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GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il)
Reynolds number: 200,000
Max Cl/Cd: 67.59 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe199-il-200000-n5.txt
Download as CSV file: xf-goe199-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 199 (L.F.G. 5406) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3192   0.09872   0.09539  -0.0237   1.0000   0.0211
  -7.750  -0.3173   0.09609   0.09282  -0.0256   1.0000   0.0211
  -7.500  -0.3147   0.09343   0.09022  -0.0276   1.0000   0.0211
  -7.250  -0.3003   0.08970   0.08649  -0.0330   0.9950   0.0212
  -7.000  -0.2810   0.08497   0.08176  -0.0366   0.9876   0.0213
  -6.750  -0.2645   0.08098   0.07777  -0.0377   0.9803   0.0217
  -6.500  -0.2422   0.07731   0.07406  -0.0420   0.9712   0.0228
  -6.250  -0.2137   0.07332   0.07001  -0.0488   0.9607   0.0249
  -6.000  -0.1735   0.06879   0.06535  -0.0600   0.9487   0.0257
  -5.750  -0.1396   0.06443   0.06082  -0.0672   0.9369   0.0258
  -5.250  -0.1044   0.05706   0.05338  -0.0695   0.9154   0.0267
  -5.000  -0.0832   0.05434   0.05059  -0.0711   0.9046   0.0281
  -4.750  -0.0553   0.05119   0.04732  -0.0743   0.8953   0.0298
  -4.500  -0.0067   0.04791   0.04360  -0.0807   0.8873   0.0319
  -4.000   0.0338   0.04152   0.03710  -0.0825   0.8708   0.0337
  -3.750   0.0595   0.03926   0.03473  -0.0837   0.8622   0.0354
  -3.500   0.0901   0.03688   0.03211  -0.0852   0.8550   0.0380
  -3.250   0.1296   0.03422   0.02895  -0.0872   0.8473   0.0407
  -3.000   0.1506   0.03189   0.02664  -0.0877   0.8401   0.0422
  -2.750   0.1770   0.03032   0.02496  -0.0883   0.8317   0.0455
  -2.500   0.2124   0.02856   0.02267  -0.0890   0.8249   0.0508
  -2.250   0.2375   0.02661   0.02071  -0.0896   0.8163   0.0524
  -2.000   0.2700   0.02694   0.02054  -0.0893   0.8077   0.0607
  -1.750   0.2950   0.02398   0.01755  -0.0898   0.7957   0.0625
  -1.250   0.3549   0.02141   0.01412  -0.0887   0.7623   0.0504
  -1.000   0.3838   0.01926   0.01170  -0.0884   0.7469   0.0396
  -0.750   0.4119   0.01807   0.01029  -0.0883   0.7325   0.0387
  -0.500   0.4403   0.01716   0.00917  -0.0882   0.7179   0.0382
  -0.250   0.4685   0.01658   0.00836  -0.0879   0.7024   0.0391
   0.000   0.4966   0.01609   0.00767  -0.0877   0.6857   0.0398
   0.250   0.5245   0.01542   0.00686  -0.0875   0.6675   0.0393
   0.500   0.5521   0.01490   0.00621  -0.0873   0.6469   0.0390
   0.750   0.5795   0.01450   0.00566  -0.0871   0.6249   0.0389
   1.000   0.6066   0.01418   0.00522  -0.0868   0.5997   0.0389
   1.250   0.6334   0.01397   0.00486  -0.0865   0.5734   0.0391
   1.500   0.6599   0.01385   0.00459  -0.0862   0.5478   0.0395
   1.750   0.6865   0.01379   0.00442  -0.0859   0.5236   0.0399
   2.000   0.7130   0.01371   0.00425  -0.0858   0.5009   0.0421
   2.250   0.7397   0.01374   0.00420  -0.0857   0.4779   0.0441
   2.500   0.7664   0.01384   0.00418  -0.0855   0.4546   0.0449
   2.750   0.7930   0.01398   0.00420  -0.0853   0.4288   0.0460
   3.000   0.8193   0.01417   0.00425  -0.0851   0.4008   0.0475
