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GOE 165 (MVA MK.11) AIRFOIL (goe165-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 165 (MVA MK.11) AIRFOIL (goe165-il)
Reynolds number: 50,000
Max Cl/Cd: 31.33 at α=10.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe165-il-50000.txt
Download as CSV file: xf-goe165-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 165 (MVA MK.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2824   0.11332   0.10700  -0.0235   1.0000   0.2411
  -8.000  -0.2712   0.10979   0.10351  -0.0225   1.0000   0.2482
  -7.750  -0.2959   0.11107   0.10500  -0.0219   1.0000   0.2538
  -7.500  -0.2698   0.10497   0.09888  -0.0208   1.0000   0.2596
  -7.250  -0.2851   0.10490   0.09897  -0.0194   1.0000   0.2672
  -7.000  -0.2796   0.10137   0.09552  -0.0183   1.0000   0.2705
  -6.750  -0.2745   0.09854   0.09276  -0.0168   1.0000   0.2757
  -6.500  -0.2958   0.09869   0.09310  -0.0141   1.0000   0.2811
  -6.250  -0.3089   0.09733   0.09192  -0.0121   1.0000   0.2830
  -6.000  -0.3039   0.09400   0.08866  -0.0103   1.0000   0.2850
  -5.750  -0.3068   0.09178   0.08655  -0.0085   1.0000   0.2870
  -5.500  -0.3144   0.08999   0.08489  -0.0068   1.0000   0.2882
  -5.250  -0.3338   0.06549   0.06037  -0.0513   1.0000   0.1273
  -5.000  -0.3234   0.06229   0.05718  -0.0513   1.0000   0.1205
  -4.750  -0.2115   0.03962   0.03226  -0.0946   1.0000   0.0997
  -4.500  -0.1798   0.03681   0.02913  -0.0973   1.0000   0.1021
  -4.250  -0.1469   0.03448   0.02638  -0.0997   1.0000   0.1042
  -4.000  -0.1163   0.03273   0.02427  -0.1010   1.0000   0.1060
  -3.750  -0.0879   0.03150   0.02274  -0.1015   1.0000   0.1095
  -3.500  -0.0611   0.03040   0.02161  -0.1017   1.0000   0.1157
  -3.250  -0.0306   0.02935   0.02064  -0.1031   1.0000   0.1323
  -3.000   0.0122   0.02781   0.01981  -0.1072   1.0000   0.1929
  -2.750   0.0070   0.03165   0.02463  -0.0989   1.0000   0.3563
  -2.500  -0.0021   0.03553   0.02862  -0.0897   1.0000   0.4131
  -2.250  -0.0083   0.03783   0.03109  -0.0815   1.0000   0.4572
  -2.000   0.0037   0.03906   0.03234  -0.0764   0.9942   0.5070
  -1.750   0.0438   0.03911   0.03213  -0.0780   0.9805   0.5509
  -1.500   0.0900   0.03873   0.03148  -0.0818   0.9661   0.5860
  -1.250   0.1374   0.03810   0.03062  -0.0860   0.9511   0.6086
  -1.000   0.1968   0.03744   0.02962  -0.0933   0.9354   0.6191
  -0.750   0.2581   0.03681   0.02869  -0.1010   0.9188   0.6262
  -0.500   0.3087   0.03612   0.02778  -0.1062   0.8997   0.6324
  -0.250   0.3654   0.03536   0.02681  -0.1120   0.8811   0.6416
   0.000   0.4220   0.03426   0.02557  -0.1170   0.8633   0.6502
   0.250   0.4722   0.03339   0.02456  -0.1209   0.8419   0.6593
   0.500   0.5299   0.03207   0.02313  -0.1253   0.8229   0.6700
   0.750   0.5888   0.03055   0.02149  -0.1292   0.8047   0.6813
   1.000   0.6342   0.02961   0.02044  -0.1313   0.7804   0.6913
   1.250   0.6891   0.02838   0.01905  -0.1344   0.7599   0.7026
   1.500   0.7256   0.02798   0.01854  -0.1350   0.7335   0.7122
   1.750   0.7620   0.02783   0.01826  -0.1358   0.7090   0.7213
