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GOE 744 AIRFOIL (goe744-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 744 AIRFOIL (goe744-il)
Reynolds number: 200,000
Max Cl/Cd: 64.81 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe744-il-200000-n5.txt
Download as CSV file: xf-goe744-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 744 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.1694   0.09467   0.08955   0.0007   0.5187   0.0414
  -7.500  -0.1643   0.09201   0.08686  -0.0008   0.5170   0.0422
  -7.250  -0.1634   0.08921   0.08406  -0.0030   0.5154   0.0431
  -7.000  -0.1683   0.08637   0.08127  -0.0058   0.5139   0.0434
  -6.750  -0.1727   0.08359   0.07851  -0.0085   0.5123   0.0436
  -6.500  -0.1683   0.08028   0.07519  -0.0118   0.5104   0.0437
  -6.250  -0.1587   0.07706   0.07197  -0.0135   0.5081   0.0438
  -6.000  -0.1453   0.07450   0.06941  -0.0134   0.5055   0.0440
  -5.750  -0.1318   0.07207   0.06696  -0.0137   0.5032   0.0444
  -5.500  -0.1184   0.06955   0.06440  -0.0146   0.5011   0.0448
  -5.250  -0.1042   0.06701   0.06181  -0.0158   0.4992   0.0454
  -5.000  -0.0891   0.06437   0.05908  -0.0172   0.4974   0.0460
  -4.750  -0.0725   0.06161   0.05623  -0.0188   0.4954   0.0469
  -4.250  -0.0340   0.05440   0.04880  -0.0236   0.4909   0.0494
  -3.750   0.0040   0.04516   0.03914  -0.0252   0.4866   0.0388
  -3.500   0.0249   0.04335   0.03726  -0.0251   0.4843   0.0384
  -3.250   0.0465   0.04090   0.03466  -0.0251   0.4820   0.0379
  -3.000   0.0683   0.03792   0.03144  -0.0250   0.4800   0.0373
  -2.750   0.0900   0.03430   0.02747  -0.0245   0.4781   0.0368
  -2.500   0.1119   0.03067   0.02344  -0.0237   0.4760   0.0371
  -2.250   0.1348   0.02780   0.02015  -0.0228   0.4736   0.0377
  -2.000   0.1591   0.02572   0.01769  -0.0220   0.4710   0.0378
  -1.750   0.1847   0.02412   0.01572  -0.0213   0.4683   0.0379
  -1.500   0.2112   0.02289   0.01417  -0.0207   0.4655   0.0382
  -1.250   0.2385   0.02190   0.01286  -0.0203   0.4630   0.0386
  -1.000   0.2662   0.02111   0.01179  -0.0198   0.4607   0.0391
  -0.750   0.2937   0.02056   0.01113  -0.0196   0.4586   0.0396
  -0.500   0.3218   0.02019   0.01079  -0.0196   0.4554   0.0405
  -0.250   0.3500   0.01982   0.01038  -0.0195   0.4521   0.0417
   0.000   0.3785   0.01941   0.00986  -0.0194   0.4490   0.0429
   0.250   0.4070   0.01901   0.00933  -0.0192   0.4462   0.0437
   0.500   0.4350   0.01859   0.00891  -0.0191   0.4438   0.0445
   0.750   0.4628   0.01828   0.00855  -0.0188   0.4414   0.0455
   1.000   0.4905   0.01808   0.00839  -0.0188   0.4381   0.0467
   1.250   0.5182   0.01792   0.00825  -0.0186   0.4346   0.0485
   1.500   0.5453   0.01771   0.00810  -0.0185   0.4313   0.0506
   1.750   0.5724   0.01754   0.00793  -0.0182   0.4283   0.0530
   2.000   0.5993   0.01737   0.00772  -0.0179   0.4256   0.0551
   2.250   0.6260   0.01726   0.00760  -0.0176   0.4228   0.0579
   2.500   0.6525   0.01724   0.00766  -0.0174   0.4190   0.0624
   2.750   0.6788   0.01719   0.00767  -0.0171   0.4153   0.0695
   3.000   0.7049   0.01708   0.00765  -0.0168   0.4120   0.0843
   3.250   0.7293   0.01685   0.00768  -0.0161   0.4091   0.1790
   3.500   0.7545   0.01682   0.00774  -0.0157   0.4061   0.2362
   3.750   0.7786   0.01682   0.00798  -0.0152   0.4020   0.3006
