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GOE 233 (MVA CA4) AIRFOIL (goe233-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 233 (MVA CA4) AIRFOIL (goe233-il)
Reynolds number: 100,000
Max Cl/Cd: 63.07 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe233-il-100000-n5.txt
Download as CSV file: xf-goe233-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1359   0.10890   0.10386  -0.0730   0.9629   0.0738
  -8.250  -0.0886   0.08846   0.08330  -0.0865   0.9374   0.0496
  -8.000  -0.0753   0.08533   0.08016  -0.0886   0.9295   0.0490
  -7.750  -0.0645   0.08196   0.07678  -0.0910   0.9214   0.0485
  -7.500  -0.0566   0.07851   0.07332  -0.0933   0.9120   0.0482
  -7.250  -0.0493   0.07452   0.06933  -0.0968   0.9027   0.0486
  -7.000  -0.0389   0.06961   0.06439  -0.1022   0.8943   0.0490
  -6.750  -0.0290   0.06471   0.05948  -0.1074   0.8846   0.0488
  -6.500   0.0457   0.03400   0.02762  -0.1698   0.8759   0.0474
  -6.250   0.1021   0.02943   0.02243  -0.1830   0.8698   0.0492
  -6.000   0.1404   0.02765   0.02043  -0.1871   0.8641   0.0505
  -5.750   0.1752   0.02659   0.01926  -0.1891   0.8599   0.0515
  -5.500   0.2055   0.02585   0.01843  -0.1901   0.8530   0.0525
  -5.250   0.2369   0.02522   0.01770  -0.1910   0.8468   0.0538
  -5.000   0.2708   0.02462   0.01695  -0.1921   0.8425   0.0554
  -4.750   0.3013   0.02414   0.01641  -0.1932   0.8347   0.0576
  -4.500   0.3368   0.02343   0.01562  -0.1954   0.8290   0.0614
  -4.250   0.3735   0.02272   0.01477  -0.1976   0.8245   0.0657
  -4.000   0.4073   0.02206   0.01403  -0.1998   0.8164   0.0718
  -3.750   0.4469   0.02104   0.01288  -0.2031   0.8110   0.0844
  -3.500   0.4874   0.01985   0.01179  -0.2071   0.8054   0.1204
  -3.250   0.5208   0.01931   0.01123  -0.2090   0.7977   0.1676
  -3.000   0.5516   0.01922   0.01122  -0.2093   0.7921   0.1983
  -2.750   0.5781   0.01947   0.01152  -0.2088   0.7839   0.2209
  -2.500   0.6064   0.01960   0.01157  -0.2084   0.7770   0.2376
  -2.250   0.6347   0.01976   0.01163  -0.2082   0.7704   0.2546
  -2.000   0.6619   0.01997   0.01176  -0.2078   0.7627   0.2680
  -1.750   0.6903   0.02024   0.01193  -0.2073   0.7571   0.2825
  -1.500   0.7155   0.02070   0.01236  -0.2065   0.7493   0.2964
  -1.250   0.7436   0.02096   0.01251  -0.2062   0.7430   0.3099
  -1.000   0.7693   0.02130   0.01285  -0.2051   0.7373   0.3170
  -0.750   0.7982   0.02129   0.01273  -0.2055   0.7299   0.3264
  -0.250   0.8562   0.02129   0.01251  -0.2058   0.7178   0.3409
   0.250   0.9117   0.02139   0.01254  -0.2052   0.7062   0.3509
   0.500   0.9398   0.02143   0.01251  -0.2055   0.6991   0.3575
   0.750   0.9667   0.02151   0.01260  -0.2051   0.6930   0.3618
   1.000   0.9960   0.02153   0.01252  -0.2052   0.6876   0.3698
   1.250   1.0215   0.02171   0.01275  -0.2048   0.6803   0.3754
   1.500   1.0495   0.02175   0.01276  -0.2046   0.6745   0.3812
   1.750   1.0780   0.02177   0.01270  -0.2049   0.6673   0.3865
   2.000   1.1054   0.02176   0.01267  -0.2047   0.6594   0.3893
   2.250   1.1327   0.02178   0.01268  -0.2044   0.6520   0.3923
   2.500   1.1591   0.02185   0.01275  -0.2041   0.6435   0.3958
   2.750   1.1880   0.02184   0.01267  -0.2041   0.6368   0.3992
