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GOE 532 AIRFOIL (goe532-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 532 AIRFOIL (goe532-il)
Reynolds number: 200,000
Max Cl/Cd: 73.55 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe532-il-200000-n5.txt
Download as CSV file: xf-goe532-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 532 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2893   0.11131   0.10748  -0.0365   1.0000   0.0415
 -10.500  -0.2930   0.10736   0.10356  -0.0387   1.0000   0.0417
 -10.250  -0.2970   0.10330   0.09955  -0.0408   1.0000   0.0418
 -10.000  -0.2886   0.10084   0.09713  -0.0397   1.0000   0.0421
  -9.750  -0.2736   0.09980   0.09612  -0.0375   1.0000   0.0432
  -9.500  -0.2698   0.09742   0.09379  -0.0374   1.0000   0.0442
  -9.000  -0.2961   0.08621   0.08266  -0.0420   0.9993   0.0362
  -8.750  -0.2803   0.08254   0.07900  -0.0454   0.9883   0.0358
  -8.500  -0.2691   0.07769   0.07415  -0.0506   0.9749   0.0357
  -8.250  -0.2601   0.07116   0.06761  -0.0587   0.9583   0.0359
  -8.000  -0.2492   0.06376   0.06018  -0.0689   0.9390   0.0358
  -7.750  -0.2342   0.05231   0.04858  -0.0863   0.9189   0.0352
  -7.500  -0.2285   0.04029   0.03593  -0.1000   0.8980   0.0348
  -7.250  -0.2145   0.03407   0.02905  -0.1046   0.8808   0.0354
  -7.000  -0.1959   0.02993   0.02424  -0.1064   0.8651   0.0360
  -6.750  -0.1736   0.02731   0.02113  -0.1069   0.8502   0.0362
  -6.500  -0.1501   0.02532   0.01870  -0.1070   0.8350   0.0365
  -6.250  -0.1258   0.02389   0.01706  -0.1069   0.8190   0.0368
  -6.000  -0.1014   0.02274   0.01570  -0.1065   0.8020   0.0372
  -5.750  -0.0766   0.02185   0.01465  -0.1061   0.7843   0.0377
  -5.500  -0.0516   0.02108   0.01370  -0.1056   0.7660   0.0384
  -5.250  -0.0265   0.02024   0.01264  -0.1050   0.7472   0.0391
  -5.000  -0.0013   0.01939   0.01153  -0.1044   0.7278   0.0397
  -4.750   0.0241   0.01860   0.01049  -0.1038   0.7077   0.0401
  -4.500   0.0496   0.01791   0.00957  -0.1031   0.6877   0.0406
  -4.250   0.0751   0.01733   0.00876  -0.1024   0.6691   0.0411
  -4.000   0.1009   0.01683   0.00806  -0.1017   0.6523   0.0416
  -3.750   0.1264   0.01633   0.00744  -0.1011   0.6377   0.0422
  -3.500   0.1522   0.01592   0.00698  -0.1005   0.6244   0.0431
  -3.250   0.1783   0.01561   0.00662  -0.1000   0.6128   0.0444
  -3.000   0.2044   0.01533   0.00623  -0.0995   0.6015   0.0455
  -2.750   0.2306   0.01502   0.00585  -0.0990   0.5900   0.0465
  -2.500   0.2569   0.01476   0.00551  -0.0984   0.5791   0.0474
  -2.250   0.2829   0.01451   0.00519  -0.0979   0.5680   0.0485
  -2.000   0.3094   0.01427   0.00493  -0.0975   0.5580   0.0499
  -1.750   0.3359   0.01413   0.00472  -0.0971   0.5489   0.0518
  -1.500   0.3629   0.01401   0.00454  -0.0967   0.5406   0.0545
  -1.250   0.3896   0.01386   0.00434  -0.0963   0.5324   0.0578
  -1.000   0.4166   0.01376   0.00419  -0.0960   0.5243   0.0620
  -0.750   0.4436   0.01363   0.00404  -0.0956   0.5166   0.0692
  -0.500   0.4702   0.01345   0.00390  -0.0952   0.5104   0.0936
  -0.250   0.4954   0.01273   0.00393  -0.0951   0.5042   0.3046
   0.000   0.5212   0.01253   0.00401  -0.0947   0.4981   0.4057
   0.250   0.5468   0.01242   0.00409  -0.0941   0.4928   0.4882
   0.500   0.5714   0.01221   0.00422  -0.0932   0.4868   0.5871
   0.750   0.5939   0.01195   0.00434  -0.0917   0.4809   0.7156
   1.000   0.6210   0.01163   0.00434  -0.0909   0.4758   0.8553
   1.250   0.6633   0.01164   0.00436  -0.0937   0.4699   1.0000
   1.500   0.6905   0.01179   0.00441  -0.0934   0.4646   1.0000
   1.750   0.7171   0.01197   0.00446  -0.0930   0.4589   1.0000
   2.000   0.7441   0.01210   0.00455  -0.0927   0.4525   1.0000
   2.250   0.7709   0.01225   0.00464  -0.0923   0.4468   1.0000
