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GOE 362 AIRFOIL (goe362-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 362 AIRFOIL (goe362-il)
Reynolds number: 200,000
Max Cl/Cd: 79.57 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe362-il-200000.txt
Download as CSV file: xf-goe362-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 362 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  -0.3290   0.10395   0.10042  -0.0250   1.0000   0.0316
  -8.250  -0.3294   0.10211   0.09865  -0.0264   1.0000   0.0318
  -8.000  -0.3300   0.10011   0.09671  -0.0268   1.0000   0.0319
  -7.750  -0.3290   0.09783   0.09449  -0.0281   1.0000   0.0319
  -7.500  -0.3273   0.09311   0.08984  -0.0278   1.0000   0.0323
  -7.250  -0.3200   0.08885   0.08558  -0.0242   1.0000   0.0331
  -7.000  -0.3149   0.08609   0.08286  -0.0230   1.0000   0.0338
  -6.750  -0.3124   0.08375   0.08057  -0.0224   1.0000   0.0345
  -6.500  -0.3113   0.08156   0.07843  -0.0222   1.0000   0.0351
  -6.250  -0.3110   0.07940   0.07633  -0.0218   1.0000   0.0360
  -6.000  -0.3113   0.07730   0.07428  -0.0216   1.0000   0.0369
  -5.750  -0.3116   0.07522   0.07225  -0.0216   1.0000   0.0376
  -5.500  -0.3109   0.07305   0.07012  -0.0220   1.0000   0.0387
  -5.250  -0.2678   0.06883   0.06580  -0.0366   0.9968   0.0418
  -5.000  -0.2187   0.06134   0.05819  -0.0498   0.9909   0.0429
  -4.750  -0.1949   0.05754   0.05442  -0.0509   0.9857   0.0446
  -4.500  -0.1562   0.05381   0.05062  -0.0567   0.9796   0.0486
  -4.250  -0.0912   0.04678   0.04328  -0.0720   0.9734   0.0557
  -4.000  -0.0574   0.04380   0.04030  -0.0751   0.9688   0.0587
  -3.750   0.0014   0.03833   0.03431  -0.0856   0.9615   0.0680
  -3.500   0.0359   0.03525   0.03130  -0.0887   0.9574   0.0708
  -3.250   0.0839   0.03137   0.02694  -0.0945   0.9506   0.0818
  -3.000   0.1314   0.02385   0.01859  -0.0984   0.9452   0.0535
  -2.750   0.1721   0.01907   0.01320  -0.1012   0.9404   0.0479
  -2.500   0.2066   0.01653   0.01010  -0.1019   0.9306   0.0482
  -2.250   0.2412   0.01543   0.00865  -0.1026   0.9210   0.0535
  -2.000   0.2755   0.01380   0.00681  -0.1033   0.9122   0.0581
  -1.750   0.3053   0.01331   0.00617  -0.1030   0.8990   0.0667
  -1.500   0.3338   0.01253   0.00539  -0.1026   0.8853   0.0765
  -1.250   0.3619   0.01209   0.00489  -0.1020   0.8709   0.0918
  -1.000   0.3890   0.01150   0.00432  -0.1013   0.8560   0.1142
  -0.750   0.4156   0.01102   0.00389  -0.1006   0.8406   0.1470
  -0.500   0.4422   0.01084   0.00370  -0.0999   0.8248   0.1804
  -0.250   0.4681   0.01062   0.00355  -0.0992   0.8079   0.2156
   0.000   0.4932   0.01021   0.00342  -0.0984   0.7908   0.2988
   0.250   0.5262   0.00862   0.00326  -0.0991   0.7741   1.0000
   0.500   0.5525   0.00873   0.00315  -0.0983   0.7564   1.0000
   0.750   0.5786   0.00886   0.00308  -0.0976   0.7386   1.0000
   1.000   0.6046   0.00900   0.00304  -0.0968   0.7200   1.0000
   1.250   0.6305   0.00914   0.00303  -0.0961   0.7003   1.0000
   1.500   0.6564   0.00932   0.00304  -0.0953   0.6810   1.0000
   1.750   0.6821   0.00951   0.00308  -0.0946   0.6609   1.0000
   2.000   0.7078   0.00971   0.00315  -0.0939   0.6404   1.0000
   2.250   0.7334   0.00994   0.00323  -0.0932   0.6210   1.0000
   2.500   0.7591   0.01016   0.00336  -0.0926   0.6012   1.0000
   2.750   0.7849   0.01039   0.00349  -0.0920   0.5822   1.0000
   3.000   0.8106   0.01063   0.00362  -0.0914   0.5646   1.0000
