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GOE 233 (MVA CA4) AIRFOIL (goe233-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 233 (MVA CA4) AIRFOIL (goe233-il)
Reynolds number: 50,000
Max Cl/Cd: 33.37 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe233-il-50000-n5.txt
Download as CSV file: xf-goe233-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.1831   0.10646   0.09978  -0.0588   0.9580   0.0841
  -7.500  -0.1707   0.10334   0.09665  -0.0600   0.9497   0.0827
  -7.250  -0.1555   0.09971   0.09301  -0.0633   0.9434   0.0802
  -7.000  -0.1510   0.09662   0.08993  -0.0655   0.9331   0.0779
  -6.750  -0.1416   0.09056   0.08383  -0.0746   0.9242   0.0739
  -6.500  -0.1327   0.08756   0.08084  -0.0765   0.9143   0.0737
  -6.250  -0.1104   0.08240   0.07563  -0.0844   0.9086   0.0741
  -6.000  -0.1013   0.08119   0.07446  -0.0831   0.8988   0.0755
  -5.750  -0.0764   0.07658   0.06978  -0.0901   0.8931   0.0756
  -5.500  -0.0621   0.06988   0.06302  -0.0995   0.8827   0.0743
  -5.250  -0.0186   0.05998   0.05290  -0.1172   0.8776   0.0740
  -5.000   0.0329   0.05223   0.04489  -0.1335   0.8725   0.0756
  -4.750   0.1217   0.04230   0.03419  -0.1604   0.8692   0.0813
  -4.500   0.1902   0.03758   0.02875  -0.1743   0.8658   0.0858
  -4.250   0.2315   0.03641   0.02753  -0.1778   0.8615   0.0905
  -4.000   0.2792   0.03497   0.02594  -0.1830   0.8582   0.0996
  -3.750   0.3097   0.03439   0.02537  -0.1851   0.8495   0.1117
  -3.500   0.3546   0.03343   0.02447  -0.1894   0.8451   0.1402
  -3.250   0.3864   0.03363   0.02483  -0.1900   0.8394   0.1748
  -3.000   0.4065   0.03465   0.02590  -0.1881   0.8307   0.2029
  -2.750   0.4306   0.03605   0.02729  -0.1853   0.8258   0.2229
  -2.500   0.4472   0.03701   0.02818  -0.1832   0.8160   0.2396
  -2.250   0.4814   0.03734   0.02830  -0.1842   0.8108   0.2635
  -2.000   0.5027   0.03815   0.02905  -0.1825   0.8033   0.2800
  -1.750   0.5276   0.03860   0.02942  -0.1818   0.7960   0.2960
  -1.500   0.5650   0.03832   0.02896  -0.1833   0.7919   0.3120
  -1.250   0.5932   0.03826   0.02872  -0.1849   0.7830   0.3249
  -1.000   0.6219   0.03814   0.02852  -0.1847   0.7773   0.3335
  -0.750   0.6629   0.03749   0.02769  -0.1873   0.7739   0.3458
  -0.500   0.6867   0.03777   0.02782  -0.1881   0.7639   0.3569
  -0.250   0.7183   0.03753   0.02750  -0.1885   0.7591   0.3663
   0.000   0.7470   0.03756   0.02744  -0.1892   0.7525   0.3764
   0.250   0.7767   0.03767   0.02740  -0.1904   0.7450   0.3875
   0.500   0.8092   0.03733   0.02704  -0.1908   0.7409   0.3958
   0.750   0.8298   0.03791   0.02757  -0.1905   0.7319   0.4053
   1.000   0.8606   0.03786   0.02746  -0.1911   0.7263   0.4162
   1.250   0.8959   0.03745   0.02702  -0.1920   0.7228   0.4257
   1.500   0.9125   0.03843   0.02795  -0.1914   0.7124   0.4336
   1.750   0.9450   0.03815   0.02767  -0.1919   0.7080   0.4400
   2.000   0.9666   0.03878   0.02828  -0.1917   0.6998   0.4455
   2.250   0.9954   0.03896   0.02842  -0.1922   0.6935   0.4508
   2.500   1.0311   0.03861   0.02804  -0.1931   0.6898   0.4565
