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GOE 165 (MVA MK.11) AIRFOIL (goe165-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 165 (MVA MK.11) AIRFOIL (goe165-il)
Reynolds number: 50,000
Max Cl/Cd: 39.9 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe165-il-50000-n5.txt
Download as CSV file: xf-goe165-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2926   0.10944   0.10302  -0.0369   1.0000   0.0515
  -8.500  -0.2897   0.10637   0.10003  -0.0363   1.0000   0.0490
  -8.000  -0.3124   0.09863   0.09257  -0.0387   1.0000   0.0426
  -7.750  -0.3103   0.09627   0.09029  -0.0368   1.0000   0.0419
  -7.500  -0.3143   0.09389   0.08802  -0.0354   1.0000   0.0413
  -7.250  -0.3212   0.09149   0.08575  -0.0340   1.0000   0.0407
  -7.000  -0.3270   0.08872   0.08310  -0.0334   1.0000   0.0400
  -6.750  -0.3327   0.08570   0.08022  -0.0334   1.0000   0.0394
  -6.500  -0.3383   0.08239   0.07703  -0.0341   1.0000   0.0388
  -6.250  -0.3431   0.07861   0.07337  -0.0356   1.0000   0.0382
  -6.000  -0.3460   0.07383   0.06867  -0.0391   1.0000   0.0373
  -5.750  -0.2953   0.05544   0.04946  -0.0740   0.9930   0.0342
  -5.500  -0.2482   0.04885   0.04241  -0.0864   0.9870   0.0349
  -5.250  -0.2046   0.04436   0.03752  -0.0946   0.9803   0.0365
  -5.000  -0.1577   0.04024   0.03279  -0.1022   0.9742   0.0377
  -4.750  -0.1128   0.03713   0.02908  -0.1073   0.9685   0.0384
  -4.500  -0.0743   0.03499   0.02653  -0.1101   0.9607   0.0395
  -4.250  -0.0355   0.03340   0.02459  -0.1122   0.9540   0.0412
  -4.000  -0.0005   0.03205   0.02312  -0.1140   0.9456   0.0452
  -3.750   0.0366   0.03095   0.02186  -0.1162   0.9375   0.0506
  -3.500   0.0803   0.02963   0.02037  -0.1199   0.9296   0.0565
  -3.250   0.1295   0.02768   0.01846  -0.1258   0.9195   0.0756
  -3.000   0.1748   0.02720   0.01912  -0.1293   0.9074   0.3178
  -2.750   0.2014   0.02959   0.02136  -0.1260   0.8909   0.3874
  -2.500   0.2372   0.02981   0.02127  -0.1262   0.8764   0.4126
  -2.250   0.2730   0.02955   0.02076  -0.1267   0.8628   0.4292
  -2.000   0.3131   0.02897   0.01985  -0.1287   0.8505   0.4419
  -1.750   0.3515   0.02834   0.01897  -0.1305   0.8390   0.4483
  -1.500   0.3890   0.02780   0.01809  -0.1327   0.8260   0.4559
  -1.250   0.4221   0.02735   0.01748  -0.1334   0.8129   0.4615
  -1.000   0.4591   0.02691   0.01677  -0.1352   0.7995   0.4696
  -0.750   0.4933   0.02649   0.01619  -0.1361   0.7860   0.4755
  -0.500   0.5292   0.02612   0.01561  -0.1375   0.7718   0.4833
  -0.250   0.5631   0.02577   0.01510  -0.1383   0.7568   0.4896
   0.000   0.5971   0.02551   0.01465  -0.1392   0.7409   0.4973
   0.250   0.6299   0.02529   0.01428  -0.1398   0.7244   0.5038
   0.500   0.6622   0.02515   0.01397  -0.1404   0.7072   0.5109
   0.750   0.6939   0.02507   0.01370  -0.1408   0.6894   0.5173
   1.000   0.7230   0.02506   0.01355  -0.1408   0.6705   0.5234
