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GOE 184 (MVA H.29) AIRFOIL (goe184-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 184 (MVA H.29) AIRFOIL (goe184-il)
Reynolds number: 100,000
Max Cl/Cd: 60.39 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe184-il-100000-n5.txt
Download as CSV file: xf-goe184-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 184 (MVA H.29) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3030   0.10140   0.09666  -0.0276   1.0000   0.0582
  -8.000  -0.3097   0.09979   0.09517  -0.0298   1.0000   0.0586
  -7.750  -0.3137   0.09771   0.09319  -0.0323   1.0000   0.0588
  -7.500  -0.3003   0.09316   0.08866  -0.0282   1.0000   0.0597
  -7.250  -0.2990   0.09062   0.08619  -0.0276   1.0000   0.0602
  -7.000  -0.3004   0.08835   0.08401  -0.0271   1.0000   0.0606
  -6.750  -0.3045   0.08631   0.08206  -0.0264   1.0000   0.0608
  -6.250  -0.2535   0.07486   0.07048  -0.0434   0.9814   0.0496
  -5.750  -0.1811   0.06025   0.05558  -0.0666   0.9622   0.0429
  -5.500  -0.1522   0.05662   0.05188  -0.0711   0.9520   0.0442
  -5.250  -0.1211   0.05362   0.04879  -0.0753   0.9427   0.0465
  -5.000  -0.0824   0.04783   0.04277  -0.0833   0.9334   0.0462
  -4.750  -0.0460   0.04235   0.03700  -0.0898   0.9223   0.0463
  -4.500  -0.0077   0.03714   0.03139  -0.0956   0.9127   0.0487
  -4.250   0.0303   0.03108   0.02472  -0.1007   0.9032   0.0492
  -4.000   0.0650   0.02614   0.01902  -0.1038   0.8927   0.0501
  -3.750   0.0969   0.02458   0.01716  -0.1050   0.8826   0.0523
  -3.500   0.1282   0.02320   0.01548  -0.1058   0.8718   0.0547
  -3.250   0.1589   0.02134   0.01315  -0.1064   0.8598   0.0563
  -3.000   0.1895   0.01974   0.01108  -0.1067   0.8481   0.0586
  -2.750   0.2185   0.01908   0.01031  -0.1067   0.8351   0.0608
  -2.500   0.2472   0.01833   0.00932  -0.1064   0.8204   0.0650
  -2.250   0.2751   0.01780   0.00860  -0.1059   0.8038   0.0712
  -2.000   0.3028   0.01719   0.00776  -0.1054   0.7869   0.0800
  -1.750   0.3302   0.01676   0.00718  -0.1049   0.7706   0.0897
  -1.500   0.3574   0.01648   0.00685  -0.1045   0.7557   0.0991
  -1.250   0.3847   0.01631   0.00656  -0.1041   0.7418   0.1083
  -1.000   0.4119   0.01616   0.00630  -0.1036   0.7279   0.1141
  -0.750   0.4390   0.01609   0.00614  -0.1032   0.7139   0.1234
  -0.500   0.4660   0.01603   0.00599  -0.1028   0.7000   0.1314
  -0.250   0.4927   0.01595   0.00585  -0.1024   0.6856   0.1390
   0.000   0.5194   0.01590   0.00573  -0.1020   0.6710   0.1477
   0.250   0.5459   0.01579   0.00560  -0.1015   0.6567   0.1535
   0.500   0.5728   0.01572   0.00547  -0.1011   0.6428   0.1582
   0.750   0.5999   0.01568   0.00536  -0.1007   0.6291   0.1649
   1.000   0.6269   0.01563   0.00529  -0.1004   0.6156   0.1761
   1.250   0.6539   0.01557   0.00526  -0.1001   0.6026   0.2004
   1.500   0.6807   0.01543   0.00530  -0.0998   0.5904   0.2832
   2.000   0.7302   0.01429   0.00534  -0.0981   0.5678   1.0000
   2.250   0.7570   0.01453   0.00542  -0.0977   0.5573   1.0000
   2.500   0.7837   0.01479   0.00552  -0.0973   0.5476   1.0000
