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GOE 165 (MVA MK.11) AIRFOIL (goe165-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 165 (MVA MK.11) AIRFOIL (goe165-il)
Reynolds number: 200,000
Max Cl/Cd: 66.64 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe165-il-200000-n5.txt
Download as CSV file: xf-goe165-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2997   0.10858   0.10532  -0.0346   1.0000   0.0264
  -9.000  -0.3040   0.10509   0.10190  -0.0357   1.0000   0.0266
  -8.750  -0.3083   0.10175   0.09863  -0.0363   1.0000   0.0267
  -8.500  -0.3125   0.09862   0.09556  -0.0363   1.0000   0.0268
  -8.250  -0.3031   0.09573   0.09270  -0.0351   0.9991   0.0276
  -8.000  -0.2863   0.09250   0.08947  -0.0378   0.9965   0.0284
  -7.750  -0.2712   0.08857   0.08554  -0.0418   0.9929   0.0292
  -7.500  -0.2617   0.07976   0.07673  -0.0492   0.9871   0.0173
  -7.250  -0.2524   0.07495   0.07195  -0.0537   0.9794   0.0160
  -7.000  -0.2381   0.06817   0.06519  -0.0615   0.9696   0.0149
  -6.750  -0.2255   0.05658   0.05357  -0.0755   0.9571   0.0136
  -6.250  -0.1312   0.03194   0.02736  -0.1220   0.9307   0.0112
  -6.000  -0.0941   0.02841   0.02337  -0.1270   0.9196   0.0112
  -5.750  -0.0526   0.02497   0.01946  -0.1319   0.9111   0.0112
  -5.500  -0.0133   0.02188   0.01593  -0.1356   0.9009   0.0116
  -5.250   0.0270   0.01982   0.01367  -0.1391   0.8896   0.0129
  -5.000   0.0719   0.01821   0.01184  -0.1429   0.8772   0.0139
  -4.750   0.1188   0.01671   0.01014  -0.1469   0.8613   0.0144
  -4.500   0.1669   0.01549   0.00871  -0.1512   0.8396   0.0151
  -4.250   0.2119   0.01455   0.00750  -0.1549   0.8116   0.0160
  -4.000   0.2506   0.01397   0.00661  -0.1572   0.7833   0.0178
  -3.750   0.2849   0.01343   0.00570  -0.1586   0.7586   0.0203
  -3.500   0.3158   0.01314   0.00514  -0.1591   0.7381   0.0234
  -3.250   0.3455   0.01291   0.00480  -0.1594   0.7215   0.0407
  -3.000   0.3746   0.01268   0.00441  -0.1597   0.7067   0.0631
  -2.750   0.4043   0.01197   0.00399  -0.1607   0.6938   0.2030
  -2.500   0.4322   0.01184   0.00406  -0.1608   0.6813   0.2854
  -2.250   0.4595   0.01201   0.00417  -0.1605   0.6690   0.3173
  -1.750   0.5141   0.01231   0.00423  -0.1598   0.6465   0.3450
  -1.500   0.5415   0.01240   0.00418  -0.1596   0.6356   0.3519
  -1.250   0.5685   0.01254   0.00422  -0.1592   0.6249   0.3574
  -1.000   0.5956   0.01264   0.00420  -0.1589   0.6133   0.3643
  -0.750   0.6223   0.01279   0.00430  -0.1585   0.6008   0.3711
  -0.500   0.6489   0.01297   0.00439  -0.1581   0.5862   0.3815
  -0.250   0.6747   0.01318   0.00456  -0.1574   0.5683   0.3894
   0.000   0.7007   0.01330   0.00455  -0.1569   0.5441   0.3955
   0.250   0.7250   0.01347   0.00457  -0.1561   0.5051   0.3978
   0.500   0.7471   0.01380   0.00461  -0.1549   0.4586   0.4004
   0.750   0.7702   0.01415   0.00474  -0.1539   0.4290   0.4036
   1.000   0.7942   0.01448   0.00489  -0.1532   0.4076   0.4077
   1.250   0.8184   0.01482   0.00507  -0.1525   0.3898   0.4121
   1.500   0.8428   0.01514   0.00532  -0.1518   0.3744   0.4166
   1.750   0.8676   0.01543   0.00552  -0.1512   0.3610   0.4222
