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GOE 425 AIRFOIL (goe425-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 425 AIRFOIL (goe425-il)
Reynolds number: 100,000
Max Cl/Cd: 44.61 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe425-il-100000-n5.txt
Download as CSV file: xf-goe425-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 425 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.2753   0.12380   0.11889  -0.0403   1.0000   0.0835
 -11.250  -0.2846   0.12037   0.11554  -0.0444   1.0000   0.0870
 -11.000  -0.2929   0.11563   0.11082  -0.0515   0.9549   0.0876
 -10.000  -0.2824   0.08795   0.08276  -0.0651   0.8507   0.0532
  -9.750  -0.2785   0.08460   0.07933  -0.0661   0.8320   0.0527
  -9.500  -0.2789   0.08025   0.07491  -0.0682   0.8169   0.0521
  -9.250  -0.2860   0.07394   0.06854  -0.0728   0.8041   0.0516
  -9.000  -0.3096   0.06348   0.05795  -0.0836   0.7932   0.0507
  -8.750  -0.3326   0.05675   0.05091  -0.0887   0.7831   0.0503
  -8.500  -0.3415   0.05165   0.04546  -0.0909   0.7732   0.0502
  -8.250  -0.3423   0.04739   0.04078  -0.0918   0.7650   0.0502
  -8.000  -0.3370   0.04367   0.03663  -0.0921   0.7562   0.0499
  -7.750  -0.3263   0.04055   0.03307  -0.0919   0.7486   0.0498
  -7.500  -0.3120   0.03790   0.03000  -0.0916   0.7409   0.0498
  -7.250  -0.2949   0.03563   0.02732  -0.0912   0.7332   0.0499
  -7.000  -0.2757   0.03368   0.02497  -0.0907   0.7264   0.0501
  -6.750  -0.2549   0.03202   0.02298  -0.0902   0.7184   0.0506
  -6.500  -0.2328   0.03060   0.02121  -0.0897   0.7120   0.0515
  -6.250  -0.2097   0.02933   0.01961  -0.0892   0.7049   0.0524
  -6.000  -0.1856   0.02818   0.01816  -0.0888   0.6983   0.0530
  -5.500  -0.1354   0.02616   0.01575  -0.0880   0.6860   0.0537
  -5.250  -0.1101   0.02522   0.01473  -0.0877   0.6798   0.0542
  -5.000  -0.0846   0.02442   0.01384  -0.0873   0.6747   0.0549
  -4.750  -0.0595   0.02373   0.01314  -0.0869   0.6679   0.0556
  -4.500  -0.0342   0.02311   0.01246  -0.0865   0.6624   0.0566
  -4.250  -0.0086   0.02257   0.01184  -0.0861   0.6582   0.0582
  -4.000   0.0163   0.02212   0.01136  -0.0857   0.6522   0.0600
  -3.750   0.0412   0.02167   0.01085  -0.0852   0.6469   0.0615
  -3.500   0.0661   0.02122   0.01035  -0.0847   0.6425   0.0630
  -3.250   0.0912   0.02088   0.00998  -0.0843   0.6375   0.0647
  -3.000   0.1165   0.02060   0.00965  -0.0839   0.6322   0.0668
  -2.750   0.1424   0.02033   0.00932  -0.0836   0.6279   0.0696
  -2.500   0.1688   0.02007   0.00903  -0.0833   0.6244   0.0743
  -2.250   0.1944   0.01989   0.00893  -0.0831   0.6194   0.0847
  -2.000   0.2203   0.01969   0.00874  -0.0828   0.6146   0.1080
  -1.750   0.2459   0.01927   0.00845  -0.0825   0.6106   0.1477
  -1.500   0.2691   0.01835   0.00827  -0.0822   0.6074   0.3300
  -1.250   0.2922   0.01810   0.00854  -0.0815   0.6030   0.4736
  -1.000   0.3171   0.01809   0.00867  -0.0808   0.5985   0.5390
  -0.750   0.3428   0.01807   0.00871  -0.0802   0.5946   0.5847
  -0.500   0.3686   0.01801   0.00871  -0.0795   0.5914   0.6308
  -0.250   0.3926   0.01797   0.00883  -0.0785   0.5878   0.6848
   0.000   0.4166   0.01794   0.00900  -0.0775   0.5833   0.7325
   0.250   0.4430   0.01791   0.00906  -0.0770   0.5794   0.7737
   0.500   0.4748   0.01784   0.00907  -0.0773   0.5760   0.8312
   0.750   0.5258   0.01781   0.00901  -0.0815   0.5729   0.9136
   1.000   0.5749   0.01805   0.00924  -0.0863   0.5678   0.9944
   1.250   0.6016   0.01828   0.00936  -0.0865   0.5636   1.0000
   1.500   0.6263   0.01846   0.00941  -0.0861   0.5601   1.0000
   1.750   0.6524   0.01862   0.00942  -0.0858   0.5572   1.0000
   2.000   0.6761   0.01892   0.00966  -0.0853   0.5534   1.0000
   2.250   0.6989   0.01926   0.00998  -0.0847   0.5489   1.0000
   2.500   0.7235   0.01952   0.01018  -0.0843   0.5451   1.0000
