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GOE 533 AIRFOIL (goe533-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 533 AIRFOIL (goe533-il)
Reynolds number: 100,000
Max Cl/Cd: 54.76 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe533-il-100000-n5.txt
Download as CSV file: xf-goe533-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 533 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2571   0.10002   0.09523  -0.0415   1.0000   0.0809
  -9.000  -0.2591   0.09764   0.09294  -0.0410   1.0000   0.0817
  -8.750  -0.2837   0.08733   0.08267  -0.0503   0.9906   0.0574
  -8.500  -0.2665   0.08273   0.07806  -0.0552   0.9769   0.0570
  -8.000  -0.2717   0.05915   0.05415  -0.0861   0.9298   0.0496
  -7.750  -0.2558   0.05412   0.04895  -0.0917   0.9118   0.0492
  -7.500  -0.2409   0.04892   0.04345  -0.0970   0.8932   0.0489
  -7.250  -0.2265   0.04364   0.03767  -0.1014   0.8745   0.0490
  -7.000  -0.2096   0.03917   0.03249  -0.1044   0.8567   0.0496
  -6.750  -0.1866   0.03652   0.02959  -0.1057   0.8407   0.0502
  -6.500  -0.1631   0.03395   0.02663  -0.1066   0.8253   0.0504
  -6.250  -0.1384   0.03171   0.02399  -0.1073   0.8111   0.0506
  -6.000  -0.1127   0.02985   0.02178  -0.1077   0.7978   0.0509
  -5.750  -0.0877   0.02827   0.01989  -0.1078   0.7843   0.0513
  -5.500  -0.0618   0.02696   0.01832  -0.1078   0.7721   0.0520
  -5.250  -0.0350   0.02588   0.01700  -0.1078   0.7613   0.0535
  -5.000  -0.0088   0.02481   0.01565  -0.1077   0.7501   0.0547
  -4.750   0.0180   0.02377   0.01435  -0.1075   0.7402   0.0556
  -4.500   0.0449   0.02283   0.01317  -0.1072   0.7307   0.0563
  -4.250   0.0716   0.02203   0.01217  -0.1068   0.7213   0.0571
  -4.000   0.0986   0.02133   0.01130  -0.1064   0.7128   0.0579
  -3.750   0.1244   0.02062   0.01059  -0.1061   0.7040   0.0590
  -3.500   0.1507   0.02011   0.01005  -0.1057   0.6957   0.0611
  -3.250   0.1769   0.01969   0.00958  -0.1053   0.6877   0.0636
  -3.000   0.2031   0.01929   0.00909  -0.1049   0.6795   0.0660
  -2.750   0.2295   0.01889   0.00863  -0.1045   0.6722   0.0682
  -2.500   0.2555   0.01858   0.00830  -0.1041   0.6638   0.0711
  -2.250   0.2828   0.01832   0.00792  -0.1038   0.6571   0.0753
  -2.000   0.3089   0.01808   0.00770  -0.1035   0.6488   0.0825
  -1.750   0.3359   0.01781   0.00741  -0.1033   0.6416   0.0977
  -1.500   0.3624   0.01739   0.00712  -0.1031   0.6345   0.1377
  -1.250   0.3872   0.01648   0.00701  -0.1032   0.6270   0.3358
  -1.000   0.4119   0.01622   0.00716  -0.1023   0.6209   0.5054
  -0.750   0.4351   0.01619   0.00740  -0.1011   0.6129   0.5832
  -0.500   0.4585   0.01627   0.00759  -0.0996   0.6060   0.6553
  -0.250   0.4817   0.01633   0.00770  -0.0981   0.5993   0.7070
   0.000   0.5054   0.01633   0.00773  -0.0968   0.5916   0.7407
   0.250   0.5308   0.01631   0.00765  -0.0959   0.5855   0.7671
   0.500   0.5552   0.01630   0.00768  -0.0950   0.5778   0.7922
   0.750   0.5807   0.01626   0.00763  -0.0942   0.5707   0.8175
   1.250   0.6407   0.01615   0.00759  -0.0946   0.5556   0.9073
   1.500   0.6765   0.01624   0.00751  -0.0962   0.5495   1.0000
   1.750   0.7033   0.01646   0.00769  -0.0963   0.5411   1.0000
   2.000   0.7311   0.01664   0.00773  -0.0963   0.5344   1.0000
   2.250   0.7578   0.01687   0.00788  -0.0963   0.5270   1.0000
   2.500   0.7846   0.01707   0.00800  -0.0961   0.5196   1.0000
   2.750   0.8117   0.01729   0.00811  -0.0960   0.5134   1.0000
   3.000   0.8375   0.01755   0.00835  -0.0958   0.5059   1.0000
