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GOE 133 (MVA H.11) AIRFOIL (goe133-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 133 (MVA H.11) AIRFOIL (goe133-il)
Reynolds number: 50,000
Max Cl/Cd: 40.85 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe133-il-50000-n5.txt
Download as CSV file: xf-goe133-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 133 (MVA H.11) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3421   0.09722   0.09065  -0.0237   1.0000   0.0884
  -7.250  -0.3407   0.09462   0.08815  -0.0245   1.0000   0.0909
  -7.000  -0.3407   0.09231   0.08594  -0.0267   1.0000   0.0939
  -6.750  -0.3419   0.09074   0.08444  -0.0327   1.0000   0.0961
  -6.500  -0.3372   0.08843   0.08213  -0.0377   1.0000   0.0967
  -6.250  -0.3319   0.08355   0.07739  -0.0330   1.0000   0.0982
  -6.000  -0.3263   0.08029   0.07420  -0.0305   1.0000   0.1010
  -5.750  -0.3204   0.07753   0.07148  -0.0308   1.0000   0.1057
  -5.250  -0.3048   0.07138   0.06536  -0.0345   1.0000   0.1154
  -4.750  -0.2613   0.06098   0.05450  -0.0435   1.0000   0.0664
  -4.500  -0.2481   0.05753   0.05103  -0.0437   1.0000   0.0635
  -4.250  -0.2288   0.05375   0.04708  -0.0457   1.0000   0.0610
  -4.000  -0.2067   0.05017   0.04328  -0.0478   1.0000   0.0608
  -3.750  -0.1830   0.04690   0.03975  -0.0498   1.0000   0.0629
  -3.500  -0.1528   0.04334   0.03580  -0.0526   0.9986   0.0639
  -3.250  -0.1045   0.03907   0.03093  -0.0583   0.9915   0.0647
  -3.000  -0.0582   0.03572   0.02700  -0.0632   0.9840   0.0705
  -2.750  -0.0132   0.03300   0.02378  -0.0672   0.9763   0.0742
  -2.500   0.0318   0.03076   0.02075  -0.0705   0.9673   0.0824
  -2.250   0.0719   0.02888   0.01868  -0.0733   0.9576   0.0874
  -2.000   0.1153   0.02753   0.01673  -0.0760   0.9481   0.0966
  -1.750   0.1558   0.02610   0.01515  -0.0784   0.9380   0.1012
  -1.500   0.1942   0.02523   0.01399  -0.0801   0.9260   0.1108
  -1.250   0.2331   0.02431   0.01294  -0.0819   0.9144   0.1184
  -1.000   0.2727   0.02355   0.01195  -0.0836   0.9028   0.1261
  -0.750   0.3099   0.02288   0.01122  -0.0850   0.8900   0.1411
  -0.500   0.3453   0.02224   0.01056  -0.0861   0.8759   0.1575
  -0.250   0.3793   0.02156   0.00997  -0.0870   0.8610   0.1855
   0.000   0.4077   0.01878   0.00952  -0.0864   0.8466   1.0000
   0.250   0.4392   0.01883   0.00912  -0.0864   0.8293   1.0000
   0.500   0.4704   0.01888   0.00887  -0.0865   0.8123   1.0000
   0.750   0.5013   0.01894   0.00868  -0.0865   0.7954   1.0000
   1.000   0.5316   0.01901   0.00854  -0.0864   0.7788   1.0000
   1.250   0.5613   0.01911   0.00846  -0.0862   0.7624   1.0000
   1.500   0.5903   0.01924   0.00843  -0.0859   0.7462   1.0000
   1.750   0.6187   0.01942   0.00846  -0.0856   0.7302   1.0000
   2.000   0.6466   0.01963   0.00854  -0.0851   0.7144   1.0000
   2.250   0.6735   0.01987   0.00866  -0.0846   0.6968   1.0000
   2.500   0.6992   0.02009   0.00877  -0.0837   0.6762   1.0000
   2.750   0.7251   0.02025   0.00880  -0.0827   0.6552   1.0000
   3.000   0.7498   0.02048   0.00892  -0.0816   0.6332   1.0000
   3.250   0.7750   0.02074   0.00908  -0.0807   0.6132   1.0000
   3.500   0.8006   0.02104   0.00933  -0.0800   0.5963   1.0000