   2.750   0.8102   0.01505   0.00571  -0.0970   0.5365   1.0000
   3.000   0.8366   0.01533   0.00589  -0.0966   0.5257   1.0000
   3.250   0.8629   0.01564   0.00606  -0.0962   0.5155   1.0000
   3.500   0.8890   0.01593   0.00633  -0.0959   0.5039   1.0000
   3.750   0.9152   0.01623   0.00659  -0.0955   0.4935   1.0000
   4.000   0.9413   0.01655   0.00684  -0.0952   0.4844   1.0000
   4.250   0.9674   0.01685   0.00720  -0.0949   0.4747   1.0000
   4.500   0.9935   0.01718   0.00750  -0.0945   0.4667   1.0000
   4.750   1.0193   0.01750   0.00786  -0.0942   0.4571   1.0000
   5.000   1.0450   0.01782   0.00822  -0.0938   0.4480   1.0000
   5.250   1.0704   0.01813   0.00854  -0.0934   0.4387   1.0000
   5.500   1.0956   0.01845   0.00894  -0.0930   0.4287   1.0000
   5.750   1.1208   0.01878   0.00930  -0.0925   0.4200   1.0000
   6.000   1.1455   0.01911   0.00971  -0.0920   0.4098   1.0000
   6.250   1.1701   0.01945   0.01013  -0.0915   0.3996   1.0000
   6.500   1.1944   0.01980   0.01053  -0.0909   0.3903   1.0000
   6.750   1.2186   0.02018   0.01104  -0.0903   0.3807   1.0000
   7.000   1.2426   0.02059   0.01154  -0.0898   0.3717   1.0000
   7.250   1.2661   0.02101   0.01203  -0.0891   0.3629   1.0000
   7.500   1.2888   0.02145   0.01259  -0.0883   0.3505   1.0000
   7.750   1.3096   0.02190   0.01311  -0.0873   0.3336   1.0000
   8.000   1.3292   0.02243   0.01365  -0.0861   0.3142   1.0000
   8.250   1.3490   0.02298   0.01431  -0.0850   0.2949   1.0000
   8.500   1.3682   0.02358   0.01501  -0.0839   0.2745   1.0000
   8.750   1.3859   0.02426   0.01575  -0.0826   0.2462   1.0000
   9.000   1.4001   0.02517   0.01660  -0.0809   0.2097   1.0000
   9.250   1.4081   0.02661   0.01775  -0.0787   0.1778   1.0000
   9.500   1.4158   0.02811   0.01915  -0.0765   0.1582   1.0000
   9.750   1.4256   0.02944   0.02055  -0.0744   0.1371   1.0000
  10.000   1.4304   0.03100   0.02206  -0.0719   0.1021   1.0000
  10.250   1.4242   0.03330   0.02411  -0.0686   0.0770   1.0000
  10.500   1.4202   0.03562   0.02636  -0.0658   0.0516   1.0000
  10.750   1.4137   0.03831   0.02898  -0.0635   0.0434   1.0000
  11.000   1.4082   0.04113   0.03188  -0.0617   0.0397   1.0000
  11.500   1.3963   0.04757   0.03858  -0.0596   0.0353   1.0000
  11.750   1.3902   0.05110   0.04231  -0.0592   0.0336   1.0000
  12.000   1.3825   0.05499   0.04637  -0.0591   0.0321   1.0000
  12.250   1.3734   0.05922   0.05076  -0.0593   0.0310   1.0000
  12.500   1.3628   0.06381   0.05549  -0.0598   0.0300   1.0000
  12.750   1.3514   0.06860   0.06042  -0.0605   0.0293   1.0000
  13.000   1.3401   0.07344   0.06539  -0.0612   0.0286   1.0000
  13.250   1.3341   0.07759   0.06968  -0.0617   0.0280   1.0000
  13.500   1.3295   0.08161   0.07387  -0.0622   0.0274   1.0000
  13.750   1.3255   0.08556   0.07798  -0.0626   0.0266   1.0000
  14.000   1.3220   0.08947   0.08203  -0.0631   0.0257   1.0000
  14.250   1.3188   0.09337   0.08605  -0.0637   0.0248   1.0000
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