   3.250   0.8363   0.01088   0.00378  -0.0909   0.5482   1.0000
   3.500   0.8620   0.01113   0.00397  -0.0903   0.5327   1.0000
   3.750   0.8878   0.01139   0.00416  -0.0898   0.5180   1.0000
   4.000   0.9135   0.01165   0.00438  -0.0893   0.5038   1.0000
   4.250   0.9392   0.01193   0.00462  -0.0888   0.4904   1.0000
   4.500   0.9647   0.01222   0.00491  -0.0883   0.4769   1.0000
   4.750   0.9898   0.01252   0.00517  -0.0877   0.4621   1.0000
   5.000   1.0145   0.01284   0.00543  -0.0870   0.4462   1.0000
   5.250   1.0392   0.01317   0.00572  -0.0864   0.4307   1.0000
   5.500   1.0637   0.01347   0.00605  -0.0857   0.4150   1.0000
   5.750   1.0882   0.01378   0.00637  -0.0851   0.4002   1.0000
   6.000   1.1126   0.01408   0.00671  -0.0844   0.3856   1.0000
   6.250   1.1369   0.01436   0.00705  -0.0838   0.3709   1.0000
   6.500   1.1610   0.01463   0.00742  -0.0831   0.3552   1.0000
   6.750   1.1848   0.01489   0.00776  -0.0823   0.3368   1.0000
   7.000   1.2078   0.01520   0.00810  -0.0815   0.3161   1.0000
   7.250   1.2305   0.01553   0.00848  -0.0806   0.2912   1.0000
   7.500   1.2514   0.01604   0.00896  -0.0795   0.2579   1.0000
   7.750   1.2687   0.01697   0.00965  -0.0780   0.2009   1.0000
   8.000   1.2817   0.01850   0.01075  -0.0762   0.1389   1.0000
   8.250   1.2965   0.01982   0.01187  -0.0745   0.1112   1.0000
   8.500   1.3116   0.02105   0.01302  -0.0729   0.0962   1.0000
   8.750   1.3275   0.02214   0.01417  -0.0713   0.0853   1.0000
   9.000   1.3425   0.02328   0.01538  -0.0696   0.0754   1.0000
   9.250   1.3548   0.02462   0.01676  -0.0676   0.0661   1.0000
   9.500   1.3649   0.02609   0.01824  -0.0654   0.0558   1.0000
   9.750   1.3721   0.02773   0.01988  -0.0629   0.0462   1.0000
  10.000   1.3824   0.02895   0.02125  -0.0605   0.0398   1.0000
  10.250   1.3820   0.03108   0.02335  -0.0571   0.0361   1.0000
  10.500   1.3897   0.03253   0.02501  -0.0546   0.0332   1.0000
  10.750   1.3960   0.03398   0.02656  -0.0523   0.0305   1.0000
  11.000   1.3992   0.03581   0.02844  -0.0502   0.0284   1.0000
  11.250   1.4029   0.03866   0.03138  -0.0480   0.0269   1.0000
  11.500   1.4098   0.04072   0.03365  -0.0462   0.0258   1.0000
  11.750   1.4158   0.04306   0.03620  -0.0445   0.0248   1.0000
  12.000   1.4203   0.04556   0.03890  -0.0429   0.0238   1.0000
  12.250   1.4226   0.04819   0.04172  -0.0416   0.0230   1.0000
  12.500   1.4229   0.05074   0.04441  -0.0405   0.0222   1.0000
  12.750   1.4227   0.05348   0.04723  -0.0398   0.0212   1.0000
  13.000   1.4199   0.05752   0.05144  -0.0390   0.0206   1.0000
  13.250   1.4090   0.06280   0.05703  -0.0386   0.0202   1.0000
  13.500   1.3988   0.06703   0.06152  -0.0389   0.0201   1.0000
  13.750   1.3863   0.07181   0.06656  -0.0397   0.0200   1.0000
  14.000   1.3725   0.07714   0.07214  -0.0411   0.0200   1.0000
  14.250   1.3567   0.08297   0.07820  -0.0432   0.0199   1.0000
  14.500   1.3391   0.08938   0.08485  -0.0460   0.0200   1.0000
  14.750   1.3210   0.09627   0.09195  -0.0493   0.0200   1.0000
  15.000   1.3019   0.10374   0.09962  -0.0534   0.0201   1.0000
  15.250   1.2821   0.11183   0.10790  -0.0580   0.0202   1.0000
  15.500   1.2649   0.11982   0.11606  -0.0630   0.0203   1.0000
  15.750   1.2494   0.12788   0.12428  -0.0685   0.0204   1.0000
  16.000   1.2320   0.13710   0.13368  -0.0749   0.0206   1.0000
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