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GOE 165 (MVA MK.11) AIRFOIL (goe165-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 165 (MVA MK.11) AIRFOIL (goe165-il)
Reynolds number: 100,000
Max Cl/Cd: 54.36 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe165-il-100000.txt
Download as CSV file: xf-goe165-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2979   0.10664   0.10212  -0.0305   1.0000   0.1075
  -8.250  -0.3214   0.10582   0.10145  -0.0324   1.0000   0.1113
  -8.000  -0.3522   0.10548   0.10130  -0.0327   1.0000   0.1120
  -7.750  -0.3026   0.09911   0.09482  -0.0288   1.0000   0.1178
  -7.500  -0.3093   0.09730   0.09311  -0.0279   1.0000   0.1229
  -7.250  -0.3459   0.09722   0.09324  -0.0273   1.0000   0.1257
  -7.000  -0.3299   0.09338   0.08942  -0.0243   1.0000   0.1296
  -6.750  -0.3296   0.09167   0.08776  -0.0218   1.0000   0.1349
  -6.250  -0.3478   0.08804   0.08436  -0.0190   1.0000   0.1448
  -5.750  -0.3747   0.08534   0.08192  -0.0179   1.0000   0.1561
  -5.500  -0.3667   0.08311   0.07974  -0.0216   0.9969   0.1690
  -5.250  -0.2481   0.04046   0.03520  -0.0947   0.9936   0.0717
  -5.000  -0.1933   0.03477   0.02887  -0.1030   0.9897   0.0659
  -4.750  -0.1321   0.03123   0.02432  -0.1100   0.9852   0.0598
  -4.500  -0.0805   0.02824   0.02093  -0.1147   0.9784   0.0579
  -4.250  -0.0264   0.02608   0.01849  -0.1192   0.9728   0.0579
  -4.000   0.0192   0.02459   0.01692  -0.1220   0.9634   0.0598
  -3.750   0.0640   0.02327   0.01576  -0.1250   0.9548   0.0676
  -3.500   0.1162   0.02208   0.01453  -0.1296   0.9477   0.0788
  -3.250   0.1657   0.02090   0.01438  -0.1342   0.9375   0.3376
  -3.000   0.1967   0.02303   0.01652  -0.1322   0.9234   0.3772
  -2.750   0.2286   0.02419   0.01769  -0.1309   0.9113   0.4011
  -2.500   0.2633   0.02496   0.01844  -0.1305   0.9022   0.4274
  -2.250   0.3020   0.02452   0.01790  -0.1318   0.8941   0.4363
  -2.000   0.3424   0.02386   0.01707  -0.1341   0.8847   0.4454
  -1.750   0.3889   0.02314   0.01617  -0.1373   0.8777   0.4577
  -1.500   0.4238   0.02277   0.01572  -0.1381   0.8657   0.4717
  -1.250   0.4602   0.02231   0.01518  -0.1392   0.8536   0.4859
  -1.000   0.4982   0.02176   0.01451  -0.1408   0.8408   0.4975
  -0.750   0.5345   0.02112   0.01378  -0.1420   0.8267   0.5044
  -0.500   0.5733   0.02064   0.01309  -0.1441   0.8107   0.5129
  -0.250   0.6063   0.02013   0.01252  -0.1446   0.7934   0.5192
   0.000   0.6431   0.01980   0.01195  -0.1461   0.7747   0.5273
   0.250   0.6712   0.01953   0.01159  -0.1457   0.7529   0.5329
   0.500   0.7034   0.01940   0.01123  -0.1462   0.7306   0.5400
   0.750   0.7302   0.01931   0.01103  -0.1457   0.7052   0.5457
   1.000   0.7573   0.01935   0.01088  -0.1452   0.6778   0.5525
   1.250   0.7833   0.01941   0.01076  -0.1445   0.6482   0.5585
   1.500   0.8080   0.01952   0.01072  -0.1436   0.6183   0.5647
   1.750   0.8337   0.01969   0.01068  -0.1431   0.5904   0.5707
   2.000   0.8583   0.01975   0.01061  -0.1423   0.5667   0.5759
   2.250   0.8841   0.01990   0.01065  -0.1419   0.5460   0.5814
   2.500   0.9107   0.02006   0.01072  -0.1417   0.5290   0.5861
   2.750   0.9365   0.02017   0.01076  -0.1413   0.5141   0.5909
   3.000   0.9626   0.02034   0.01083  -0.1410   0.4998   0.5959
   3.250   0.9887   0.02054   0.01091  -0.1407   0.4862   0.6002
   3.500   1.0143   0.02073   0.01105  -0.1403   0.4738   0.6047
   3.750   1.0408   0.02102   0.01121  -0.1401   0.4626   0.6100
   4.000   1.0674   0.02135   0.01153  -0.1400   0.4522   0.6148
   4.250   1.0945   0.02171   0.01189  -0.1400   0.4443   0.6194
   4.500   1.1217   0.02211   0.01227  -0.1400   0.4364   0.6247