   3.250   0.8452   0.01443   0.00434  -0.0849   0.3727   0.0498
   3.500   0.8710   0.01471   0.00452  -0.0847   0.3478   0.0562
   4.000   0.9224   0.01375   0.00498  -0.0844   0.3099   1.0000
   4.250   0.9481   0.01411   0.00523  -0.0842   0.2957   1.0000
   4.500   0.9737   0.01448   0.00551  -0.0839   0.2839   1.0000
   4.750   0.9991   0.01485   0.00580  -0.0837   0.2738   1.0000
   5.000   1.0248   0.01518   0.00612  -0.0835   0.2654   1.0000
   5.250   1.0499   0.01558   0.00645  -0.0832   0.2581   1.0000
   5.500   1.0754   0.01591   0.00680  -0.0829   0.2517   1.0000
   5.750   1.1004   0.01629   0.00716  -0.0826   0.2457   1.0000
   6.000   1.1252   0.01669   0.00756  -0.0823   0.2405   1.0000
   6.250   1.1503   0.01704   0.00795  -0.0820   0.2355   1.0000
   6.500   1.1749   0.01744   0.00837  -0.0816   0.2313   1.0000
   6.750   1.1989   0.01787   0.00883  -0.0812   0.2268   1.0000
   7.000   1.2238   0.01821   0.00925  -0.0808   0.2214   1.0000
   7.250   1.2476   0.01862   0.00969  -0.0804   0.2158   1.0000
   7.500   1.2713   0.01905   0.01016  -0.0799   0.2112   1.0000
   7.750   1.2955   0.01939   0.01063  -0.0795   0.2051   1.0000
   8.000   1.3179   0.01985   0.01110  -0.0789   0.1974   1.0000
   8.250   1.3414   0.02018   0.01153  -0.0784   0.1869   1.0000
   8.500   1.3641   0.02058   0.01200  -0.0779   0.1757   1.0000
   8.750   1.3859   0.02105   0.01252  -0.0772   0.1590   1.0000
   9.000   1.3989   0.02239   0.01339  -0.0755   0.0852   1.0000
   9.250   1.4063   0.02441   0.01517  -0.0730   0.0438   1.0000
   9.500   1.4192   0.02571   0.01649  -0.0711   0.0338   1.0000
   9.750   1.4304   0.02702   0.01789  -0.0690   0.0286   1.0000
  10.000   1.4429   0.02806   0.01911  -0.0670   0.0255   1.0000
  10.250   1.4506   0.02932   0.02052  -0.0644   0.0233   1.0000
  10.500   1.4504   0.03094   0.02228  -0.0608   0.0216   1.0000
  10.750   1.4546   0.03236   0.02386  -0.0581   0.0204   1.0000
  11.000   1.4583   0.03394   0.02559  -0.0557   0.0191   1.0000
  11.250   1.4607   0.03574   0.02753  -0.0535   0.0179   1.0000
  11.500   1.4612   0.03782   0.02975  -0.0516   0.0170   1.0000
  11.750   1.4585   0.04036   0.03244  -0.0498   0.0164   1.0000
  12.000   1.4518   0.04348   0.03569  -0.0484   0.0158   1.0000
  12.250   1.4427   0.04709   0.03943  -0.0473   0.0154   1.0000
  12.500   1.4390   0.05031   0.04282  -0.0466   0.0151   1.0000
  12.750   1.4341   0.05382   0.04649  -0.0463   0.0147   1.0000
  13.000   1.4284   0.05756   0.05039  -0.0462   0.0144   1.0000
  13.250   1.4225   0.06149   0.05447  -0.0464   0.0139   1.0000
  13.500   1.4161   0.06563   0.05876  -0.0468   0.0135   1.0000
  13.750   1.4096   0.06991   0.06317  -0.0475   0.0132   1.0000
  14.000   1.4029   0.07433   0.06772  -0.0484   0.0128   1.0000
  14.250   1.3965   0.07889   0.07240  -0.0495   0.0124   1.0000
  14.500   1.3895   0.08359   0.07723  -0.0507   0.0121   1.0000
  14.750   1.3824   0.08834   0.08209  -0.0520   0.0119   1.0000
  15.000   1.3755   0.09308   0.08692  -0.0533   0.0117   1.0000
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