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GOE 165 (MVA MK.11) AIRFOIL (goe165-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 165 (MVA MK.11) AIRFOIL (goe165-il)
Reynolds number: 500,000
Max Cl/Cd: 85.7 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe165-il-500000.txt
Download as CSV file: xf-goe165-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3270   0.11140   0.10922  -0.0309   1.0000   0.0151
  -9.750  -0.3264   0.10777   0.10561  -0.0316   1.0000   0.0151
  -9.500  -0.3344   0.10277   0.10066  -0.0318   1.0000   0.0156
  -9.250  -0.3325   0.10044   0.09835  -0.0314   1.0000   0.0159
  -9.000  -0.3311   0.09809   0.09602  -0.0310   1.0000   0.0162
  -8.750  -0.3306   0.09571   0.09368  -0.0305   1.0000   0.0166
  -8.500  -0.3324   0.09313   0.09113  -0.0301   1.0000   0.0170
  -8.250  -0.3365   0.09050   0.08854  -0.0294   1.0000   0.0174
  -8.000  -0.3254   0.08585   0.08390  -0.0341   0.9980   0.0182
  -7.750  -0.3120   0.07979   0.07785  -0.0413   0.9949   0.0193
  -7.500  -0.3014   0.06999   0.06806  -0.0523   0.9885   0.0207
  -7.250  -0.2762   0.05359   0.05143  -0.0815   0.9792   0.0209
  -7.000  -0.2241   0.03625   0.03343  -0.1170   0.9731   0.0223
  -6.750  -0.1956   0.03371   0.03085  -0.1203   0.9665   0.0234
  -6.500  -0.1526   0.03144   0.02824  -0.1266   0.9624   0.0272
  -6.250  -0.1180   0.02732   0.02385  -0.1322   0.9569   0.0311
  -6.000  -0.0834   0.02600   0.02236  -0.1347   0.9496   0.0353
  -5.500  -0.0082   0.01647   0.01171  -0.1393   0.9343   0.0187
  -5.250   0.0266   0.01407   0.00904  -0.1404   0.9237   0.0167
  -5.000   0.0704   0.01271   0.00757  -0.1437   0.9130   0.0171
  -4.750   0.1289   0.01153   0.00625  -0.1503   0.8992   0.0179
  -4.500   0.1832   0.01072   0.00524  -0.1561   0.8709   0.0196
  -4.250   0.2209   0.01028   0.00448  -0.1581   0.8229   0.0206
  -4.000   0.2491   0.01004   0.00387  -0.1580   0.7758   0.0214
  -3.750   0.2761   0.00984   0.00337  -0.1576   0.7463   0.0239
  -3.500   0.3033   0.00973   0.00312  -0.1573   0.7260   0.0290
  -3.250   0.3309   0.00962   0.00292  -0.1572   0.7103   0.0500
  -3.000   0.3589   0.00932   0.00264  -0.1573   0.6969   0.1016
  -2.500   0.4150   0.00866   0.00225  -0.1577   0.6752   0.2527
  -2.250   0.4426   0.00861   0.00231  -0.1576   0.6658   0.3076
  -1.750   0.4974   0.00886   0.00248  -0.1570   0.6437   0.3475
  -1.500   0.5247   0.00898   0.00252  -0.1567   0.6315   0.3561
  -1.250   0.5519   0.00909   0.00256  -0.1563   0.6192   0.3618
  -1.000   0.5791   0.00920   0.00257  -0.1560   0.6068   0.3675
  -0.750   0.6059   0.00930   0.00262  -0.1556   0.5906   0.3721
  -0.500   0.6321   0.00944   0.00267  -0.1551   0.5665   0.3772
  -0.250   0.6574   0.00966   0.00268  -0.1544   0.5237   0.3828
   0.000   0.6790   0.01016   0.00282  -0.1531   0.4464   0.3872
   0.250   0.7034   0.01058   0.00303  -0.1523   0.4110   0.3918
   0.750   0.7551   0.01112   0.00331  -0.1514   0.3756   0.3995
   1.000   0.7815   0.01133   0.00350  -0.1510   0.3643   0.4043
   1.250   0.8080   0.01155   0.00365  -0.1507   0.3555   0.4091
   1.500   0.8346   0.01174   0.00377  -0.1504   0.3467   0.4123
   1.750   0.8613   0.01184   0.00387  -0.1501   0.3389   0.4151
   2.000   0.8875   0.01202   0.00401  -0.1497   0.3310   0.4180
   2.250   0.9143   0.01216   0.00415  -0.1494   0.3245   0.4217
