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GOE 164 (MVA MK.10) AIRFOIL (goe164-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 164 (MVA MK.10) AIRFOIL (goe164-il)
Reynolds number: 200,000
Max Cl/Cd: 81.39 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe164-il-200000.txt
Download as CSV file: xf-goe164-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 164 (MVA MK.10) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2995   0.11116   0.10785  -0.0281   1.0000   0.0379
  -8.250  -0.3062   0.10969   0.10645  -0.0275   1.0000   0.0381
  -8.000  -0.3142   0.10819   0.10502  -0.0262   1.0000   0.0382
  -7.750  -0.3208   0.10646   0.10337  -0.0249   1.0000   0.0382
  -7.500  -0.3050   0.09965   0.09656  -0.0226   1.0000   0.0395
  -7.250  -0.3041   0.09751   0.09447  -0.0203   1.0000   0.0401
  -7.000  -0.3108   0.09608   0.09311  -0.0176   1.0000   0.0407
  -6.750  -0.3198   0.09486   0.09198  -0.0151   1.0000   0.0412
  -6.500  -0.3033   0.09160   0.08873  -0.0189   0.9967   0.0428
  -6.250  -0.2707   0.08683   0.08394  -0.0276   0.9904   0.0455
  -6.000  -0.2099   0.08036   0.07740  -0.0526   0.9794   0.0491
  -5.750  -0.1908   0.07419   0.07123  -0.0553   0.9748   0.0504
  -5.500  -0.1624   0.07109   0.06811  -0.0570   0.9716   0.0526
  -5.250  -0.1298   0.06730   0.06429  -0.0630   0.9627   0.0566
  -5.000  -0.0786   0.06038   0.05728  -0.0788   0.9548   0.0637
  -4.750  -0.0484   0.05782   0.05470  -0.0810   0.9485   0.0678
  -4.500   0.0059   0.05132   0.04806  -0.0953   0.9408   0.0768
  -4.250   0.1052   0.02487   0.02005  -0.1290   0.9389   0.0432
  -4.000   0.1512   0.02136   0.01581  -0.1337   0.9345   0.0453
  -3.750   0.1971   0.01901   0.01288  -0.1373   0.9315   0.0473
  -3.500   0.2313   0.01772   0.01122  -0.1381   0.9213   0.0491
  -3.250   0.2736   0.01563   0.00901  -0.1411   0.9176   0.0560
  -3.000   0.3070   0.01464   0.00785  -0.1416   0.9064   0.0612
  -2.750   0.3439   0.01352   0.00671  -0.1431   0.8959   0.0726
  -2.500   0.3833   0.01260   0.00584  -0.1449   0.8853   0.0938
  -2.250   0.4232   0.01266   0.00600  -0.1466   0.8730   0.1622
  -2.000   0.4625   0.01296   0.00612  -0.1483   0.8586   0.1882
  -1.750   0.5002   0.01299   0.00604  -0.1499   0.8421   0.2038
  -1.500   0.5351   0.01301   0.00584  -0.1509   0.8246   0.2152
  -1.250   0.5663   0.01299   0.00575  -0.1513   0.8071   0.2263
  -1.000   0.5954   0.01298   0.00564  -0.1513   0.7900   0.2365
  -0.750   0.6237   0.01306   0.00550  -0.1510   0.7731   0.2444
  -0.500   0.6507   0.01287   0.00524  -0.1506   0.7563   0.2481
  -0.250   0.6773   0.01281   0.00507  -0.1500   0.7396   0.2521
   0.000   0.7035   0.01278   0.00492  -0.1494   0.7227   0.2568
   0.250   0.7295   0.01271   0.00478  -0.1488   0.7066   0.2620
   0.500   0.7554   0.01266   0.00471  -0.1481   0.6906   0.2675
   0.750   0.7813   0.01266   0.00462  -0.1475   0.6744   0.2733
   1.000   0.8069   0.01261   0.00456  -0.1468   0.6579   0.2792
   1.250   0.8324   0.01262   0.00453  -0.1461   0.6406   0.2867
   1.500   0.8576   0.01263   0.00453  -0.1454   0.6224   0.2954
   1.750   0.8826   0.01270   0.00453  -0.1446   0.6033   0.3064
   2.000   0.9071   0.01277   0.00457  -0.1437   0.5815   0.3191
   2.250   0.9311   0.01289   0.00463  -0.1428   0.5588   0.3354
   2.500   0.9550   0.01298   0.00475  -0.1418   0.5350   0.3602
   2.750   0.9783   0.01302   0.00484  -0.1409   0.5128   0.4195
   3.000   0.9986   0.01227   0.00491  -0.1390   0.4920   1.0000
   3.250   1.0228   0.01258   0.00504  -0.1382   0.4725   1.0000
   3.500   1.0470   0.01289   0.00524  -0.1374   0.4551   1.0000
   3.750   1.0712   0.01321   0.00543  -0.1366   0.4391   1.0000
   4.000   1.0955   0.01352   0.00565  -0.1359   0.4248   1.0000
   4.250   1.1199   0.01383   0.00590  -0.1352   0.4125   1.0000
   4.500   1.1443   0.01416   0.00618  -0.1345   0.4014   1.0000
