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GOE 144 (MVA H.21) AIRFOIL (goe144-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 144 (MVA H.21) AIRFOIL (goe144-il)
Reynolds number: 500,000
Max Cl/Cd: 98.21 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe144-il-500000-n5.txt
Download as CSV file: xf-goe144-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 144 (MVA H.21) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3618   0.09198   0.08981  -0.0260   1.0000   0.0070
  -8.500  -0.3676   0.08840   0.08627  -0.0260   1.0000   0.0069
  -8.000  -0.4066   0.02919   0.02614  -0.0923   0.9705   0.0072
  -7.750  -0.3801   0.02074   0.01702  -0.0983   0.9664   0.0075
  -7.500  -0.3543   0.01872   0.01474  -0.0991   0.9608   0.0080
  -7.250  -0.3259   0.01706   0.01280  -0.1001   0.9567   0.0087
  -7.000  -0.2943   0.01584   0.01132  -0.1015   0.9539   0.0092
  -6.750  -0.2657   0.01442   0.00964  -0.1022   0.9488   0.0101
  -6.500  -0.2341   0.01359   0.00867  -0.1032   0.9442   0.0111
  -6.250  -0.2001   0.01293   0.00787  -0.1047   0.9402   0.0123
  -6.000  -0.1682   0.01234   0.00713  -0.1056   0.9346   0.0136
  -5.750  -0.1355   0.01177   0.00651  -0.1067   0.9291   0.0160
  -5.500  -0.1015   0.01144   0.00610  -0.1080   0.9237   0.0186
  -5.250  -0.0708   0.01115   0.00569  -0.1085   0.9164   0.0206
  -4.750  -0.0108   0.01030   0.00461  -0.1093   0.9012   0.0255
  -4.500   0.0183   0.01002   0.00422  -0.1095   0.8927   0.0276
  -4.250   0.0462   0.00978   0.00387  -0.1093   0.8827   0.0296
  -4.000   0.0733   0.00956   0.00354  -0.1090   0.8716   0.0308
  -3.750   0.1004   0.00938   0.00327  -0.1086   0.8580   0.0316
  -3.500   0.1269   0.00908   0.00285  -0.1081   0.8404   0.0340
  -3.250   0.1529   0.00886   0.00252  -0.1075   0.8103   0.0370
  -3.000   0.1771   0.00881   0.00221  -0.1064   0.7589   0.0396
  -2.750   0.2009   0.00883   0.00203  -0.1053   0.7225   0.0450
  -2.500   0.2260   0.00883   0.00198  -0.1046   0.6995   0.0610
  -2.250   0.2517   0.00888   0.00190  -0.1039   0.6805   0.0666
  -2.000   0.2776   0.00890   0.00183  -0.1034   0.6635   0.0719
  -1.750   0.3037   0.00894   0.00176  -0.1029   0.6479   0.0752
  -1.500   0.3299   0.00896   0.00168  -0.1024   0.6335   0.0773
  -1.250   0.3560   0.00894   0.00160  -0.1019   0.6181   0.0802
  -1.000   0.3819   0.00894   0.00154  -0.1014   0.6015   0.0839
  -0.750   0.4078   0.00897   0.00149  -0.1009   0.5846   0.0878
  -0.500   0.4337   0.00900   0.00145  -0.1004   0.5686   0.0916
  -0.250   0.4597   0.00902   0.00144  -0.0999   0.5536   0.0979
   0.000   0.4856   0.00904   0.00147  -0.0995   0.5388   0.1140
   0.250   0.5118   0.00910   0.00150  -0.0990   0.5255   0.1267
   0.500   0.5381   0.00917   0.00153  -0.0986   0.5142   0.1350
   1.000   0.5906   0.00931   0.00159  -0.0978   0.4894   0.1462
   1.250   0.6169   0.00938   0.00163  -0.0974   0.4769   0.1511
   1.500   0.6433   0.00946   0.00167  -0.0970   0.4674   0.1545
   2.000   0.6957   0.00960   0.00179  -0.0962   0.4452   0.1639
   2.250   0.7219   0.00969   0.00187  -0.0958   0.4335   0.1681
   2.500   0.7480   0.00977   0.00195  -0.0954   0.4223   0.1732
   2.750   0.7739   0.00987   0.00204  -0.0950   0.4111   0.1796
   3.000   0.7999   0.00997   0.00216  -0.0946   0.3998   0.1873
   3.250   0.8256   0.01007   0.00228  -0.0942   0.3864   0.2011
   3.500   0.8510   0.01017   0.00244  -0.0937   0.3709   0.2373
   3.750   0.8764   0.01027   0.00261  -0.0932   0.3567   0.2801
   4.000   0.9004   0.01012   0.00281  -0.0927   0.3418   0.4689
   4.500   0.9575   0.00975   0.00328  -0.0934   0.2907   1.0000
   4.750   0.9783   0.01039   0.00363  -0.0922   0.2403   1.0000
