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GOE 234 (MVA CA5) AIRFOIL (goe234-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 234 (MVA CA5) AIRFOIL (goe234-il)
Reynolds number: 200,000
Max Cl/Cd: 77.01 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe234-il-200000.txt
Download as CSV file: xf-goe234-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250   0.0217   0.09789   0.09414  -0.1055   0.9510   0.0735
  -9.000   0.0102   0.09464   0.09091  -0.1147   0.9408   0.0790
  -8.750   0.0340   0.09052   0.08677  -0.1142   0.9391   0.0804
  -8.500   0.0501   0.08881   0.08506  -0.1127   0.9322   0.0819
  -8.250   0.0660   0.08663   0.08286  -0.1134   0.9267   0.0845
  -8.000   0.0381   0.08397   0.08024  -0.1208   0.9120   0.0911
  -7.750   0.0676   0.08070   0.07695  -0.1181   0.9104   0.0927
  -7.500   0.0923   0.07914   0.07536  -0.1170   0.9073   0.0957
  -7.250   0.0875   0.03770   0.03299  -0.1944   0.8899   0.0680
  -7.000   0.1449   0.03117   0.02598  -0.2105   0.8848   0.0670
  -6.750   0.2024   0.02804   0.02224  -0.2218   0.8805   0.0680
  -6.500   0.2443   0.02558   0.01947  -0.2266   0.8768   0.0685
  -6.250   0.2803   0.02353   0.01727  -0.2289   0.8738   0.0694
  -6.000   0.3099   0.02245   0.01617  -0.2297   0.8677   0.0709
  -5.750   0.3412   0.02159   0.01527  -0.2306   0.8621   0.0732
  -5.500   0.3739   0.02078   0.01437  -0.2314   0.8580   0.0753
  -5.250   0.4048   0.02022   0.01375  -0.2318   0.8526   0.0770
  -5.000   0.4346   0.01984   0.01330  -0.2320   0.8459   0.0787
  -4.750   0.4608   0.01971   0.01326  -0.2305   0.8411   0.0820
  -4.500   0.4885   0.01974   0.01336  -0.2298   0.8354   0.0862
  -4.250   0.5160   0.01984   0.01347  -0.2291   0.8282   0.0901
  -4.000   0.5456   0.01995   0.01364  -0.2286   0.8231   0.0965
  -3.750   0.5871   0.01905   0.01278  -0.2328   0.8171   0.1137
  -3.500   0.6247   0.01861   0.01294  -0.2358   0.8102   0.2362
  -3.250   0.6522   0.01918   0.01338  -0.2347   0.8048   0.2685
  -3.000   0.6674   0.02079   0.01509  -0.2301   0.7971   0.2730
  -2.750   0.6927   0.02144   0.01566  -0.2288   0.7904   0.2835
  -2.500   0.7120   0.02249   0.01669  -0.2252   0.7855   0.2861
  -2.250   0.7420   0.02262   0.01675  -0.2260   0.7774   0.2978
  -2.000   0.7610   0.02338   0.01753  -0.2227   0.7712   0.2997
  -1.750   0.7825   0.02395   0.01808  -0.2203   0.7657   0.3035
  -1.500   0.8121   0.02402   0.01811  -0.2210   0.7581   0.3146
  -1.250   0.8470   0.02409   0.01802  -0.2227   0.7525   0.3283
  -1.000   0.8641   0.02444   0.01845  -0.2194   0.7464   0.3306
  -0.750   0.8931   0.02486   0.01881  -0.2196   0.7392   0.3445
  -0.500   0.9039   0.02512   0.01917  -0.2142   0.7339   0.3498
   0.000   0.9422   0.02551   0.01961  -0.2091   0.7189   0.3843
   0.250   0.9784   0.02510   0.01910  -0.2115   0.7110   0.3967
   0.500   1.0037   0.02453   0.01850  -0.2109   0.7020   0.4016
   0.750   1.0400   0.02416   0.01801  -0.2133   0.6928   0.4122
   1.000   1.0663   0.02365   0.01746  -0.2130   0.6847   0.4164
   1.250   1.1025   0.02349   0.01720  -0.2153   0.6782   0.4275
   1.500   1.1277   0.02310   0.01684  -0.2149   0.6709   0.4316
   1.750   1.1616   0.02293   0.01655  -0.2165   0.6649   0.4437
   2.000   1.1867   0.02267   0.01635  -0.2162   0.6573   0.4495
   2.250   1.2203   0.02253   0.01613  -0.2178   0.6501   0.4593
