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GOE 165 (MVA MK.11) AIRFOIL (goe165-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 165 (MVA MK.11) AIRFOIL (goe165-il)
Reynolds number: 1,000,000
Max Cl/Cd: 85.7 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe165-il-1000000-n5.txt
Download as CSV file: xf-goe165-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2095   0.08832   0.08669  -0.0645   0.9806   0.0035
  -9.000  -0.2056   0.08379   0.08218  -0.0670   0.9753   0.0035
  -8.750  -0.2074   0.07965   0.07806  -0.0680   0.9637   0.0035
  -8.500  -0.1986   0.07351   0.07191  -0.0737   0.9441   0.0036
  -8.250  -0.1718   0.06061   0.05892  -0.0921   0.9172   0.0035
  -8.000  -0.1795   0.03222   0.02979  -0.1349   0.8602   0.0033
  -7.750  -0.1461   0.02484   0.02152  -0.1498   0.7687   0.0034
  -7.500  -0.1213   0.02242   0.01859  -0.1529   0.7181   0.0035
  -7.250  -0.0939   0.02017   0.01597  -0.1553   0.6959   0.0037
  -7.000  -0.0659   0.01800   0.01345  -0.1572   0.6808   0.0038
  -6.750  -0.0379   0.01609   0.01120  -0.1584   0.6686   0.0038
  -6.250   0.0183   0.01362   0.00828  -0.1597   0.6487   0.0040
  -6.000   0.0466   0.01282   0.00732  -0.1602   0.6408   0.0042
  -5.750   0.0753   0.01220   0.00655  -0.1606   0.6336   0.0044
  -5.250   0.1332   0.01104   0.00515  -0.1615   0.6217   0.0049
  -5.000   0.1619   0.01066   0.00469  -0.1618   0.6151   0.0052
  -4.750   0.1905   0.01038   0.00433  -0.1621   0.6082   0.0054
  -4.500   0.2193   0.01010   0.00397  -0.1623   0.6012   0.0058
  -4.250   0.2478   0.00990   0.00369  -0.1625   0.5954   0.0064
  -4.000   0.2765   0.00971   0.00344  -0.1626   0.5870   0.0069
  -3.750   0.3051   0.00946   0.00306  -0.1627   0.5744   0.0074
  -3.500   0.3335   0.00925   0.00274  -0.1628   0.5596   0.0083
  -3.250   0.3614   0.00917   0.00253  -0.1628   0.5379   0.0092
  -3.000   0.3867   0.00935   0.00240  -0.1623   0.4730   0.0103
  -2.750   0.4115   0.00967   0.00238  -0.1617   0.4092   0.0117
  -2.000   0.4944   0.00973   0.00220  -0.1614   0.3584   0.0440
  -1.750   0.5219   0.00979   0.00216  -0.1613   0.3439   0.0489
  -1.500   0.5494   0.00986   0.00214  -0.1612   0.3302   0.0528
  -1.250   0.5771   0.00991   0.00213  -0.1611   0.3212   0.0570
  -1.000   0.6052   0.00986   0.00211  -0.1611   0.3148   0.0891
  -0.750   0.6328   0.00990   0.00213  -0.1610   0.3073   0.1013
  -0.500   0.6605   0.00995   0.00214  -0.1609   0.2995   0.1071
  -0.250   0.6880   0.01001   0.00216  -0.1608   0.2925   0.1134
   0.000   0.7160   0.00995   0.00215  -0.1609   0.2847   0.1558
   0.250   0.7436   0.00989   0.00217  -0.1610   0.2763   0.2127
   0.500   0.7712   0.00988   0.00221  -0.1609   0.2688   0.2416
   0.750   0.7986   0.00989   0.00227  -0.1609   0.2615   0.2809
   1.000   0.8259   0.00993   0.00237  -0.1608   0.2535   0.3165
   1.250   0.8526   0.01008   0.00249  -0.1606   0.2410   0.3328
   1.500   0.8784   0.01033   0.00263  -0.1602   0.2208   0.3385
   1.750   0.8971   0.01133   0.00317  -0.1586   0.1281   0.3469
   2.000   0.9220   0.01167   0.00344  -0.1580   0.1080   0.3547
   2.250   0.9482   0.01186   0.00361  -0.1577   0.1012   0.3601
   2.500   0.9741   0.01208   0.00379  -0.1573   0.0936   0.3642