   3.000   1.2141   0.02200   0.01283  -0.2039   0.6282   0.4023
   3.250   1.2423   0.02198   0.01278  -0.2037   0.6213   0.4049
   3.500   1.2663   0.02219   0.01309  -0.2031   0.6119   0.4077
   3.750   1.2940   0.02224   0.01311  -0.2028   0.6046   0.4110
   4.000   1.3184   0.02247   0.01340  -0.2023   0.5954   0.4142
   4.250   1.3459   0.02255   0.01344  -0.2021   0.5875   0.4172
   4.500   1.3695   0.02278   0.01376  -0.2013   0.5774   0.4195
   4.750   1.3962   0.02287   0.01384  -0.2009   0.5695   0.4223
   5.000   1.4187   0.02317   0.01429  -0.2000   0.5596   0.4255
   5.250   1.4444   0.02333   0.01444  -0.1995   0.5516   0.4292
   5.500   1.4669   0.02365   0.01486  -0.1986   0.5413   0.4327
   5.750   1.4907   0.02387   0.01515  -0.1978   0.5324   0.4353
   6.000   1.5132   0.02414   0.01552  -0.1968   0.5226   0.4379
   6.250   1.5351   0.02445   0.01592  -0.1957   0.5127   0.4410
   6.500   1.5579   0.02470   0.01619  -0.1947   0.5030   0.4448
   6.750   1.5777   0.02511   0.01670  -0.1933   0.4913   0.4487
   7.000   1.5975   0.02545   0.01714  -0.1918   0.4796   0.4518
   7.250   1.6171   0.02581   0.01754  -0.1903   0.4675   0.4553
   7.500   1.6353   0.02624   0.01803  -0.1886   0.4547   0.4589
   7.750   1.6520   0.02677   0.01865  -0.1867   0.4415   0.4623
   8.000   1.6675   0.02734   0.01927  -0.1846   0.4273   0.4656
   8.250   1.6798   0.02799   0.01995  -0.1820   0.4104   0.4691
   8.500   1.6879   0.02878   0.02074  -0.1789   0.3906   0.4729
   8.750   1.6903   0.02973   0.02165  -0.1748   0.3698   0.4765
   9.000   1.6927   0.03090   0.02281  -0.1712   0.3468   0.4801
   9.250   1.6943   0.03223   0.02410  -0.1677   0.3248   0.4832
   9.500   1.6958   0.03371   0.02553  -0.1645   0.3057   0.4866
   9.750   1.6978   0.03530   0.02709  -0.1615   0.2893   0.4901
  10.000   1.6991   0.03705   0.02881  -0.1587   0.2746   0.4938
  10.250   1.7010   0.03886   0.03065  -0.1561   0.2613   0.4976
  10.500   1.7030   0.04074   0.03257  -0.1536   0.2495   0.5020
  10.750   1.7045   0.04273   0.03460  -0.1513   0.2393   0.5070
  11.000   1.7070   0.04474   0.03670  -0.1492   0.2289   0.5126
  11.250   1.7085   0.04688   0.03895  -0.1472   0.2187   0.5181
  11.500   1.7070   0.04934   0.04147  -0.1452   0.2080   0.5241
  11.750   1.7075   0.05177   0.04407  -0.1435   0.1955   0.5309
  12.000   1.7060   0.05448   0.04692  -0.1419   0.1815   0.5383
  12.250   1.7019   0.05754   0.05009  -0.1404   0.1638   0.5466
  12.500   1.6944   0.06112   0.05370  -0.1391   0.1404   0.5562
  12.750   1.6814   0.06549   0.05799  -0.1379   0.1178   0.5675
  13.000   1.6681   0.07007   0.06251  -0.1369   0.1013   0.5859
  13.250   1.6541   0.07430   0.06688  -0.1357   0.0912   0.8640
  13.500   1.6413   0.07880   0.07139  -0.1349   0.0838   1.0000
  13.750   1.6324   0.08321   0.07586  -0.1344   0.0778   1.0000
  14.000   1.6227   0.08782   0.08052  -0.1342   0.0729   1.0000
  14.250   1.6131   0.09255   0.08530  -0.1341   0.0692   1.0000
  14.500   1.6070   0.09682   0.08971  -0.1342   0.0655   1.0000
  14.750   1.5989   0.10146   0.09444  -0.1345   0.0624   1.0000
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