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GOE 679 AIRFOIL (goe679-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 679 AIRFOIL (goe679-il)
Reynolds number: 50,000
Max Cl/Cd: 5.38 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe679-il-50000.txt
Download as CSV file: xf-goe679-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 679 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2562   0.13405   0.12714  -0.0215   1.0000   0.2625
  -9.500  -0.2795   0.13428   0.12748  -0.0199   1.0000   0.2691
  -9.250  -0.3281   0.13651   0.12988  -0.0183   1.0000   0.2711
  -9.000  -0.2860   0.12954   0.12291  -0.0166   1.0000   0.2753
  -8.750  -0.2816   0.12739   0.12081  -0.0146   1.0000   0.2806
  -8.500  -0.2945   0.12648   0.12000  -0.0128   1.0000   0.2870
  -8.250  -0.3492   0.12856   0.12225  -0.0108   1.0000   0.2914
  -8.000  -0.3241   0.12338   0.11710  -0.0094   1.0000   0.2950
  -7.750  -0.3128   0.12099   0.11474  -0.0073   1.0000   0.3022
  -7.500  -0.3391   0.12075   0.11462  -0.0052   1.0000   0.3103
  -7.250  -0.3977   0.12205   0.11608  -0.0028   1.0000   0.3128
  -7.000  -0.3439   0.11611   0.11012  -0.0016   1.0000   0.3204
  -6.750  -0.3548   0.11486   0.10895   0.0005   1.0000   0.3285
  -6.500  -0.4160   0.11588   0.11014   0.0036   1.0000   0.3339
  -6.250  -0.3912   0.11148   0.10577   0.0046   1.0000   0.3388
  -6.000  -0.5894   0.08552   0.07941  -0.0145   1.0000   0.1963
  -5.750  -0.5939   0.08180   0.07567  -0.0136   1.0000   0.1955
  -5.500  -0.6010   0.07742   0.07119  -0.0133   1.0000   0.1946
  -5.250  -0.6077   0.07259   0.06619  -0.0134   1.0000   0.1939
  -5.000  -0.6021   0.06566   0.05873  -0.0173   0.9944   0.1951
  -4.750  -0.5532   0.06447   0.05751  -0.0228   0.9753   0.2052
  -4.500  -0.5373   0.05852   0.05069  -0.0265   0.9630   0.2145
  -4.250  -0.5000   0.05838   0.05069  -0.0286   0.9470   0.2274
  -4.000  -0.4699   0.05715   0.04935  -0.0303   0.9322   0.2418
  -3.750  -0.4428   0.05577   0.04777  -0.0316   0.9184   0.2579
  -3.500  -0.4150   0.05458   0.04631  -0.0328   0.9051   0.2750
  -3.250  -0.3818   0.05377   0.04524  -0.0345   0.8924   0.2938
  -3.000  -0.3575   0.05334   0.04482  -0.0345   0.8784   0.3084
  -2.750  -0.3365   0.05266   0.04409  -0.0341   0.8649   0.3210
  -2.500  -0.3112   0.05190   0.04291  -0.0346   0.8526   0.3351
  -2.250  -0.2727   0.05140   0.04246  -0.0365   0.8413   0.3494
  -2.000  -0.2602   0.05088   0.04166  -0.0351   0.8281   0.3583
  -1.750  -0.2326   0.05060   0.04138  -0.0354   0.8167   0.3700
  -1.500  -0.2024   0.05015   0.04073  -0.0362   0.8054   0.3827
  -1.250  -0.1879   0.05019   0.04073  -0.0349   0.7936   0.3923
  -1.000  -0.1455   0.04978   0.04018  -0.0371   0.7840   0.4082
  -0.750  -0.1403   0.05013   0.04045  -0.0347   0.7720   0.4177
  -0.500  -0.0902   0.04973   0.03998  -0.0378   0.7632   0.4378