   2.750   1.0440   0.03983   0.02929  -0.1918   0.6795   0.4604
   3.000   1.0784   0.03971   0.02910  -0.1927   0.6748   0.4649
   3.250   1.0971   0.04048   0.02992  -0.1918   0.6669   0.4684
   3.500   1.1218   0.04085   0.03032  -0.1915   0.6598   0.4729
   3.750   1.1616   0.04018   0.02958  -0.1925   0.6559   0.4782
   4.000   1.1713   0.04150   0.03095  -0.1906   0.6439   0.4808
   4.250   1.2127   0.04036   0.02982  -0.1913   0.6390   0.4851
   4.500   1.2237   0.04135   0.03088  -0.1891   0.6264   0.4886
   4.750   1.2707   0.03975   0.02922  -0.1903   0.6210   0.4949
   5.000   1.2798   0.04079   0.03036  -0.1878   0.6076   0.4978
   5.250   1.2990   0.04120   0.03084  -0.1864   0.5976   0.5012
   5.500   1.3266   0.04112   0.03082  -0.1858   0.5898   0.5052
   5.750   1.3399   0.04212   0.03192  -0.1840   0.5797   0.5091
   6.000   1.3688   0.04192   0.03180  -0.1835   0.5721   0.5143
   6.250   1.3762   0.04322   0.03323  -0.1810   0.5609   0.5179
   6.500   1.4102   0.04263   0.03272  -0.1809   0.5540   0.5238
   6.750   1.4093   0.04440   0.03463  -0.1776   0.5417   0.5268
   7.000   1.4488   0.04341   0.03374  -0.1780   0.5351   0.5324
   7.250   1.4467   0.04513   0.03562  -0.1744   0.5223   0.5358
   7.500   1.4521   0.04654   0.03716  -0.1718   0.5101   0.5404
   7.750   1.4922   0.04517   0.03593  -0.1718   0.5027   0.5486
   8.000   1.4905   0.04710   0.03802  -0.1686   0.4892   0.5528
   8.250   1.4963   0.04857   0.03964  -0.1663   0.4767   0.5580
   8.500   1.5212   0.04837   0.03958  -0.1650   0.4667   0.5650
   8.750   1.5393   0.04873   0.04011  -0.1633   0.4550   0.5723
   9.000   1.5439   0.05035   0.04190  -0.1610   0.4416   0.5790
   9.250   1.5570   0.05125   0.04296  -0.1591   0.4296   0.5883
   9.500   1.5907   0.05030   0.04216  -0.1583   0.4198   0.6035
   9.750   1.5883   0.05273   0.04481  -0.1558   0.4065   0.6130
  10.250   1.6167   0.05450   0.04699  -0.1524   0.3839   0.6641
  10.500   1.6144   0.05621   0.04885  -0.1494   0.3711   1.0000
  10.750   1.6096   0.05883   0.05154  -0.1471   0.3567   1.0000
  11.000   1.6066   0.06116   0.05390  -0.1449   0.3412   1.0000
  11.250   1.6033   0.06353   0.05628  -0.1428   0.3249   1.0000
  11.500   1.5996   0.06606   0.05880  -0.1409   0.3087   1.0000
  11.750   1.5960   0.06880   0.06156  -0.1392   0.2938   1.0000
  12.000   1.5938   0.07158   0.06438  -0.1378   0.2807   1.0000
  12.250   1.5940   0.07409   0.06691  -0.1364   0.2683   1.0000
  12.500   1.5954   0.07639   0.06919  -0.1349   0.2557   1.0000
  12.750   1.5917   0.07956   0.07244  -0.1338   0.2431   1.0000
  13.000   1.5847   0.08340   0.07641  -0.1331   0.2308   1.0000
  13.250   1.5793   0.08700   0.08007  -0.1324   0.2178   1.0000
  13.500   1.5728   0.09080   0.08391  -0.1319   0.2041   1.0000
  13.750   1.5642   0.09509   0.08827  -0.1317   0.1899   1.0000
  14.000   1.5532   0.10000   0.09329  -0.1321   0.1750   1.0000
  14.250   1.5418   0.10521   0.09862  -0.1328   0.1594   1.0000
  14.500   1.5320   0.11021   0.10367  -0.1336   0.1440   1.0000
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