   4.750   1.1482   0.02252   0.01273  -0.1398   0.4287   0.6305
   5.000   1.1751   0.02292   0.01310  -0.1397   0.4209   0.6369
   5.250   1.2005   0.02337   0.01364  -0.1394   0.4133   0.6434
   5.500   1.2272   0.02378   0.01410  -0.1393   0.4061   0.6501
   5.750   1.2525   0.02426   0.01472  -0.1390   0.3997   0.6580
   6.000   1.2777   0.02466   0.01527  -0.1386   0.3932   0.6677
   6.250   1.3026   0.02510   0.01583  -0.1381   0.3861   0.6798
   6.500   1.3258   0.02533   0.01615  -0.1373   0.3749   0.6962
   6.750   1.3440   0.02536   0.01649  -0.1356   0.3624   0.7279
   7.000   1.3620   0.02541   0.01687  -0.1337   0.3523   1.0000
   7.250   1.3847   0.02578   0.01721  -0.1328   0.3420   1.0000
   7.500   1.4028   0.02595   0.01738  -0.1312   0.3281   1.0000
   7.750   1.4204   0.02615   0.01769  -0.1294   0.3156   1.0000
   8.000   1.4384   0.02648   0.01822  -0.1277   0.3054   1.0000
   8.250   1.4571   0.02683   0.01868  -0.1261   0.2959   1.0000
   8.500   1.4732   0.02711   0.01905  -0.1241   0.2841   1.0000
   8.750   1.4839   0.02730   0.01944  -0.1211   0.2632   1.0000
   9.000   1.4970   0.02769   0.01994  -0.1187   0.2438   1.0000
   9.250   1.5089   0.02825   0.02063  -0.1160   0.2137   1.0000
   9.500   1.5012   0.02996   0.02179  -0.1110   0.1412   1.0000
   9.750   1.4875   0.03284   0.02425  -0.1058   0.0725   1.0000
  10.000   1.4698   0.03610   0.02723  -0.1008   0.0595   1.0000
  10.250   1.4551   0.03923   0.03046  -0.0965   0.0538   1.0000
  10.500   1.4464   0.04210   0.03357  -0.0935   0.0497   1.0000
  10.750   1.4344   0.04550   0.03719  -0.0910   0.0470   1.0000
  11.000   1.4197   0.04953   0.04144  -0.0894   0.0452   1.0000
  11.250   1.4025   0.05430   0.04641  -0.0888   0.0441   1.0000
  11.500   1.3840   0.05969   0.05198  -0.0890   0.0433   1.0000
  11.750   1.3736   0.06437   0.05686  -0.0894   0.0420   1.0000
  12.000   1.3622   0.06936   0.06204  -0.0901   0.0408   1.0000
  12.250   1.3496   0.07462   0.06748  -0.0910   0.0398   1.0000
  12.500   1.3374   0.07992   0.07292  -0.0920   0.0388   1.0000
  12.750   1.3272   0.08494   0.07808  -0.0929   0.0377   1.0000
  13.000   1.3204   0.08930   0.08252  -0.0933   0.0368   1.0000
  13.250   1.3185   0.09259   0.08584  -0.0930   0.0357   1.0000
  13.500   1.3245   0.09395   0.08713  -0.0910   0.0344   1.0000
  13.750   1.3532   0.09101   0.08395  -0.0848   0.0330   1.0000
  14.000   1.3782   0.09029   0.08324  -0.0807   0.0323   1.0000
  14.250   1.4024   0.09043   0.08350  -0.0772   0.0318   1.0000
  14.500   1.4142   0.09258   0.08581  -0.0756   0.0313   1.0000
  14.750   1.4180   0.09578   0.08922  -0.0752   0.0308   1.0000
  15.000   1.4181   0.09950   0.09316  -0.0753   0.0303   1.0000
  15.250   1.4158   0.10361   0.09748  -0.0758   0.0300   1.0000
  15.500   1.4109   0.10815   0.10225  -0.0768   0.0298   1.0000
  15.750   1.4036   0.11318   0.10752  -0.0784   0.0298   1.0000
  16.000   1.3941   0.11872   0.11331  -0.0805   0.0301   1.0000
  16.250   1.3826   0.12474   0.11956  -0.0834   0.0304   1.0000
  16.500   1.3695   0.13126   0.12632  -0.0869   0.0307   1.0000
  16.750   1.3551   0.13826   0.13354  -0.0911   0.0310   1.0000
  17.000   1.3399   0.14574   0.14122  -0.0960   0.0314   1.0000
  17.250   1.3242   0.15368   0.14935  -0.1014   0.0317   1.0000
  17.500   1.3081   0.16210   0.15794  -0.1074   0.0321   1.0000
  17.750   1.2927   0.17080   0.16678  -0.1135   0.0325   1.0000
  18.000   1.2794   0.17939   0.17548  -0.1194   0.0330   1.0000
  18.250   1.2736   0.18642   0.18259  -0.1234   0.0336   1.0000
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