   2.500   1.2475   0.02226   0.01585  -0.2178   0.6431   0.4639
   2.750   1.2796   0.02225   0.01580  -0.2192   0.6349   0.4744
   3.000   1.3081   0.02194   0.01544  -0.2195   0.6283   0.4779
   3.250   1.3380   0.02206   0.01558  -0.2203   0.6198   0.4896
   3.500   1.3664   0.02173   0.01519  -0.2206   0.6130   0.4931
   3.750   1.3941   0.02182   0.01533  -0.2209   0.6045   0.5058
   4.000   1.4211   0.02158   0.01507  -0.2209   0.5969   0.5111
   4.250   1.4476   0.02156   0.01509  -0.2209   0.5884   0.5240
   4.500   1.4750   0.02153   0.01504  -0.2210   0.5800   0.5382
   4.750   1.5003   0.02152   0.01508  -0.2207   0.5710   0.5532
   5.000   1.5262   0.02142   0.01496  -0.2205   0.5620   0.5618
   5.250   1.5649   0.02184   0.01526  -0.2237   0.5510   0.5025
   5.500   1.5888   0.02176   0.01517  -0.2230   0.5415   0.5163
   5.750   1.6335   0.02145   0.01452  -0.2278   0.5284   0.4218
   6.000   1.6556   0.02158   0.01466  -0.2269   0.5153   0.4224
   6.250   1.6764   0.02177   0.01481  -0.2256   0.5005   0.4232
   6.500   1.6951   0.02202   0.01501  -0.2241   0.4843   0.4243
   6.750   1.7114   0.02235   0.01528  -0.2220   0.4669   0.4259
   7.000   1.7245   0.02274   0.01568  -0.2195   0.4493   0.4278
   7.250   1.7356   0.02326   0.01617  -0.2165   0.4317   0.4298
   7.500   1.7433   0.02389   0.01674  -0.2130   0.4148   0.4316
   7.750   1.7463   0.02461   0.01740  -0.2087   0.3996   0.4328
   8.000   1.7541   0.02547   0.01819  -0.2056   0.3848   0.4341
   8.250   1.7628   0.02642   0.01905  -0.2027   0.3717   0.4356
   8.500   1.7732   0.02734   0.01995  -0.2003   0.3596   0.4372
   8.750   1.7845   0.02829   0.02087  -0.1980   0.3494   0.4390
   9.000   1.7945   0.02936   0.02185  -0.1956   0.3402   0.4406
   9.250   1.8063   0.03027   0.02284  -0.1936   0.3314   0.4426
   9.500   1.8160   0.03135   0.02390  -0.1913   0.3236   0.4448
   9.750   1.8266   0.03238   0.02502  -0.1892   0.3156   0.4474
  10.000   1.8348   0.03361   0.02622  -0.1869   0.3075   0.4498
  10.250   1.8445   0.03477   0.02747  -0.1848   0.3000   0.4521
  10.500   1.8531   0.03605   0.02877  -0.1828   0.2929   0.4541
  10.750   1.8620   0.03736   0.03011  -0.1808   0.2863   0.4560
  11.000   1.8699   0.03873   0.03158  -0.1788   0.2790   0.4578
  11.250   1.8759   0.04027   0.03311  -0.1767   0.2722   0.4597
  11.500   1.8810   0.04191   0.03492  -0.1747   0.2639   0.4617
  11.750   1.8835   0.04380   0.03680  -0.1725   0.2563   0.4640
  12.000   1.8886   0.04559   0.03877  -0.1708   0.2480   0.4668
  12.250   1.8882   0.04787   0.04102  -0.1686   0.2399   0.4693
  12.500   1.8884   0.05027   0.04355  -0.1668   0.2282   0.4717
  12.750   1.8865   0.05299   0.04634  -0.1650   0.2153   0.4736
  13.000   1.8829   0.05600   0.04941  -0.1633   0.2003   0.4754
  13.250   1.8745   0.05971   0.05311  -0.1616   0.1782   0.4769
  13.500   1.8527   0.06507   0.05824  -0.1597   0.1332   0.4776
  13.750   1.8240   0.07147   0.06439  -0.1579   0.1041   0.4780
  14.000   1.8014   0.07735   0.07020  -0.1565   0.0833   0.4787
  14.250   1.7829   0.08293   0.07575  -0.1556   0.0686   0.4797
  14.500   1.7682   0.08817   0.08101  -0.1550   0.0606   0.4809
  14.750   1.7559   0.09324   0.08615  -0.1547   0.0562   0.4823
  15.000   1.7442   0.09831   0.09130  -0.1546   0.0533   0.4838
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