   5.000   1.0013   0.01081   0.00392  -0.0914   0.2140   1.0000
   5.250   1.0234   0.01132   0.00425  -0.0905   0.1804   1.0000
   5.500   1.0409   0.01231   0.00483  -0.0889   0.1085   1.0000
   5.750   1.0624   0.01287   0.00528  -0.0879   0.0869   1.0000
   6.000   1.0847   0.01335   0.00568  -0.0870   0.0690   1.0000
   6.250   1.1016   0.01438   0.00644  -0.0852   0.0191   1.0000
   6.500   1.1240   0.01483   0.00695  -0.0842   0.0138   1.0000
   6.750   1.1468   0.01521   0.00739  -0.0833   0.0125   1.0000
   7.000   1.1688   0.01566   0.00793  -0.0823   0.0112   1.0000
   7.250   1.1901   0.01617   0.00851  -0.0812   0.0101   1.0000
   7.500   1.2085   0.01696   0.00941  -0.0796   0.0088   1.0000
   7.750   1.2295   0.01744   0.00995  -0.0785   0.0082   1.0000
   8.000   1.2492   0.01802   0.01060  -0.0772   0.0076   1.0000
   8.250   1.2678   0.01868   0.01133  -0.0757   0.0070   1.0000
   8.500   1.2852   0.01939   0.01213  -0.0741   0.0066   1.0000
   8.750   1.3014   0.02016   0.01296  -0.0723   0.0063   1.0000
   9.000   1.3144   0.02112   0.01400  -0.0700   0.0060   1.0000
   9.250   1.3220   0.02232   0.01531  -0.0669   0.0057   1.0000
   9.500   1.3326   0.02314   0.01622  -0.0643   0.0055   1.0000
   9.750   1.3437   0.02392   0.01709  -0.0617   0.0052   1.0000
  10.000   1.3520   0.02488   0.01813  -0.0590   0.0049   1.0000
  10.250   1.3599   0.02589   0.01923  -0.0563   0.0046   1.0000
  10.500   1.3651   0.02711   0.02054  -0.0535   0.0045   1.0000
  10.750   1.3693   0.02845   0.02199  -0.0508   0.0044   1.0000
  11.000   1.3729   0.02992   0.02354  -0.0484   0.0043   1.0000
  11.250   1.3761   0.03151   0.02523  -0.0461   0.0042   1.0000
  11.500   1.3782   0.03328   0.02713  -0.0441   0.0041   1.0000
  11.750   1.3788   0.03531   0.02925  -0.0424   0.0040   1.0000
  12.000   1.3758   0.03785   0.03189  -0.0407   0.0038   1.0000
  12.250   1.3720   0.04070   0.03486  -0.0394   0.0038   1.0000
  12.500   1.3703   0.04352   0.03782  -0.0386   0.0037   1.0000
  12.750   1.3687   0.04650   0.04093  -0.0380   0.0037   1.0000
  13.000   1.3676   0.04955   0.04413  -0.0378   0.0036   1.0000
  13.250   1.3648   0.05293   0.04767  -0.0376   0.0035   1.0000
  13.500   1.3615   0.05648   0.05135  -0.0377   0.0035   1.0000
  13.750   1.3574   0.06025   0.05528  -0.0381   0.0035   1.0000
  14.000   1.3515   0.06442   0.05962  -0.0386   0.0034   1.0000
  14.250   1.3453   0.06875   0.06412  -0.0394   0.0033   1.0000
  14.500   1.3375   0.07348   0.06902  -0.0405   0.0033   1.0000
  14.750   1.3287   0.07855   0.07427  -0.0420   0.0033   1.0000
  15.000   1.3197   0.08383   0.07972  -0.0439   0.0032   1.0000
  15.250   1.3099   0.08941   0.08546  -0.0461   0.0032   1.0000
  15.500   1.2972   0.09577   0.09200  -0.0488   0.0032   1.0000
  15.750   1.2871   0.10187   0.09825  -0.0517   0.0031   1.0000
  16.000   1.2736   0.10886   0.10542  -0.0552   0.0031   1.0000
  16.250   1.2617   0.11581   0.11252  -0.0589   0.0031   1.0000
  16.500   1.2490   0.12317   0.12004  -0.0630   0.0030   1.0000
  16.750   1.2345   0.13122   0.12825  -0.0676   0.0031   1.0000
  17.000   1.2200   0.13961   0.13679  -0.0726   0.0031   1.0000
  17.250   1.2074   0.14784   0.14516  -0.0776   0.0031   1.0000
  17.500   1.1925   0.15703   0.15449  -0.0832   0.0031   1.0000
  17.750   1.1800   0.16591   0.16350  -0.0888   0.0031   1.0000
  18.000   1.1632   0.17655   0.17426  -0.0953   0.0032   1.0000
  18.250   1.1471   0.18774   0.18556  -0.1021   0.0032   1.0000
  18.500   1.1287   0.20101   0.19893  -0.1097   0.0033   1.0000
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