   2.750   0.8239   0.01258   0.00485  -0.0915   0.4340   1.0000
   3.000   0.8500   0.01275   0.00496  -0.0911   0.4267   1.0000
   3.250   0.8760   0.01292   0.00508  -0.0906   0.4184   1.0000
   3.500   0.9018   0.01309   0.00520  -0.0901   0.4098   1.0000
   3.750   0.9276   0.01328   0.00535  -0.0896   0.4019   1.0000
   4.000   0.9532   0.01346   0.00551  -0.0891   0.3930   1.0000
   4.250   0.9786   0.01365   0.00567  -0.0886   0.3835   1.0000
   4.500   1.0031   0.01387   0.00583  -0.0879   0.3718   1.0000
   4.750   1.0278   0.01408   0.00602  -0.0873   0.3573   1.0000
   5.000   1.0520   0.01432   0.00622  -0.0866   0.3414   1.0000
   5.250   1.0753   0.01462   0.00644  -0.0857   0.3209   1.0000
   5.500   1.0962   0.01505   0.00671  -0.0846   0.2906   1.0000
   5.750   1.1149   0.01564   0.00709  -0.0832   0.2596   1.0000
   6.000   1.1339   0.01625   0.00756  -0.0819   0.2384   1.0000
   6.250   1.1537   0.01679   0.00802  -0.0806   0.2256   1.0000
   6.500   1.1736   0.01732   0.00848  -0.0794   0.2171   1.0000
   6.750   1.1944   0.01776   0.00893  -0.0783   0.2109   1.0000
   7.000   1.2140   0.01826   0.00941  -0.0771   0.2056   1.0000
   7.250   1.2331   0.01876   0.00990  -0.0758   0.2011   1.0000
   7.500   1.2529   0.01921   0.01037  -0.0746   0.1970   1.0000
   7.750   1.2713   0.01970   0.01089  -0.0732   0.1929   1.0000
   8.000   1.2880   0.02027   0.01145  -0.0716   0.1889   1.0000
   8.250   1.3033   0.02082   0.01201  -0.0697   0.1855   1.0000
   8.500   1.3202   0.02127   0.01254  -0.0681   0.1826   1.0000
   8.750   1.3358   0.02180   0.01311  -0.0663   0.1794   1.0000
   9.000   1.3499   0.02240   0.01375  -0.0644   0.1757   1.0000
   9.250   1.3619   0.02312   0.01448  -0.0624   0.1722   1.0000
   9.500   1.3748   0.02383   0.01523  -0.0605   0.1689   1.0000
   9.750   1.3902   0.02442   0.01592  -0.0591   0.1654   1.0000
  10.000   1.4035   0.02514   0.01671  -0.0574   0.1617   1.0000
  10.250   1.4147   0.02601   0.01763  -0.0557   0.1579   1.0000
  10.500   1.4228   0.02710   0.01874  -0.0538   0.1541   1.0000
  10.750   1.4379   0.02781   0.01958  -0.0527   0.1488   1.0000
  11.000   1.4483   0.02883   0.02068  -0.0513   0.1428   1.0000
  11.250   1.4583   0.02995   0.02186  -0.0500   0.1369   1.0000
  11.500   1.4678   0.03115   0.02313  -0.0487   0.1272   1.0000
  11.750   1.4750   0.03259   0.02459  -0.0475   0.1130   1.0000
  12.000   1.4760   0.03460   0.02654  -0.0463   0.1024   1.0000
  12.250   1.4754   0.03689   0.02879  -0.0452   0.0966   1.0000
  12.500   1.4756   0.03924   0.03117  -0.0444   0.0938   1.0000
  12.750   1.4750   0.04178   0.03376  -0.0438   0.0915   1.0000
  13.000   1.4734   0.04454   0.03658  -0.0433   0.0896   1.0000
  13.250   1.4700   0.04760   0.03970  -0.0431   0.0878   1.0000
  13.500   1.4696   0.05041   0.04260  -0.0430   0.0864   1.0000
  13.750   1.4695   0.05325   0.04555  -0.0429   0.0853   1.0000
  14.000   1.4685   0.05626   0.04866  -0.0430   0.0842   1.0000
  14.250   1.4666   0.05944   0.05193  -0.0432   0.0830   1.0000
  14.500   1.4649   0.06266   0.05525  -0.0435   0.0820   1.0000
  14.750   1.4628   0.06597   0.05864  -0.0439   0.0811   1.0000
  15.000   1.4610   0.06930   0.06203  -0.0444   0.0802   1.0000
  15.250   1.4598   0.07254   0.06531  -0.0448   0.0793   1.0000
  15.500   1.4605   0.07550   0.06829  -0.0451   0.0784   1.0000
  15.750   1.4635   0.07827   0.07116  -0.0454   0.0776   1.0000
  16.000   1.4663   0.08117   0.07419  -0.0460   0.0768   1.0000
  16.250   1.4696   0.08401   0.07713  -0.0465   0.0759   1.0000
  16.500   1.4723   0.08694   0.08017  -0.0471   0.0749   1.0000
  16.750   1.4756   0.08978   0.08310  -0.0477   0.0740   1.0000
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