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GOE 369 AIRFOIL (goe369-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 369 AIRFOIL (goe369-il)
Reynolds number: 50,000
Max Cl/Cd: 37.89 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe369-il-50000.txt
Download as CSV file: xf-goe369-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 369 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3777   0.11063   0.10388  -0.0094   1.0000   0.0895
  -8.250  -0.3807   0.10996   0.10334  -0.0119   1.0000   0.0904
  -8.000  -0.3823   0.10954   0.10303  -0.0163   1.0000   0.0909
  -7.750  -0.3602   0.10090   0.09438  -0.0112   1.0000   0.0960
  -7.500  -0.3562   0.09837   0.09190  -0.0121   1.0000   0.0999
  -7.250  -0.3535   0.09699   0.09062  -0.0160   1.0000   0.1032
  -6.750  -0.3365   0.08962   0.08340  -0.0164   1.0000   0.1114
  -6.500  -0.3286   0.08794   0.08177  -0.0209   1.0000   0.1167
  -6.250  -0.3198   0.08427   0.07819  -0.0217   1.0000   0.1203
  -6.000  -0.3100   0.08102   0.07500  -0.0215   1.0000   0.1277
  -5.750  -0.2981   0.07889   0.07291  -0.0263   1.0000   0.1333
  -5.500  -0.2898   0.07508   0.06919  -0.0240   1.0000   0.1412
  -5.250  -0.2781   0.07238   0.06654  -0.0266   1.0000   0.1492
  -5.000  -0.2626   0.07083   0.06496  -0.0305   1.0000   0.1617
  -4.750  -0.2584   0.06673   0.06101  -0.0267   1.0000   0.1720
  -4.500  -0.2504   0.06401   0.05837  -0.0264   1.0000   0.1838
  -4.250  -0.2444   0.06168   0.05613  -0.0259   1.0000   0.1977
  -4.000  -0.2419   0.05967   0.05418  -0.0247   1.0000   0.2132
  -3.750  -0.2373   0.05848   0.05295  -0.0253   1.0000   0.2351
  -3.500  -0.2393   0.05589   0.05050  -0.0219   1.0000   0.2530
  -3.250  -0.2377   0.05386   0.04852  -0.0199   1.0000   0.2822
  -3.000  -0.2364   0.05193   0.04665  -0.0176   1.0000   0.3245
  -2.250  -0.2489   0.04465   0.03980  -0.0014   1.0000   0.4872
  -2.000  -0.2486   0.04243   0.03767   0.0033   1.0000   0.5432
  -1.750  -0.2489   0.03990   0.03528   0.0089   1.0000   0.5891
  -1.500  -0.2434   0.03763   0.03309   0.0128   1.0000   0.6295
  -1.250  -0.2262   0.03541   0.03087   0.0131   1.0000   0.6616
  -1.000  -0.1885   0.03311   0.02851   0.0084   0.9971   0.6777
  -0.750   0.0216   0.03385   0.02710  -0.0407   0.9827   0.3947
  -0.500   0.1066   0.03361   0.02555  -0.0508   0.9710   0.2478
  -0.250   0.1595   0.03244   0.02376  -0.0545   0.9595   0.1969
   0.000   0.2100   0.03155   0.02226  -0.0576   0.9476   0.1657
   0.250   0.2565   0.03076   0.02105  -0.0604   0.9354   0.1525
   0.500   0.3059   0.03003   0.01991  -0.0636   0.9231   0.1518
   0.750   0.3593   0.02938   0.01890  -0.0673   0.9111   0.1495
   1.000   0.4083   0.02876   0.01815  -0.0705   0.8989   0.1621
   1.250   0.4483   0.02840   0.01774  -0.0724   0.8855   0.1759
   1.500   0.4891   0.02795   0.01757  -0.0748   0.8721   0.2247
   1.750   0.5430   0.02652   0.01727  -0.0785   0.8590   1.0000
   2.000   0.5814   0.02703   0.01737  -0.0799   0.8441   1.0000
   2.250   0.6184   0.02751   0.01765  -0.0812   0.8286   1.0000
   2.500   0.6538   0.02799   0.01800  -0.0820   0.8128   1.0000
   2.750   0.6892   0.02839   0.01834  -0.0824   0.7966   1.0000
   3.000   0.7147   0.02900   0.01891  -0.0814   0.7771   1.0000
   3.250   0.7467   0.02906   0.01895  -0.0803   0.7554   1.0000
   3.500   0.7754   0.02908   0.01898  -0.0784   0.7327   1.0000
   3.750   0.8033   0.02904   0.01891  -0.0762   0.7105   1.0000
   4.000   0.8280   0.02926   0.01915  -0.0741   0.6894   1.0000
   4.250   0.8518   0.02946   0.01937  -0.0719   0.6674   1.0000
   4.500   0.8766   0.02950   0.01943  -0.0695   0.6454   1.0000
   4.750   0.9010   0.02940   0.01940  -0.0669   0.6216   1.0000
   5.000   0.9237   0.02931   0.01934  -0.0642   0.5948   1.0000
   5.250   0.9476   0.02888   0.01891  -0.0612   0.5659   1.0000
   5.500   0.9723   0.02820   0.01817  -0.0581   0.5342   1.0000
   5.750   0.9953   0.02768   0.01764  -0.0552   0.4985   1.0000
   6.000   1.0186   0.02729   0.01708  -0.0524   0.4606   1.0000
   6.250   1.0395   0.02753   0.01717  -0.0500   0.4212   1.0000
   6.500   1.0616   0.02802   0.01736  -0.0479   0.3862   1.0000
   6.750   1.0826   0.02917   0.01844  -0.0463   0.3557   1.0000
   7.000   1.1052   0.03049   0.01958  -0.0451   0.3304   1.0000
   7.250   1.1246   0.03211   0.02131  -0.0438   0.3076   1.0000
   7.500   1.1466   0.03372   0.02291  -0.0427   0.2894   1.0000
   7.750   1.1679   0.03558   0.02486  -0.0418   0.2744   1.0000
   8.000   1.1877   0.03741   0.02688  -0.0407   0.2601   1.0000
   8.250   1.2054   0.03960   0.02934  -0.0396   0.2482   1.0000
   8.500   1.2224   0.04211   0.03213  -0.0386   0.2387   1.0000
   8.750   1.2426   0.04417   0.03425  -0.0377   0.2283   1.0000
   9.000   1.2533   0.04696   0.03748  -0.0363   0.2194   1.0000
   9.250   1.2664   0.05020   0.04104  -0.0352   0.2135   1.0000
   9.500   1.2642   0.05459   0.04600  -0.0337   0.2094   1.0000
   9.750   1.2882   0.05684   0.04822  -0.0330   0.2013   1.0000
  10.000   1.2704   0.06223   0.05420  -0.0313   0.1992   1.0000
  10.250   1.2457   0.06818   0.06053  -0.0302   0.1982   1.0000
  10.500   1.2130   0.07486   0.06742  -0.0299   0.1991   1.0000
  10.750   1.1776   0.08185   0.07446  -0.0303   0.2006   1.0000
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