   2.500   0.9409   0.01233   0.00429  -0.1491   0.3185   0.4254
   2.750   0.9672   0.01246   0.00441  -0.1488   0.3131   0.4286
   3.000   0.9939   0.01256   0.00454  -0.1485   0.3064   0.4314
   3.250   1.0197   0.01275   0.00471  -0.1481   0.2996   0.4345
   3.500   1.0465   0.01286   0.00484  -0.1479   0.2938   0.4379
   3.750   1.0726   0.01304   0.00499  -0.1475   0.2873   0.4411
   4.000   1.0989   0.01313   0.00512  -0.1472   0.2808   0.4441
   4.250   1.1247   0.01328   0.00528  -0.1468   0.2722   0.4464
   4.500   1.1501   0.01348   0.00541  -0.1463   0.2569   0.4485
   4.750   1.1750   0.01371   0.00557  -0.1458   0.2376   0.4509
   5.000   1.1987   0.01406   0.00579  -0.1452   0.2131   0.4532
   5.250   1.2115   0.01552   0.00667  -0.1428   0.1205   0.4550
   5.500   1.2331   0.01605   0.00712  -0.1418   0.1012   0.4573
   5.750   1.2531   0.01674   0.00768  -0.1405   0.0635   0.4596
   6.000   1.2748   0.01725   0.00816  -0.1395   0.0570   0.4622
   6.250   1.2977   0.01761   0.00860  -0.1386   0.0512   0.4648
   6.500   1.3190   0.01814   0.00918  -0.1375   0.0446   0.4675
   6.750   1.3428   0.01839   0.00944  -0.1368   0.0394   0.4701
   7.000   1.3633   0.01890   0.00989  -0.1356   0.0196   0.4727
   7.250   1.3828   0.01952   0.01053  -0.1341   0.0158   0.4754
   7.500   1.4034   0.02001   0.01112  -0.1328   0.0142   0.4785
   7.750   1.4230   0.02056   0.01180  -0.1313   0.0136   0.4818
   8.000   1.4411   0.02120   0.01256  -0.1296   0.0129   0.4852
   8.250   1.4574   0.02192   0.01343  -0.1277   0.0123   0.4885
   8.500   1.4706   0.02276   0.01440  -0.1252   0.0118   0.4919
   8.750   1.4793   0.02371   0.01548  -0.1220   0.0114   0.4953
   9.000   1.4847   0.02497   0.01686  -0.1184   0.0109   0.4984
   9.250   1.4833   0.02662   0.01868  -0.1140   0.0104   0.5012
   9.750   1.4832   0.02984   0.02219  -0.1065   0.0099   0.5079
  10.000   1.4865   0.03134   0.02381  -0.1037   0.0098   0.5120
  10.250   1.4879   0.03309   0.02570  -0.1009   0.0096   0.5159
  10.500   1.4878   0.03510   0.02785  -0.0984   0.0095   0.5203
  10.750   1.4863   0.03743   0.03030  -0.0963   0.0094   0.5250
  11.000   1.4836   0.04008   0.03309  -0.0945   0.0093   0.5300
  11.250   1.4806   0.04298   0.03614  -0.0932   0.0091   0.5359
  11.500   1.4769   0.04619   0.03949  -0.0922   0.0091   0.5427
  11.750   1.4729   0.04957   0.04302  -0.0916   0.0090   0.5512
  12.000   1.4689   0.05306   0.04666  -0.0911   0.0090   0.5628
  12.250   1.4651   0.05656   0.05033  -0.0906   0.0089   0.5844
  12.500   1.4602   0.05937   0.05378  -0.0897   0.0089   1.0000
  12.750   1.4568   0.06280   0.05730  -0.0890   0.0089   1.0000
  13.000   1.4543   0.06608   0.06068  -0.0882   0.0090   1.0000
  13.250   1.4530   0.06914   0.06382  -0.0872   0.0091   1.0000
  13.500   1.4533   0.07202   0.06679  -0.0860   0.0092   1.0000
  13.750   1.4545   0.07486   0.06971  -0.0850   0.0092   1.0000
  14.000   1.4545   0.07801   0.07297  -0.0846   0.0091   1.0000
  14.250   1.4542   0.08127   0.07635  -0.0842   0.0090   1.0000
  14.500   1.4539   0.08456   0.07975  -0.0839   0.0090   1.0000
  14.750   1.4567   0.08725   0.08256  -0.0821   0.0094   1.0000
  15.000   1.2217   0.09242   0.08812  -0.0631   0.0104   1.0000
  15.250   1.2126   0.09505   0.09086  -0.0628   0.0104   1.0000
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