   2.750   0.7495   0.01972   0.01029  -0.0840   0.5419   1.0000
   3.000   0.7768   0.01990   0.01034  -0.0839   0.5392   1.0000
   3.250   0.7982   0.02036   0.01085  -0.0832   0.5347   1.0000
   3.500   0.8212   0.02074   0.01125  -0.0826   0.5305   1.0000
   3.750   0.8462   0.02102   0.01150  -0.0822   0.5269   1.0000
   4.000   0.8729   0.02123   0.01164  -0.0821   0.5239   1.0000
   4.250   0.8993   0.02149   0.01185  -0.0819   0.5209   1.0000
   4.500   0.9187   0.02209   0.01255  -0.0810   0.5162   1.0000
   4.750   0.9414   0.02252   0.01302  -0.0804   0.5122   1.0000
   5.000   0.9666   0.02281   0.01330  -0.0801   0.5088   1.0000
   5.250   0.9941   0.02301   0.01345  -0.0800   0.5060   1.0000
   5.500   1.0160   0.02350   0.01400  -0.0794   0.5021   1.0000
   5.750   1.0344   0.02416   0.01477  -0.0783   0.4974   1.0000
   6.000   1.0570   0.02462   0.01528  -0.0778   0.4937   1.0000
   6.250   1.0826   0.02492   0.01559  -0.0775   0.4906   1.0000
   6.500   1.1110   0.02510   0.01574  -0.0776   0.4881   1.0000
   6.750   1.1243   0.02601   0.01682  -0.0760   0.4828   1.0000
   7.000   1.1426   0.02664   0.01754  -0.0750   0.4781   1.0000
   7.250   1.1673   0.02689   0.01783  -0.0746   0.4743   1.0000
   7.500   1.1977   0.02685   0.01776  -0.0748   0.4711   1.0000
   7.750   1.2042   0.02799   0.01910  -0.0724   0.4646   1.0000
   8.000   1.2233   0.02843   0.01962  -0.0714   0.4595   1.0000
   8.250   1.2511   0.02845   0.01966  -0.0713   0.4559   1.0000
   8.500   1.2649   0.02922   0.02054  -0.0697   0.4510   1.0000
   8.750   1.2724   0.03023   0.02171  -0.0675   0.4450   1.0000
   9.000   1.2970   0.03029   0.02181  -0.0670   0.4406   1.0000
   9.250   1.3127   0.03077   0.02237  -0.0656   0.4352   1.0000
   9.500   1.3088   0.03208   0.02384  -0.0620   0.4282   1.0000
   9.750   1.3412   0.03146   0.02322  -0.0621   0.4228   1.0000
  10.000   1.3206   0.03383   0.02577  -0.0575   0.4146   1.0000
  10.250   1.3450   0.03348   0.02543  -0.0567   0.4076   1.0000
  10.500   1.3215   0.03671   0.02883  -0.0534   0.3988   1.0000
  10.750   1.3437   0.03658   0.02873  -0.0526   0.3920   1.0000
  11.000   1.3131   0.04129   0.03361  -0.0504   0.3824   1.0000
  11.250   1.3392   0.04084   0.03319  -0.0498   0.3761   1.0000
  11.500   1.3037   0.04674   0.03923  -0.0485   0.3654   1.0000
  11.750   1.3389   0.04522   0.03774  -0.0478   0.3597   1.0000
  12.000   1.3017   0.05171   0.04437  -0.0470   0.3479   1.0000
  12.250   1.2959   0.05484   0.04759  -0.0464   0.3383   1.0000
  12.500   1.3119   0.05535   0.04814  -0.0456   0.3298   1.0000
  12.750   1.2918   0.06033   0.05323  -0.0453   0.3177   1.0000
  13.000   1.2929   0.06273   0.05569  -0.0448   0.3069   1.0000
  13.250   1.3078   0.06332   0.05631  -0.0441   0.2962   1.0000
  13.500   1.3019   0.06669   0.05973  -0.0438   0.2826   1.0000
  13.750   1.2968   0.07002   0.06310  -0.0436   0.2679   1.0000
  14.000   1.2968   0.07268   0.06577  -0.0434   0.2522   1.0000
  14.250   1.2961   0.07551   0.06857  -0.0432   0.2358   1.0000
  14.500   1.2962   0.07822   0.07123  -0.0430   0.2194   1.0000
  14.750   1.2970   0.08080   0.07372  -0.0427   0.2048   1.0000
  15.000   1.2976   0.08342   0.07624  -0.0425   0.1924   1.0000
  15.250   1.2979   0.08613   0.07886  -0.0423   0.1819   1.0000
  15.500   1.2981   0.08897   0.08169  -0.0422   0.1729   1.0000
  15.750   1.3013   0.09124   0.08386  -0.0420   0.1649   1.0000
  16.000   1.3016   0.09420   0.08688  -0.0421   0.1572   1.0000
  16.250   1.3065   0.09626   0.08885  -0.0419   0.1500   1.0000
  16.500   1.3051   0.09964   0.09236  -0.0423   0.1428   1.0000
  16.750   1.3088   0.10194   0.09457  -0.0423   0.1360   1.0000
  17.000   1.3053   0.10582   0.09862  -0.0432   0.1293   1.0000
  17.250   1.3047   0.10897   0.10174  -0.0438   0.1229   1.0000
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