   3.250   0.8644   0.01774   0.00844  -0.0956   0.4996   1.0000
   3.500   0.8897   0.01801   0.00870  -0.0952   0.4915   1.0000
   3.750   0.9157   0.01822   0.00882  -0.0948   0.4844   1.0000
   4.000   0.9409   0.01849   0.00907  -0.0944   0.4768   1.0000
   4.250   0.9663   0.01874   0.00928  -0.0940   0.4694   1.0000
   4.500   0.9916   0.01901   0.00950  -0.0936   0.4626   1.0000
   4.750   1.0160   0.01931   0.00980  -0.0931   0.4547   1.0000
   5.000   1.0414   0.01956   0.00997  -0.0927   0.4481   1.0000
   5.250   1.0649   0.01991   0.01037  -0.0920   0.4402   1.0000
   5.500   1.0900   0.02020   0.01060  -0.0916   0.4340   1.0000
   5.750   1.1131   0.02057   0.01102  -0.0909   0.4264   1.0000
   6.000   1.1369   0.02090   0.01133  -0.0903   0.4194   1.0000
   6.250   1.1607   0.02127   0.01171  -0.0897   0.4133   1.0000
   6.500   1.1833   0.02169   0.01219  -0.0890   0.4067   1.0000
   6.750   1.2074   0.02205   0.01254  -0.0885   0.4013   1.0000
   7.000   1.2297   0.02251   0.01308  -0.0877   0.3953   1.0000
   7.250   1.2516   0.02297   0.01360  -0.0870   0.3891   1.0000
   7.500   1.2751   0.02335   0.01396  -0.0864   0.3838   1.0000
   7.750   1.2951   0.02388   0.01463  -0.0853   0.3772   1.0000
   8.000   1.3158   0.02435   0.01516  -0.0844   0.3708   1.0000
   8.250   1.3377   0.02480   0.01560  -0.0836   0.3651   1.0000
   8.500   1.3548   0.02538   0.01633  -0.0822   0.3577   1.0000
   8.750   1.3747   0.02582   0.01679  -0.0811   0.3510   1.0000
   9.000   1.3900   0.02643   0.01752  -0.0795   0.3432   1.0000
   9.250   1.4060   0.02694   0.01807  -0.0779   0.3353   1.0000
   9.500   1.4188   0.02759   0.01881  -0.0759   0.3270   1.0000
   9.750   1.4307   0.02818   0.01947  -0.0738   0.3192   1.0000
  10.000   1.4402   0.02891   0.02028  -0.0715   0.3116   1.0000
  10.250   1.4488   0.02968   0.02113  -0.0691   0.3038   1.0000
  10.500   1.4570   0.03054   0.02206  -0.0668   0.2964   1.0000
  10.750   1.4631   0.03154   0.02318  -0.0646   0.2887   1.0000
  11.000   1.4707   0.03256   0.02426  -0.0626   0.2821   1.0000
  11.250   1.4749   0.03385   0.02569  -0.0606   0.2747   1.0000
  11.500   1.4809   0.03507   0.02694  -0.0588   0.2682   1.0000
  11.750   1.4816   0.03676   0.02879  -0.0571   0.2602   1.0000
  12.000   1.4841   0.03838   0.03044  -0.0555   0.2531   1.0000
  12.250   1.4829   0.04047   0.03269  -0.0542   0.2452   1.0000
  12.500   1.4847   0.04240   0.03466  -0.0531   0.2391   1.0000
  12.750   1.4834   0.04481   0.03724  -0.0522   0.2324   1.0000
  13.000   1.4838   0.04707   0.03953  -0.0515   0.2264   1.0000
  13.250   1.4802   0.04994   0.04255  -0.0510   0.2198   1.0000
  13.500   1.4772   0.05274   0.04541  -0.0506   0.2132   1.0000
  13.750   1.4711   0.05607   0.04887  -0.0505   0.2063   1.0000
  14.000   1.4662   0.05930   0.05215  -0.0505   0.1998   1.0000
  14.250   1.4608   0.06277   0.05573  -0.0506   0.1938   1.0000
  14.500   1.4542   0.06648   0.05953  -0.0509   0.1876   1.0000
  14.750   1.4503   0.06987   0.06295  -0.0512   0.1816   1.0000
  15.000   1.4402   0.07439   0.06763  -0.0521   0.1751   1.0000
  15.250   1.4369   0.07780   0.07101  -0.0525   0.1684   1.0000
  15.500   1.4233   0.08320   0.07662  -0.0540   0.1615   1.0000
  15.750   1.4161   0.08748   0.08090  -0.0551   0.1539   1.0000
  16.000   1.4005   0.09356   0.08718  -0.0571   0.1462   1.0000
  16.250   1.3899   0.09873   0.09238  -0.0589   0.1379   1.0000
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