   2.750   0.9985   0.01247   0.00406  -0.1566   0.0642   0.3676
   3.000   1.0240   0.01271   0.00429  -0.1562   0.0561   0.3714
   3.250   1.0501   0.01289   0.00448  -0.1558   0.0523   0.3750
   3.500   1.0762   0.01307   0.00467  -0.1554   0.0512   0.3775
   3.750   1.1019   0.01328   0.00488  -0.1550   0.0492   0.3795
   4.000   1.1273   0.01350   0.00512  -0.1546   0.0471   0.3820
   4.250   1.1527   0.01372   0.00538  -0.1541   0.0448   0.3849
   4.500   1.1781   0.01393   0.00561  -0.1536   0.0429   0.3877
   4.750   1.2035   0.01412   0.00582  -0.1532   0.0418   0.3900
   5.000   1.2286   0.01434   0.00604  -0.1527   0.0391   0.3921
   5.250   1.2530   0.01462   0.00631  -0.1521   0.0347   0.3945
   5.500   1.2754   0.01509   0.00669  -0.1512   0.0139   0.3974
   5.750   1.2995   0.01537   0.00703  -0.1505   0.0105   0.4007
   6.000   1.3229   0.01571   0.00742  -0.1497   0.0084   0.4029
   6.250   1.3461   0.01606   0.00781  -0.1489   0.0070   0.4047
   6.500   1.3692   0.01639   0.00821  -0.1480   0.0061   0.4066
   6.750   1.3915   0.01679   0.00863  -0.1471   0.0053   0.4084
   7.000   1.4136   0.01717   0.00906  -0.1461   0.0047   0.4100
   7.250   1.4356   0.01755   0.00948  -0.1451   0.0042   0.4123
   7.500   1.4567   0.01796   0.00994  -0.1440   0.0038   0.4147
   7.750   1.4765   0.01847   0.01050  -0.1426   0.0034   0.4170
   8.000   1.4956   0.01901   0.01111  -0.1411   0.0032   0.4192
   8.250   1.5144   0.01953   0.01172  -0.1396   0.0030   0.4215
   8.500   1.5320   0.02009   0.01234  -0.1379   0.0028   0.4236
   8.750   1.5470   0.02066   0.01298  -0.1357   0.0026   0.4254
   9.000   1.5608   0.02125   0.01363  -0.1333   0.0025   0.4278
   9.250   1.5751   0.02186   0.01431  -0.1311   0.0023   0.4303
   9.500   1.5878   0.02256   0.01508  -0.1287   0.0022   0.4328
   9.750   1.5961   0.02354   0.01614  -0.1257   0.0020   0.4353
  10.000   1.6069   0.02436   0.01705  -0.1231   0.0019   0.4379
  10.250   1.6158   0.02531   0.01809  -0.1204   0.0019   0.4401
  10.500   1.6228   0.02639   0.01929  -0.1175   0.0018   0.4428
  10.750   1.6290   0.02757   0.02058  -0.1147   0.0017   0.4458
  11.000   1.6329   0.02897   0.02208  -0.1118   0.0017   0.4490
  11.250   1.6361   0.03049   0.02372  -0.1091   0.0016   0.4521
  11.500   1.6383   0.03221   0.02554  -0.1066   0.0016   0.4549
  11.750   1.6384   0.03423   0.02767  -0.1043   0.0015   0.4577
  12.000   1.6390   0.03635   0.02991  -0.1024   0.0015   0.4608
  12.250   1.6383   0.03880   0.03247  -0.1008   0.0014   0.4640
  12.500   1.6370   0.04148   0.03527  -0.0996   0.0014   0.4672
  12.750   1.6338   0.04460   0.03850  -0.0987   0.0014   0.4701
  13.000   1.6301   0.04799   0.04201  -0.0983   0.0013   0.4733
  13.250   1.6241   0.05181   0.04597  -0.0981   0.0013   0.4766
  13.500   1.6184   0.05566   0.04993  -0.0980   0.0013   0.4802
  13.750   1.6094   0.06006   0.05446  -0.0982   0.0013   0.4834
  14.000   1.5995   0.06468   0.05920  -0.0985   0.0013   0.4864
  14.250   1.5883   0.06957   0.06422  -0.0990   0.0012   0.4899
  14.500   1.5756   0.07485   0.06961  -0.0998   0.0012   0.4934
  14.750   1.5597   0.08083   0.07574  -0.1010   0.0012   0.4964
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