.3648
   2.500   1.2469   0.02585   0.01695  -0.2231   0.6198   0.3662
   2.750   1.2774   0.02573   0.01676  -0.2236   0.6135   0.3678
   3.000   1.3020   0.02587   0.01693  -0.2234   0.6047   0.3695
   3.250   1.3319   0.02580   0.01678  -0.2239   0.5975   0.3716
   3.500   1.3570   0.02595   0.01695  -0.2237   0.5886   0.3744
   3.750   1.3862   0.02595   0.01685  -0.2242   0.5806   0.3775
   4.000   1.4090   0.02615   0.01712  -0.2234   0.5719   0.3788
   4.250   1.4341   0.02626   0.01725  -0.2229   0.5636   0.3801
   4.500   1.4572   0.02648   0.01751  -0.2222   0.5548   0.3816
   4.750   1.4812   0.02665   0.01769  -0.2216   0.5459   0.3833
   5.000   1.5032   0.02692   0.01799  -0.2208   0.5365   0.3852
   5.250   1.5267   0.02712   0.01818  -0.2201   0.5271   0.3876
   5.500   1.5466   0.02747   0.01858  -0.2189   0.5166   0.3904
   5.750   1.5691   0.02772   0.01878  -0.2180   0.5066   0.3931
   6.000   1.5853   0.02814   0.01931  -0.2161   0.4950   0.3947
   6.250   1.6018   0.02857   0.01979  -0.2142   0.4834   0.3964
   6.500   1.6185   0.02899   0.02020  -0.2124   0.4717   0.3981
   6.750   1.6309   0.02955   0.02080  -0.2099   0.4590   0.3998
   7.000   1.6398   0.03018   0.02148  -0.2068   0.4466   0.4016
   7.250   1.6512   0.03086   0.02214  -0.2042   0.4345   0.4036
   7.500   1.6638   0.03160   0.02285  -0.2020   0.4224   0.4061
   7.750   1.6750   0.03249   0.02376  -0.1997   0.4099   0.4086
   8.000   1.6862   0.03339   0.02470  -0.1974   0.3986   0.4104
   8.500   1.7063   0.03543   0.02675  -0.1927   0.3763   0.4146
   8.750   1.7157   0.03656   0.02787  -0.1904   0.3658   0.4167
   9.000   1.7249   0.03774   0.02901  -0.1882   0.3558   0.4188
   9.250   1.7339   0.03900   0.03031  -0.1860   0.3464   0.4209
   9.500   1.7436   0.04023   0.03148  -0.1840   0.3381   0.4230
   9.750   1.7524   0.04156   0.03292  -0.1820   0.3301   0.4249
  10.000   1.7618   0.04284   0.03422  -0.1800   0.3231   0.4271
  10.250   1.7705   0.04422   0.03567  -0.1781   0.3162   0.4297
  10.500   1.7780   0.04571   0.03724  -0.1761   0.3091   0.4323
  10.750   1.7870   0.04708   0.03859  -0.1742   0.3029   0.4352
  11.000   1.7935   0.04875   0.04041  -0.1724   0.2965   0.4377
  11.250   1.8012   0.05029   0.04201  -0.1706   0.2908   0.4399
  11.500   1.8092   0.05180   0.04356  -0.1689   0.2853   0.4418
  11.750   1.8128   0.05376   0.04572  -0.1670   0.2791   0.4437
  12.000   1.8161   0.05569   0.04769  -0.1651   0.2724   0.4457
  12.250   1.8177   0.05787   0.04999  -0.1633   0.2657   0.4481
  12.500   1.8176   0.06029   0.05255  -0.1616   0.2586   0.4507
  12.750   1.8206   0.06236   0.05460  -0.1599   0.2525   0.4537
  13.000   1.8188   0.06520   0.05769  -0.1585   0.2458   0.4559
  13.250   1.8176   0.06793   0.06056  -0.1571   0.2390   0.4581
  13.500   1.8156   0.07083   0.06357  -0.1558   0.2320   0.4605
  13.750   1.8095   0.07440   0.06731  -0.1547   0.2234   0.4626
  14.000   1.8042   0.07791   0.07092  -0.1537   0.2154   0.4648
  14.250   1.7972   0.08188   0.07507  -0.1531   0.2066   0.4668
  14.500   1.7883   0.08621   0.07954  -0.1526   0.1964   0.4687
  14.750   1.7771   0.09101   0.08446  -0.1524   0.1841   0.4703
  15.000   1.7658   0.09599   0.08962  -0.1525   0.1675   0.4717
  15.250   1.7490   0.10179   0.09542  -0.1529   0.1420   0.4728
  15.500   1.7250   0.10878   0.10227  -0.1538   0.1226   0.4734
  15.750   1.7013   0.11600   0.10942  -0.1551   0.1090   0.4740
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