   4.750   1.1683   0.01452   0.00646  -0.1338   0.3919   1.0000
   5.000   1.1928   0.01484   0.00677  -0.1331   0.3824   1.0000
   5.250   1.2170   0.01520   0.00710  -0.1324   0.3741   1.0000
   5.500   1.2410   0.01557   0.00747  -0.1317   0.3657   1.0000
   5.750   1.2651   0.01593   0.00784  -0.1310   0.3577   1.0000
   6.000   1.2887   0.01633   0.00822  -0.1303   0.3499   1.0000
   6.250   1.3125   0.01669   0.00865  -0.1295   0.3419   1.0000
   6.500   1.3356   0.01713   0.00907  -0.1287   0.3342   1.0000
   6.750   1.3590   0.01749   0.00952  -0.1279   0.3261   1.0000
   7.000   1.3815   0.01797   0.00998  -0.1270   0.3182   1.0000
   7.250   1.4035   0.01830   0.01044  -0.1260   0.3079   1.0000
   7.500   1.4244   0.01868   0.01087  -0.1248   0.2961   1.0000
   7.750   1.4444   0.01903   0.01127  -0.1235   0.2825   1.0000
   8.000   1.4644   0.01939   0.01168  -0.1221   0.2696   1.0000
   8.250   1.4842   0.01977   0.01213  -0.1208   0.2567   1.0000
   8.500   1.5036   0.02014   0.01255  -0.1194   0.2398   1.0000
   8.750   1.5219   0.02061   0.01305  -0.1179   0.2232   1.0000
   9.250   1.5474   0.02220   0.01446  -0.1133   0.1816   1.0000
   9.500   1.5554   0.02327   0.01548  -0.1102   0.1636   1.0000
   9.750   1.5647   0.02435   0.01651  -0.1074   0.1264   1.0000
  10.000   1.5529   0.02690   0.01856  -0.1020   0.0757   1.0000
  10.250   1.5525   0.02875   0.02035  -0.0982   0.0441   1.0000
  10.500   1.5502   0.03078   0.02226  -0.0945   0.0349   1.0000
  10.750   1.5522   0.03252   0.02416  -0.0915   0.0320   1.0000
  11.000   1.5513   0.03455   0.02635  -0.0886   0.0300   1.0000
  11.250   1.5469   0.03700   0.02895  -0.0858   0.0286   1.0000
  11.500   1.5389   0.03999   0.03211  -0.0834   0.0276   1.0000
  11.750   1.5286   0.04347   0.03576  -0.0815   0.0268   1.0000
  12.000   1.5242   0.04660   0.03906  -0.0803   0.0263   1.0000
  12.250   1.5183   0.05006   0.04270  -0.0794   0.0256   1.0000
  12.500   1.5115   0.05377   0.04656  -0.0788   0.0249   1.0000
  12.750   1.5037   0.05772   0.05066  -0.0784   0.0242   1.0000
  13.000   1.4958   0.06181   0.05488  -0.0782   0.0236   1.0000
  13.250   1.4875   0.06604   0.05924  -0.0782   0.0232   1.0000
  13.500   1.4798   0.07022   0.06353  -0.0782   0.0228   1.0000
  13.750   1.4729   0.07432   0.06773  -0.0781   0.0224   1.0000
  14.000   1.4674   0.07819   0.07167  -0.0780   0.0220   1.0000
  14.250   1.4635   0.08174   0.07529  -0.0775   0.0217   1.0000
  14.500   1.4626   0.08469   0.07828  -0.0765   0.0213   1.0000
  14.750   1.4667   0.08669   0.08030  -0.0744   0.0209   1.0000
  15.000   1.4791   0.08749   0.08113  -0.0705   0.0204   1.0000
  15.250   1.4798   0.09073   0.08453  -0.0702   0.0202   1.0000
  15.500   1.4765   0.09468   0.08869  -0.0709   0.0200   1.0000
  15.750   1.4726   0.09881   0.09302  -0.0717   0.0198   1.0000
  16.000   1.4678   0.10318   0.09759  -0.0729   0.0195   1.0000
  16.250   1.4627   0.10765   0.10226  -0.0741   0.0192   1.0000
  16.500   1.4567   0.11236   0.10717  -0.0755   0.0191   1.0000
  16.750   1.4497   0.11735   0.11236  -0.0771   0.0191   1.0000
  17.000   1.4413   0.12276   0.11798  -0.0793   0.0191   1.0000
  17.250   1.4316   0.12857   0.12399  -0.0819   0.0192   1.0000
  17.500   1.4207   0.13481   0.13044  -0.0852   0.0193   1.0000
  17.750   1.4087   0.14147   0.13730  -0.0890   0.0194   1.0000
  18.000   1.3959   0.14852   0.14454  -0.0932   0.0195   1.0000
  18.250   1.3824   0.15602   0.15222  -0.0980   0.0197   1.0000
  18.500   1.3683   0.16394   0.16032  -0.1033   0.0199   1.0000
  18.750   1.3541   0.17217   0.16870  -0.1088   0.0201   1.0000
  19.000   1.3451   0.17923   0.17589  -0.1131   0.0205   1.0000
  19.250   1.3350   0.18755   0.18436  -0.1197   0.0207   1.0000
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