   4.250   0.9712   0.01598   0.00832  -0.0427   0.3916   1.0000
   4.500   0.9962   0.01622   0.00856  -0.0425   0.3878   1.0000
   4.750   1.0211   0.01648   0.00881  -0.0422   0.3836   1.0000
   5.000   1.0458   0.01669   0.00898  -0.0418   0.3799   1.0000
   5.250   1.0702   0.01689   0.00909  -0.0414   0.3767   1.0000
   5.500   1.0944   0.01714   0.00930  -0.0409   0.3735   1.0000
   5.750   1.1180   0.01748   0.00968  -0.0406   0.3695   1.0000
   6.000   1.1414   0.01779   0.00998  -0.0402   0.3656   1.0000
   6.250   1.1646   0.01805   0.01020  -0.0396   0.3619   1.0000
   6.500   1.1874   0.01832   0.01038  -0.0391   0.3587   1.0000
   6.750   1.2091   0.01876   0.01089  -0.0386   0.3543   1.0000
   7.000   1.2304   0.01915   0.01131  -0.0380   0.3503   1.0000
   7.250   1.2514   0.01953   0.01165  -0.0373   0.3468   1.0000
   7.500   1.2721   0.01988   0.01195  -0.0366   0.3437   1.0000
   7.750   1.2910   0.02040   0.01252  -0.0358   0.3401   1.0000
   8.000   1.3087   0.02096   0.01313  -0.0349   0.3363   1.0000
   8.250   1.3256   0.02149   0.01367  -0.0339   0.3326   1.0000
   8.500   1.3418   0.02201   0.01415  -0.0328   0.3293   1.0000
   8.750   1.3559   0.02264   0.01478  -0.0316   0.3259   1.0000
   9.000   1.3648   0.02359   0.01582  -0.0301   0.3219   1.0000
   9.250   1.3666   0.02469   0.01696  -0.0280   0.3183   1.0000
   9.500   1.3678   0.02574   0.01800  -0.0257   0.3152   1.0000
   9.750   1.3752   0.02661   0.01884  -0.0240   0.3125   1.0000
  10.000   1.3775   0.02797   0.02025  -0.0224   0.3092   1.0000
  10.250   1.3778   0.02960   0.02197  -0.0211   0.3056   1.0000
  10.500   1.3815   0.03108   0.02348  -0.0199   0.3023   1.0000
  10.750   1.3889   0.03229   0.02468  -0.0189   0.2992   1.0000
  11.000   1.4013   0.03311   0.02546  -0.0180   0.2966   1.0000
  11.250   1.4004   0.03516   0.02759  -0.0172   0.2931   1.0000
  11.500   1.3971   0.03749   0.03002  -0.0165   0.2891   1.0000
  11.750   1.4002   0.03927   0.03184  -0.0158   0.2859   1.0000
  12.000   1.4095   0.04049   0.03304  -0.0152   0.2832   1.0000
  12.250   1.4247   0.04114   0.03367  -0.0145   0.2810   1.0000
  12.500   1.4217   0.04364   0.03626  -0.0140   0.2780   1.0000
  12.750   1.4140   0.04666   0.03941  -0.0138   0.2745   1.0000
  13.000   1.4120   0.04919   0.04200  -0.0135   0.2712   1.0000
  13.250   1.4205   0.05064   0.04346  -0.0131   0.2685   1.0000
  13.500   1.4365   0.05126   0.04405  -0.0126   0.2663   1.0000
  13.750   1.4435   0.05291   0.04574  -0.0123   0.2639   1.0000
  14.000   1.4235   0.05775   0.05075  -0.0127   0.2603   1.0000
  14.250   1.4150   0.06133   0.05444  -0.0130   0.2570   1.0000
  14.500   1.4165   0.06376   0.05692  -0.0130   0.2542   1.0000
  14.750   1.4304   0.06467   0.05783  -0.0127   0.2521   1.0000
  15.000   1.4519   0.06466   0.05780  -0.0122   0.2504   1.0000
  15.250   1.4230   0.07095   0.06427  -0.0132   0.2466   1.0000
  15.500   1.3811   0.07920   0.07271  -0.0147   0.2414   1.0000
  15.750   1.3814   0.08198   0.07555  -0.0150   0.2387   1.0000
  16.000   1.3972   0.08267   0.07624  -0.0148   0.2370   1.0000
  16.250   1.4202   0.08237   0.07594  -0.0144   0.2358   1.0000
  16.500   1.4458   0.08173   0.07530  -0.0138   0.2347   1.0000
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