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GOE 143 (MVA H.20) AIRFOIL (goe143-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 143 (MVA H.20) AIRFOIL (goe143-il)
Reynolds number: 100,000
Max Cl/Cd: 53.72 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe143-il-100000.txt
Download as CSV file: xf-goe143-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 143 (MVA H.20) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4031   0.10187   0.09693  -0.0082   1.0000   0.0716
  -8.000  -0.4008   0.09930   0.09442  -0.0109   1.0000   0.0744
  -7.750  -0.4039   0.09806   0.09329  -0.0188   1.0000   0.0761
  -7.500  -0.3959   0.09526   0.09050  -0.0310   1.0000   0.0768
  -7.250  -0.3875   0.08911   0.08439  -0.0184   1.0000   0.0791
  -7.000  -0.3775   0.08576   0.08106  -0.0181   1.0000   0.0817
  -6.750  -0.3681   0.08250   0.07783  -0.0205   1.0000   0.0848
  -6.500  -0.3547   0.07939   0.07470  -0.0294   1.0000   0.0894
  -6.250  -0.3400   0.07515   0.07038  -0.0381   1.0000   0.0913
  -6.000  -0.3350   0.07151   0.06687  -0.0326   1.0000   0.0933
  -5.750  -0.3254   0.06874   0.06414  -0.0315   1.0000   0.0975
  -5.500  -0.3007   0.06515   0.06027  -0.0429   1.0000   0.1052
  -5.250  -0.2958   0.06161   0.05687  -0.0390   1.0000   0.1069
  -5.000  -0.2863   0.05898   0.05429  -0.0375   1.0000   0.1105
  -4.750  -0.2622   0.05564   0.05065  -0.0438   1.0000   0.1197
  -4.500  -0.2561   0.05294   0.04810  -0.0407   1.0000   0.1228
  -4.250  -0.2357   0.05024   0.04519  -0.0436   1.0000   0.1347
  -4.000  -0.2266   0.04795   0.04299  -0.0415   1.0000   0.1396
  -3.750  -0.2069   0.04533   0.04020  -0.0432   1.0000   0.1512
  -3.500  -0.1877   0.04318   0.03791  -0.0442   1.0000   0.1652
  -3.250  -0.1700   0.04120   0.03585  -0.0445   1.0000   0.1803
  -3.000  -0.1546   0.03927   0.03395  -0.0439   1.0000   0.1972
  -2.750  -0.1381   0.03766   0.03236  -0.0434   1.0000   0.2177
  -1.500   0.1190   0.02435   0.01634  -0.0679   0.9719   0.1304
  -1.250   0.1682   0.02260   0.01431  -0.0717   0.9616   0.1257
  -1.000   0.2194   0.02130   0.01274  -0.0758   0.9518   0.1267
  -0.750   0.2719   0.02000   0.01125  -0.0799   0.9420   0.1260
  -0.500   0.3173   0.01897   0.01014  -0.0825   0.9287   0.1285
  -0.250   0.3595   0.01797   0.00915  -0.0845   0.9140   0.1366
   0.000   0.3977   0.01708   0.00834  -0.0856   0.8978   0.1438
   0.250   0.4307   0.01627   0.00761  -0.0854   0.8793   0.1520
   0.500   0.4592   0.01569   0.00709  -0.0844   0.8571   0.1685
   0.750   0.4883   0.01509   0.00658  -0.0834   0.8359   0.2035
   1.000   0.5121   0.01297   0.00623  -0.0810   0.8110   1.0000
   1.250   0.5374   0.01306   0.00602  -0.0793   0.7847   1.0000
   1.500   0.5625   0.01318   0.00589  -0.0778   0.7583   1.0000
   1.750   0.5875   0.01334   0.00585  -0.0765   0.7311   1.0000
   2.000   0.6129   0.01353   0.00586  -0.0754   0.7042   1.0000
   2.250   0.6386   0.01376   0.00591  -0.0744   0.6795   1.0000
   2.500   0.6644   0.01400   0.00596  -0.0735   0.6564   1.0000
   2.750   0.6901   0.01428   0.00609  -0.0726   0.6322   1.0000
   3.000   0.7157   0.01456   0.00618  -0.0717   0.6097   1.0000
