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GOE 184 (MVA H.29) AIRFOIL (goe184-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 184 (MVA H.29) AIRFOIL (goe184-il)
Reynolds number: 200,000
Max Cl/Cd: 79.45 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe184-il-200000-n5.txt
Download as CSV file: xf-goe184-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3081   0.08972   0.08638  -0.0287   1.0000   0.0225
  -7.750  -0.3089   0.08711   0.08383  -0.0287   1.0000   0.0223
  -7.500  -0.3138   0.08475   0.08155  -0.0281   0.9998   0.0222
  -7.250  -0.2918   0.07910   0.07588  -0.0366   0.9881   0.0224
  -7.000  -0.2680   0.07462   0.07139  -0.0437   0.9767   0.0239
  -6.750  -0.2437   0.07164   0.06839  -0.0482   0.9660   0.0256
  -6.500  -0.2180   0.06622   0.06292  -0.0565   0.9531   0.0259
  -6.250  -0.1904   0.06044   0.05706  -0.0650   0.9396   0.0261
  -6.000  -0.1599   0.05404   0.05052  -0.0741   0.9257   0.0273
  -5.750  -0.1187   0.03970   0.03574  -0.0909   0.9115   0.0289
  -5.500  -0.0890   0.03475   0.03051  -0.0957   0.8990   0.0299
  -5.250  -0.0617   0.03375   0.02940  -0.0967   0.8863   0.0313
  -5.000  -0.0267   0.02016   0.01418  -0.1049   0.8752   0.0334
  -4.750   0.0016   0.01828   0.01178  -0.1054   0.8628   0.0348
  -4.500   0.0296   0.01705   0.01015  -0.1054   0.8501   0.0358
  -4.250   0.0570   0.01585   0.00868  -0.1054   0.8369   0.0366
  -4.000   0.0843   0.01507   0.00769  -0.1051   0.8231   0.0374
  -3.750   0.1116   0.01448   0.00692  -0.1048   0.8086   0.0382
  -3.500   0.1387   0.01401   0.00629  -0.1044   0.7932   0.0396
  -3.250   0.1659   0.01361   0.00570  -0.1041   0.7773   0.0412
  -3.000   0.1931   0.01325   0.00517  -0.1037   0.7614   0.0423
  -2.750   0.2205   0.01295   0.00472  -0.1033   0.7460   0.0432
  -2.500   0.2479   0.01272   0.00439  -0.1030   0.7319   0.0449
  -2.250   0.2756   0.01255   0.00418  -0.1028   0.7186   0.0472
  -1.750   0.3309   0.01241   0.00397  -0.1023   0.6918   0.0591
  -1.500   0.3586   0.01238   0.00381  -0.1020   0.6782   0.0695
  -1.250   0.3863   0.01240   0.00371  -0.1017   0.6640   0.0773
  -1.000   0.4138   0.01233   0.00358  -0.1015   0.6488   0.0832
  -0.750   0.4412   0.01230   0.00346  -0.1013   0.6325   0.0869
  -0.500   0.4686   0.01230   0.00335  -0.1010   0.6157   0.0899
  -0.250   0.4958   0.01227   0.00325  -0.1008   0.5994   0.0938
   0.000   0.5230   0.01228   0.00318  -0.1006   0.5846   0.0975
   0.250   0.5502   0.01231   0.00313  -0.1004   0.5717   0.0999
   0.500   0.5774   0.01237   0.00310  -0.1001   0.5601   0.1040
   0.750   0.6045   0.01241   0.00312  -0.1000   0.5488   0.1109
   1.000   0.6317   0.01248   0.00315  -0.0998   0.5377   0.1183
   1.250   0.6589   0.01254   0.00319  -0.0996   0.5269   0.1236
   1.750   0.7132   0.01268   0.00331  -0.0993   0.5060   0.1419
   2.000   0.7403   0.01272   0.00340  -0.0991   0.4969   0.1698
   2.250   0.7673   0.01264   0.00356  -0.0990   0.4874   0.2643
   2.500   0.7931   0.01224   0.00372  -0.0989   0.4780   0.5050
   3.000   0.8428   0.01169   0.00390  -0.0971   0.4592   1.0000
   3.250   0.8697   0.01189   0.00403  -0.0969   0.4500   1.0000