  -0.250  -0.0938   0.05041   0.04059  -0.0345   0.7516   0.4470
   0.000  -0.0411   0.05003   0.04024  -0.0377   0.7431   0.4727
   0.250  -0.0458   0.05100   0.04119  -0.0345   0.7315   0.4850
   0.500   0.0103   0.05068   0.04097  -0.0382   0.7232   0.5222
   0.750   0.0051   0.05185   0.04221  -0.0353   0.7125   0.5399
   1.000   0.0567   0.05137   0.04206  -0.0380   0.7037   0.6031
   1.250   0.0546   0.05244   0.04351  -0.0354   0.6941   0.6488
   1.500   0.2219   0.05248   0.04402  -0.0597   0.6793   1.0000
   1.750   0.2216   0.05406   0.04539  -0.0573   0.6689   1.0000
   2.000   0.2616   0.05448   0.04550  -0.0585   0.6610   1.0000
   2.250   0.2443   0.05677   0.04771  -0.0547   0.6506   1.0000
   2.500   0.3035   0.05642   0.04707  -0.0573   0.6428   1.0000
   2.750   0.2673   0.05966   0.05030  -0.0523   0.6327   1.0000
   3.000   0.3162   0.05963   0.05005  -0.0538   0.6240   1.0000
   3.250   0.2921   0.06263   0.05301  -0.0501   0.6146   1.0000
   3.500   0.3266   0.06321   0.05343  -0.0505   0.6058   1.0000
   3.750   0.3175   0.06577   0.05594  -0.0482   0.5971   1.0000
   4.000   0.3344   0.06718   0.05724  -0.0476   0.5883   1.0000
   4.250   0.3464   0.06897   0.05894  -0.0467   0.5800   1.0000
   4.500   0.3432   0.07141   0.06134  -0.0451   0.5717   1.0000
   4.750   0.3827   0.07195   0.06174  -0.0455   0.5629   1.0000
   5.000   0.3573   0.07576   0.06556  -0.0433   0.5569   1.0000
   5.250   0.3762   0.07737   0.06709  -0.0430   0.5489   1.0000
   5.500   0.3878   0.07953   0.06919  -0.0424   0.5418   1.0000
   5.750   0.3748   0.08313   0.07279  -0.0413   0.5391   1.0000
   6.000   0.3698   0.08633   0.07598  -0.0407   0.5366   1.0000
   6.250   0.3677   0.08987   0.07950  -0.0405   0.5389   1.0000
   6.500   0.3794   0.09340   0.08301  -0.0413   0.5431   1.0000
   6.750   0.3165   0.10319   0.09301  -0.0438   0.6238   1.0000
   7.000   0.3015   0.10397   0.09378  -0.0414   0.6158   1.0000
   7.250   0.3222   0.10649   0.09625  -0.0419   0.6070   1.0000
   7.500   0.3436   0.11012   0.09981  -0.0428   0.6023   1.0000
   7.750   0.3377   0.11068   0.10036  -0.0410   0.5901   1.0000
   8.000   0.3808   0.11560   0.10521  -0.0434   0.5841   1.0000
   8.250   0.3564   0.11518   0.10478  -0.0406   0.5742   1.0000
   8.500   0.3812   0.11826   0.10782  -0.0414   0.5671   1.0000
   8.750   0.3905   0.12115   0.11067  -0.0414   0.5624   1.0000
   9.000   0.3919   0.12219   0.11170  -0.0405   0.5510   1.0000
   9.250   0.4304   0.12702   0.11649  -0.0423   0.5454   1.0000
   9.500   0.4094   0.12678   0.11625  -0.0403   0.5363   1.0000
   9.750   0.4286   0.12953   0.11896  -0.0407   0.5292   1.0000
  10.000   0.4670   0.13517   0.12459  -0.0426   0.5254   1.0000
  10.250   0.4398   0.13377   0.12318  -0.0404   0.5153   1.0000
  10.500   0.4643   0.13704   0.12643  -0.0411   0.5084   1.0000
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