   3.250   0.7409   0.01484   0.00633  -0.0708   0.5843   1.0000
   3.500   0.7661   0.01514   0.00647  -0.0699   0.5603   1.0000
   3.750   0.7915   0.01546   0.00667  -0.0692   0.5384   1.0000
   4.000   0.8174   0.01583   0.00695  -0.0686   0.5203   1.0000
   4.250   0.8433   0.01622   0.00727  -0.0681   0.5033   1.0000
   4.500   0.8691   0.01660   0.00763  -0.0675   0.4854   1.0000
   4.750   0.8946   0.01698   0.00802  -0.0670   0.4673   1.0000
   5.000   0.9198   0.01736   0.00837  -0.0664   0.4488   1.0000
   5.250   0.9448   0.01775   0.00870  -0.0657   0.4300   1.0000
   5.500   0.9694   0.01813   0.00911  -0.0650   0.4088   1.0000
   5.750   0.9936   0.01852   0.00951  -0.0642   0.3860   1.0000
   6.000   1.0170   0.01893   0.00994  -0.0633   0.3586   1.0000
   6.250   1.0394   0.01945   0.01038  -0.0623   0.3268   1.0000
   6.500   1.0614   0.02018   0.01095  -0.0613   0.2951   1.0000
   6.750   1.0840   0.02103   0.01174  -0.0604   0.2694   1.0000
   7.000   1.1068   0.02182   0.01241  -0.0597   0.2514   1.0000
   7.250   1.1293   0.02250   0.01307  -0.0589   0.2349   1.0000
   7.500   1.1515   0.02312   0.01371  -0.0582   0.2199   1.0000
   7.750   1.1735   0.02377   0.01438  -0.0575   0.2072   1.0000
   8.000   1.1959   0.02439   0.01514  -0.0568   0.1962   1.0000
   8.250   1.2175   0.02500   0.01589  -0.0560   0.1849   1.0000
   8.500   1.2381   0.02554   0.01656  -0.0552   0.1722   1.0000
   8.750   1.2580   0.02607   0.01727  -0.0543   0.1581   1.0000
   9.000   1.2761   0.02673   0.01801  -0.0533   0.1392   1.0000
   9.250   1.2941   0.02763   0.01907  -0.0521   0.1157   1.0000
   9.500   1.3085   0.02903   0.02046  -0.0506   0.0874   1.0000
   9.750   1.3216   0.03058   0.02197  -0.0488   0.0680   1.0000
  10.000   1.3324   0.03223   0.02358  -0.0469   0.0596   1.0000
  10.250   1.3417   0.03392   0.02538  -0.0448   0.0551   1.0000
  10.500   1.3462   0.03590   0.02737  -0.0424   0.0524   1.0000
  10.750   1.3500   0.03780   0.02941  -0.0397   0.0506   1.0000
  11.000   1.3535   0.03979   0.03153  -0.0373   0.0486   1.0000
  11.250   1.3562   0.04192   0.03376  -0.0351   0.0467   1.0000
  11.500   1.3580   0.04427   0.03616  -0.0333   0.0451   1.0000
  11.750   1.3618   0.04696   0.03887  -0.0315   0.0438   1.0000
  12.000   1.3699   0.04975   0.04179  -0.0298   0.0431   1.0000
  12.250   1.3758   0.05261   0.04491  -0.0284   0.0427   1.0000
  12.500   1.3789   0.05579   0.04835  -0.0271   0.0424   1.0000
  12.750   1.3782   0.05932   0.05216  -0.0260   0.0422   1.0000
  13.000   1.3732   0.06327   0.05639  -0.0253   0.0422   1.0000
  13.250   1.3637   0.06765   0.06107  -0.0252   0.0422   1.0000
  13.500   1.3507   0.07251   0.06620  -0.0258   0.0422   1.0000
  13.750   1.3345   0.07795   0.07191  -0.0272   0.0423   1.0000
  14.000   1.3160   0.08400   0.07821  -0.0294   0.0424   1.0000
  14.250   1.2957   0.09071   0.08515  -0.0326   0.0426   1.0000
  14.500   1.2737   0.09807   0.09272  -0.0364   0.0428   1.0000
  14.750   1.2510   0.10604   0.10087  -0.0410   0.0431   1.0000
  15.000   1.2261   0.11487   0.10992  -0.0467   0.0435   1.0000
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