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GOE 182 (MVA H.27) AIRFOIL (goe182-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 182 (MVA H.27) AIRFOIL (goe182-il)
Reynolds number: 50,000
Max Cl/Cd: 36.45 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe182-il-50000-n5.txt
Download as CSV file: xf-goe182-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 182 (MVA H.27) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2865   0.10374   0.09714  -0.0201   1.0000   0.1144
  -7.750  -0.2919   0.10258   0.09611  -0.0218   1.0000   0.1180
  -7.500  -0.2996   0.10187   0.09555  -0.0254   1.0000   0.1191
  -7.250  -0.2875   0.09711   0.09084  -0.0231   1.0000   0.1209
  -7.000  -0.2777   0.09385   0.08762  -0.0216   1.0000   0.1250
  -6.750  -0.2787   0.09230   0.08619  -0.0233   1.0000   0.1311
  -6.500  -0.2825   0.09120   0.08523  -0.0289   1.0000   0.1335
  -6.250  -0.2725   0.08698   0.08107  -0.0230   1.0000   0.1376
  -6.000  -0.2697   0.08480   0.07898  -0.0228   1.0000   0.1421
  -5.750  -0.2701   0.08409   0.07834  -0.0303   1.0000   0.1475
  -5.500  -0.2681   0.08104   0.07541  -0.0290   1.0000   0.1486
  -5.250  -0.2675   0.07841   0.07286  -0.0263   1.0000   0.1499
  -4.750  -0.1674   0.06251   0.05634  -0.0562   0.9771   0.0932
  -4.500  -0.1348   0.05890   0.05266  -0.0592   0.9656   0.0898
  -4.250  -0.0895   0.05362   0.04715  -0.0679   0.9532   0.0854
  -4.000  -0.0405   0.04832   0.04151  -0.0770   0.9408   0.0842
  -3.750   0.0069   0.04419   0.03705  -0.0842   0.9285   0.0861
  -3.500   0.0556   0.03964   0.03199  -0.0911   0.9153   0.0850
  -3.250   0.0999   0.03586   0.02769  -0.0960   0.8994   0.0847
  -3.000   0.1390   0.03308   0.02444  -0.0989   0.8804   0.0860
  -2.750   0.1778   0.03076   0.02159  -0.1012   0.8611   0.0901
  -2.500   0.2164   0.02853   0.01872  -0.1030   0.8420   0.0926
  -2.250   0.2517   0.02692   0.01681  -0.1038   0.8227   0.0947
  -2.000   0.2834   0.02576   0.01539  -0.1039   0.8011   0.0976
  -1.750   0.3149   0.02480   0.01408  -0.1038   0.7802   0.1032
  -1.500   0.3447   0.02406   0.01311  -0.1033   0.7599   0.1102
  -1.250   0.3736   0.02343   0.01215  -0.1026   0.7379   0.1172
  -1.000   0.4020   0.02295   0.01147  -0.1020   0.7163   0.1265
  -0.750   0.4301   0.02258   0.01089  -0.1012   0.6956   0.1417
  -0.500   0.4571   0.02221   0.01036  -0.1005   0.6731   0.1612
  -0.250   0.4839   0.02182   0.00996  -0.0998   0.6514   0.1931
   0.000   0.5103   0.02138   0.00968  -0.0991   0.6301   0.2509
   0.250   0.5358   0.02091   0.00949  -0.0984   0.6079   0.3445
   0.500   0.5573   0.02002   0.00937  -0.0968   0.5881   0.5690
   1.000   0.6107   0.01986   0.00895  -0.0951   0.5472   1.0000
   1.250   0.6369   0.02020   0.00894  -0.0944   0.5280   1.0000
   1.500   0.6630   0.02057   0.00900  -0.0938   0.5102   1.0000
   1.750   0.6891   0.02097   0.00913  -0.0933   0.4935   1.0000
   2.000   0.7151   0.02139   0.00932  -0.0928   0.4778   1.0000
   2.250   0.7412   0.02184   0.00956  -0.0923   0.4633   1.0000
   2.500   0.7672   0.02231   0.00984  -0.0919   0.4501   1.0000
   2.750   0.7933   0.02278   0.01013  -0.0914   0.4388   1.0000
   3.000   0.8193   0.02328   0.01049  -0.0910   0.4282   1.0000
   3.250   0.8453   0.02382   0.01095  -0.0907   0.4189   1.0000
   3.500   0.8715   0.02434   0.01134  -0.0903   0.4113   1.0000
   3.750   0.8974   0.02494   0.01191  -0.0900   0.4037   1.0000
   4.000   0.9233   0.02552   0.01243  -0.0897   0.3973   1.0000
   4.250   0.9492   0.02614   0.01300  -0.0893   0.3915   1.0000
   4.500   0.9745   0.02682   0.01370  -0.0890   0.3854   1.0000
   4.750   1.0002   0.02744   0.01428  -0.0886   0.3807   1.0000
   5.000   1.0253   0.02816   0.01504  -0.0883   0.3759   1.0000
   5.250   1.0499   0.02895   0.01592  -0.0880   0.3711   1.0000
   5.500   1.0749   0.02970   0.01671  -0.0876   0.3672   1.0000
   5.750   1.1006   0.03044   0.01745  -0.0873   0.3643   1.0000
   6.000   1.1243   0.03140   0.01855  -0.0870   0.3611   1.0000
   6.250   1.1471   0.03246   0.01983  -0.0866   0.3578   1.0000
   6.500   1.1702   0.03351   0.02103  -0.0862   0.3550   1.0000
   6.750   1.1935   0.03454   0.02219  -0.0858   0.3526   1.0000
   7.000   1.2172   0.03555   0.02331  -0.0854   0.3504   1.0000
   7.250   1.2416   0.03652   0.02439  -0.0851   0.3484   1.0000
   7.500   1.2595   0.03808   0.02624  -0.0844   0.3457   1.0000
   7.750   1.2766   0.03972   0.02818  -0.0837   0.3428   1.0000
   8.000   1.2939   0.04134   0.03005  -0.0830   0.3404   1.0000
   8.250   1.3112   0.04300   0.03199  -0.0823   0.3384   1.0000
   8.500   1.3284   0.04470   0.03392  -0.0817   0.3367   1.0000
   8.750   1.3455   0.04642   0.03586  -0.0810   0.3351   1.0000
   9.000   1.3629   0.04816   0.03782  -0.0803   0.3337   1.0000
   9.250   1.3709   0.05075   0.04071  -0.0793   0.3319   1.0000
   9.500   1.3524   0.05560   0.04597  -0.0775   0.3284   1.0000
   9.750   1.3318   0.06058   0.05122  -0.0759   0.3246   1.0000
  10.250   1.3951   0.06014   0.05109  -0.0743   0.3175   1.0000
  10.500   1.1565   0.09416   0.08496  -0.0839   0.3076   1.0000
  10.750   1.1797   0.09418   0.08515  -0.0822   0.3041   1.0000
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