   2.000   0.8928   0.01568   0.00569  -0.1507   0.3506   0.4266
   2.250   0.9181   0.01589   0.00590  -0.1502   0.3424   0.4296
   2.500   0.9435   0.01609   0.00609  -0.1498   0.3356   0.4331
   2.750   0.9690   0.01630   0.00626  -0.1493   0.3279   0.4366
   3.000   0.9944   0.01650   0.00644  -0.1489   0.3202   0.4395
   3.250   1.0197   0.01668   0.00662  -0.1484   0.3127   0.4416
   3.500   1.0447   0.01688   0.00683  -0.1479   0.3063   0.4434
   3.750   1.0701   0.01705   0.00705  -0.1475   0.2993   0.4457
   4.000   1.0946   0.01729   0.00729  -0.1469   0.2932   0.4484
   4.250   1.1201   0.01745   0.00751  -0.1465   0.2878   0.4513
   4.500   1.1450   0.01765   0.00776  -0.1460   0.2821   0.4540
   4.750   1.1695   0.01787   0.00801  -0.1454   0.2762   0.4563
   5.000   1.1943   0.01805   0.00828  -0.1449   0.2694   0.4584
   5.250   1.2182   0.01829   0.00855  -0.1442   0.2594   0.4608
   5.500   1.2408   0.01862   0.00884  -0.1434   0.2365   0.4635
   5.750   1.2575   0.01946   0.00931  -0.1418   0.1747   0.4664
   6.000   1.2666   0.02116   0.01050  -0.1391   0.1076   0.4691
   6.250   1.2825   0.02215   0.01134  -0.1373   0.0621   0.4717
   6.500   1.3004   0.02288   0.01209  -0.1358   0.0530   0.4743
   6.750   1.3202   0.02340   0.01278  -0.1344   0.0470   0.4772
   7.000   1.3393   0.02395   0.01343  -0.1330   0.0398   0.4803
   7.250   1.3547   0.02478   0.01421  -0.1311   0.0167   0.4834
   7.500   1.3702   0.02550   0.01508  -0.1290   0.0146   0.4864
   7.750   1.3832   0.02627   0.01603  -0.1266   0.0130   0.4892
   8.000   1.3946   0.02721   0.01716  -0.1239   0.0113   0.4924
   8.250   1.4069   0.02809   0.01821  -0.1215   0.0106   0.4963
   8.500   1.4176   0.02909   0.01937  -0.1190   0.0102   0.5002
   8.750   1.4263   0.03021   0.02069  -0.1163   0.0098   0.5038
   9.000   1.4328   0.03149   0.02221  -0.1135   0.0094   0.5078
   9.250   1.4371   0.03298   0.02388  -0.1106   0.0090   0.5120
   9.500   1.4389   0.03470   0.02579  -0.1078   0.0086   0.5158
   9.750   1.4374   0.03678   0.02805  -0.1050   0.0082   0.5195
  10.000   1.4319   0.03936   0.03081  -0.1024   0.0079   0.5233
  10.250   1.4222   0.04259   0.03421  -0.1002   0.0076   0.5271
  10.500   1.4075   0.04669   0.03848  -0.0986   0.0074   0.5303
  10.750   1.4064   0.04965   0.04161  -0.0978   0.0073   0.5355
  11.000   1.4016   0.05323   0.04535  -0.0974   0.0071   0.5410
  11.250   1.3955   0.05709   0.04938  -0.0972   0.0070   0.5472
  11.500   1.3889   0.06112   0.05357  -0.0972   0.0070   0.5549
  11.750   1.3821   0.06526   0.05786  -0.0972   0.0069   0.5646
  12.000   1.3751   0.06945   0.06222  -0.0974   0.0068   0.5794
  12.250   1.3694   0.07354   0.06658  -0.0977   0.0067   0.6405
  12.500   1.3601   0.07707   0.07052  -0.0971   0.0067   1.0000
  12.750   1.3553   0.08107   0.07461  -0.0972   0.0066   1.0000
  13.000   1.3520   0.08486   0.07849  -0.0973   0.0065   1.0000
  13.250   1.3502   0.08842   0.08213  -0.0972   0.0064   1.0000
  13.500   1.3499   0.09174   0.08552  -0.0970   0.0063   1.0000
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