   3.750   0.8263   0.02137   0.00961  -0.0793   0.5802   1.0000
   4.000   0.8518   0.02173   0.00993  -0.0786   0.5645   1.0000
   4.250   0.8772   0.02211   0.01032  -0.0780   0.5489   1.0000
   4.500   0.9023   0.02253   0.01073  -0.0773   0.5332   1.0000
   4.750   0.9270   0.02298   0.01120  -0.0766   0.5171   1.0000
   5.000   0.9515   0.02345   0.01175  -0.0759   0.5008   1.0000
   5.250   0.9757   0.02396   0.01232  -0.0752   0.4846   1.0000
   5.500   0.9997   0.02449   0.01293  -0.0745   0.4684   1.0000
   5.750   1.0233   0.02505   0.01360  -0.0737   0.4516   1.0000
   6.000   1.0465   0.02563   0.01428  -0.0729   0.4347   1.0000
   6.250   1.0696   0.02624   0.01498  -0.0721   0.4180   1.0000
   6.500   1.0924   0.02689   0.01573  -0.0712   0.4018   1.0000
   6.750   1.1148   0.02754   0.01652  -0.0704   0.3858   1.0000
   7.000   1.1365   0.02819   0.01726  -0.0694   0.3695   1.0000
   7.250   1.1573   0.02880   0.01795  -0.0682   0.3528   1.0000
   7.500   1.1769   0.02947   0.01874  -0.0670   0.3356   1.0000
   7.750   1.1960   0.03017   0.01957  -0.0658   0.3186   1.0000
   8.000   1.2145   0.03091   0.02048  -0.0645   0.3024   1.0000
   8.250   1.2321   0.03169   0.02137  -0.0631   0.2861   1.0000
   8.500   1.2482   0.03254   0.02229  -0.0616   0.2692   1.0000
   8.750   1.2639   0.03351   0.02336  -0.0601   0.2536   1.0000
   9.000   1.2780   0.03459   0.02453  -0.0585   0.2376   1.0000
   9.250   1.2901   0.03583   0.02591  -0.0567   0.2209   1.0000
   9.500   1.3004   0.03724   0.02749  -0.0548   0.2038   1.0000
   9.750   1.3085   0.03880   0.02921  -0.0527   0.1868   1.0000
  10.000   1.3141   0.04050   0.03105  -0.0505   0.1705   1.0000
  10.250   1.3175   0.04230   0.03296  -0.0481   0.1565   1.0000
  10.500   1.3207   0.04421   0.03498  -0.0458   0.1454   1.0000
  10.750   1.3236   0.04623   0.03712  -0.0437   0.1360   1.0000
  11.000   1.3253   0.04851   0.03960  -0.0418   0.1268   1.0000
  11.250   1.3246   0.05087   0.04208  -0.0402   0.1192   1.0000
  11.500   1.3228   0.05343   0.04480  -0.0389   0.1123   1.0000
  11.750   1.3211   0.05634   0.04786  -0.0379   0.1062   1.0000
  12.000   1.3161   0.05936   0.05091  -0.0373   0.1002   1.0000
  12.250   1.3091   0.06307   0.05477  -0.0371   0.0941   1.0000
  12.500   1.3022   0.06667   0.05834  -0.0372   0.0883   1.0000
  12.750   1.2942   0.07097   0.06282  -0.0376   0.0832   1.0000
  13.000   1.2859   0.07543   0.06745  -0.0383   0.0784   1.0000
  13.250   1.2827   0.07896   0.07086  -0.0381   0.0731   1.0000
  13.500   1.2686   0.08483   0.07712  -0.0399   0.0704   1.0000
  13.750   1.2549   0.09082   0.08339  -0.0420   0.0677   1.0000
  14.000   1.2421   0.09671   0.08949  -0.0441   0.0650   1.0000
  14.250   1.2435   0.09955   0.09213  -0.0437   0.0601   1.0000
  14.500   1.2252   0.10696   0.09985  -0.0472   0.0593   1.0000
  14.750   1.2055   0.11509   0.10825  -0.0514   0.0587   1.0000
  15.000   1.1841   0.12415   0.11754  -0.0564   0.0585   1.0000
  15.250   1.1611   0.13431   0.12787  -0.0623   0.0587   1.0000
  15.500   1.1364   0.14583   0.13949  -0.0690   0.0592   1.0000
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