   2.000   0.7985   0.02784   0.01813  -0.1368   0.6875   0.7310
   2.250   0.8287   0.02812   0.01833  -0.1370   0.6681   0.7401
   2.500   0.8560   0.02868   0.01886  -0.1371   0.6498   0.7490
   2.750   0.8834   0.02920   0.01937  -0.1372   0.6341   0.7591
   3.000   0.9104   0.02974   0.01996  -0.1372   0.6205   0.7700
   3.250   0.9395   0.03019   0.02042  -0.1374   0.6092   0.7826
   3.500   0.9617   0.03102   0.02140  -0.1370   0.5977   0.7967
   3.750   0.9819   0.03195   0.02253  -0.1363   0.5872   0.8164
   4.000   1.0074   0.03227   0.02307  -0.1357   0.5790   0.8683
   4.250   1.0296   0.03366   0.02457  -0.1361   0.5691   1.0000
   4.500   1.0545   0.03515   0.02609  -0.1368   0.5612   1.0000
   4.750   1.0794   0.03657   0.02755  -0.1374   0.5537   1.0000
   5.000   1.0996   0.03833   0.02943  -0.1375   0.5464   1.0000
   5.250   1.1203   0.04000   0.03117  -0.1376   0.5392   1.0000
   5.500   1.1406   0.04180   0.03305  -0.1375   0.5334   1.0000
   5.750   1.1449   0.04489   0.03631  -0.1365   0.5266   1.0000
   6.000   1.1758   0.04555   0.03698  -0.1367   0.5199   1.0000
   6.250   1.1590   0.05051   0.04214  -0.1344   0.5127   1.0000
   6.500   1.1962   0.05033   0.04201  -0.1345   0.5051   1.0000
   6.750   1.1142   0.06231   0.05415  -0.1312   0.5024   1.0000
   7.000   1.0250   0.07657   0.06837  -0.1321   0.5029   1.0000
   7.250   0.9960   0.08381   0.07563  -0.1329   0.5013   1.0000
   7.500   1.0258   0.08426   0.07614  -0.1318   0.4900   1.0000
   7.750   0.9978   0.09095   0.08284  -0.1323   0.4860   1.0000
   8.000   1.0160   0.09235   0.08430  -0.1311   0.4733   1.0000
   8.250   1.0370   0.09330   0.08535  -0.1297   0.4598   1.0000
   8.500   1.0212   0.09891   0.09100  -0.1302   0.4545   1.0000
   8.750   1.0317   0.10139   0.09355  -0.1294   0.4442   1.0000
   9.000   1.0553   0.10223   0.09449  -0.1279   0.4316   1.0000
   9.250   1.0307   0.10947   0.10175  -0.1294   0.4301   1.0000
   9.500   1.0153   0.11568   0.10801  -0.1308   0.4290   1.0000
   9.750   1.0052   0.12150   0.11388  -0.1321   0.4295   1.0000
  10.000   1.0010   0.12693   0.11938  -0.1335   0.4311   1.0000
  10.250   1.0045   0.13192   0.12445  -0.1347   0.4328   1.0000
  10.500   1.0117   0.13417   0.12676  -0.1337   0.4174   1.0000
  10.750   1.5101   0.04820   0.04178  -0.0966   0.2665   1.0000
  11.000   1.4911   0.05014   0.04399  -0.0919   0.2510   1.0000
  11.250   1.4695   0.05315   0.04724  -0.0887   0.2331   1.0000
  11.500   1.4481   0.05713   0.05144  -0.0871   0.2115   1.0000
  11.750   1.4271   0.06202   0.05647  -0.0869   0.1843   1.0000
  12.000   1.4075   0.06669   0.06069  -0.0867   0.1464   1.0000
  12.250   1.3848   0.07275   0.06656  -0.0875   0.1322   1.0000
  12.500   1.3619   0.07924   0.07298  -0.0887   0.1230   1.0000
  12.750   1.3406   0.08579   0.07952  -0.0901   0.1149   1.0000
  13.000   1.3206   0.09219   0.08581  -0.0915   0.1083   1.0000
  13.250   1.3049   0.09823   0.09185  -0.0929   0.1000   1.0000
  13.500   1.2914   0.10384   0.09735  -0.0941   0.0932   1.0000
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