   3.500   0.8965   0.01208   0.00419  -0.0967   0.4399   1.0000
   3.750   0.9233   0.01227   0.00435  -0.0965   0.4289   1.0000
   4.000   0.9497   0.01248   0.00451  -0.0962   0.4177   1.0000
   4.250   0.9760   0.01271   0.00470  -0.0959   0.4065   1.0000
   4.500   1.0023   0.01293   0.00490  -0.0957   0.3955   1.0000
   4.750   1.0285   0.01317   0.00512  -0.0954   0.3858   1.0000
   5.000   1.0543   0.01344   0.00537  -0.0951   0.3773   1.0000
   5.250   1.0804   0.01369   0.00564  -0.0948   0.3689   1.0000
   5.500   1.1060   0.01399   0.00592  -0.0944   0.3611   1.0000
   5.750   1.1317   0.01426   0.00624  -0.0941   0.3522   1.0000
   6.000   1.1569   0.01458   0.00656  -0.0937   0.3431   1.0000
   6.250   1.1822   0.01488   0.00690  -0.0933   0.3351   1.0000
   6.500   1.2070   0.01521   0.00726  -0.0929   0.3254   1.0000
   6.750   1.2310   0.01560   0.00764  -0.0924   0.3111   1.0000
   7.000   1.2548   0.01598   0.00804  -0.0918   0.2954   1.0000
   7.250   1.2787   0.01636   0.00845  -0.0913   0.2823   1.0000
   7.500   1.3021   0.01677   0.00888  -0.0907   0.2613   1.0000
   7.750   1.3227   0.01740   0.00939  -0.0898   0.2204   1.0000
   8.000   1.3388   0.01849   0.01017  -0.0885   0.1782   1.0000
   8.250   1.3565   0.01943   0.01103  -0.0873   0.1598   1.0000
   8.500   1.3751   0.02025   0.01184  -0.0861   0.1443   1.0000
   8.750   1.3934   0.02106   0.01264  -0.0850   0.1205   1.0000
   9.000   1.4051   0.02241   0.01374  -0.0831   0.0847   1.0000
   9.250   1.4146   0.02385   0.01504  -0.0810   0.0474   1.0000
   9.500   1.4202   0.02552   0.01656  -0.0783   0.0343   1.0000
   9.750   1.4260   0.02693   0.01803  -0.0755   0.0296   1.0000
  10.000   1.4338   0.02815   0.01938  -0.0731   0.0269   1.0000
  10.250   1.4408   0.02948   0.02087  -0.0708   0.0248   1.0000
  10.500   1.4449   0.03110   0.02264  -0.0686   0.0231   1.0000
  10.750   1.4448   0.03317   0.02485  -0.0664   0.0216   1.0000
  11.000   1.4463   0.03525   0.02707  -0.0646   0.0204   1.0000
  11.250   1.4500   0.03726   0.02924  -0.0634   0.0194   1.0000
  11.500   1.4516   0.03959   0.03171  -0.0623   0.0183   1.0000
  11.750   1.4513   0.04227   0.03453  -0.0615   0.0176   1.0000
  12.000   1.4495   0.04524   0.03764  -0.0609   0.0170   1.0000
  12.250   1.4461   0.04850   0.04104  -0.0606   0.0164   1.0000
  12.500   1.4407   0.05214   0.04479  -0.0605   0.0160   1.0000
  12.750   1.4328   0.05618   0.04896  -0.0607   0.0156   1.0000
  13.000   1.4223   0.06066   0.05354  -0.0609   0.0152   1.0000
  13.250   1.4195   0.06424   0.05727  -0.0612   0.0149   1.0000
  13.500   1.4160   0.06795   0.06113  -0.0616   0.0144   1.0000
  13.750   1.4122   0.07179   0.06510  -0.0620   0.0140   1.0000
  14.000   1.4080   0.07572   0.06915  -0.0626   0.0135   1.0000
  14.250   1.4039   0.07971   0.07326  -0.0632   0.0131   1.0000
  14.500   1.3998   0.08375   0.07741  -0.0640   0.0128   1.0000
  14.750   1.3956   0.08781   0.08158  -0.0647   0.0125   1.0000
  15.000   1.3917   0.09187   0.08573  -0.0655   0.0122   1.0000
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