   1.250   0.7514   0.02515   0.01350  -0.1408   0.6503   0.5298
   1.500   0.7787   0.02519   0.01344  -0.1405   0.6304   0.5348
   1.750   0.8063   0.02531   0.01343  -0.1403   0.6103   0.5407
   2.000   0.8315   0.02549   0.01354  -0.1398   0.5884   0.5460
   2.250   0.8571   0.02564   0.01362  -0.1393   0.5682   0.5509
   2.500   0.8832   0.02585   0.01376  -0.1389   0.5492   0.5562
   2.750   0.9086   0.02608   0.01395  -0.1386   0.5311   0.5612
   3.000   0.9343   0.02631   0.01413  -0.1382   0.5153   0.5665
   3.250   0.9606   0.02659   0.01436  -0.1379   0.5013   0.5720
   3.500   0.9870   0.02685   0.01456  -0.1377   0.4895   0.5768
   3.750   1.0133   0.02717   0.01488  -0.1375   0.4785   0.5823
   4.250   1.0674   0.02790   0.01563  -0.1373   0.4615   0.5945
   4.500   1.0933   0.02839   0.01620  -0.1372   0.4530   0.6010
   4.750   1.1209   0.02878   0.01664  -0.1372   0.4464   0.6074
   5.000   1.1458   0.02934   0.01736  -0.1369   0.4389   0.6146
   5.250   1.1727   0.02981   0.01794  -0.1368   0.4330   0.6229
   5.500   1.1982   0.03041   0.01871  -0.1366   0.4271   0.6326
   5.750   1.2226   0.03097   0.01952  -0.1362   0.4204   0.6434
   6.000   1.2475   0.03148   0.02020  -0.1358   0.4134   0.6567
   6.250   1.2689   0.03203   0.02105  -0.1349   0.4051   0.6756
   6.500   1.2888   0.03230   0.02170  -0.1334   0.3977   0.7659
   6.750   1.3093   0.03301   0.02259  -0.1324   0.3895   1.0000
   7.000   1.3328   0.03379   0.02352  -0.1318   0.3822   1.0000
   7.250   1.3530   0.03452   0.02436  -0.1307   0.3725   1.0000
   7.500   1.3673   0.03499   0.02484  -0.1285   0.3566   1.0000
   7.750   1.3788   0.03543   0.02527  -0.1258   0.3399   1.0000
   8.000   1.3891   0.03614   0.02615  -0.1232   0.3267   1.0000
   8.250   1.3993   0.03690   0.02708  -0.1207   0.3147   1.0000
   8.500   1.4085   0.03767   0.02800  -0.1181   0.3028   1.0000
   8.750   1.4119   0.03851   0.02898  -0.1147   0.2878   1.0000
   9.000   1.4104   0.03953   0.03015  -0.1108   0.2713   1.0000
   9.250   1.4123   0.04074   0.03164  -0.1077   0.2565   1.0000
   9.500   1.4133   0.04220   0.03331  -0.1048   0.2398   1.0000
   9.750   1.4146   0.04388   0.03521  -0.1023   0.2208   1.0000
  10.000   1.4152   0.04583   0.03733  -0.1001   0.1948   1.0000
  10.250   1.4068   0.04839   0.03967  -0.0976   0.1537   1.0000
  10.500   1.3894   0.05236   0.04331  -0.0957   0.1251   1.0000
  10.750   1.3761   0.05663   0.04756  -0.0947   0.0904   1.0000
  11.250   1.3320   0.06859   0.05946  -0.0954   0.0607   1.0000
  11.500   1.3123   0.07486   0.06584  -0.0965   0.0578   1.0000
  11.750   1.2930   0.08134   0.07247  -0.0980   0.0555   1.0000
  12.000   1.2741   0.08800   0.07927  -0.0997   0.0535   1.0000
  12.250   1.2585   0.09430   0.08574  -0.1014   0.0504   1.0000
  12.500   1.2450   0.10040   0.09204  -0.1032   0.0476   1.0000
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