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GOE 155 (SSW D.1) AIRFOIL (goe155-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 155 (SSW D.1) AIRFOIL (goe155-il)
Reynolds number: 100,000
Max Cl/Cd: 59.79 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe155-il-100000.txt
Download as CSV file: xf-goe155-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 155 (SSW D.1) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3038   0.09531   0.09083  -0.0260   1.0000   0.0571
  -7.250  -0.3074   0.09397   0.08959  -0.0267   1.0000   0.0589
  -7.000  -0.3193   0.09379   0.08952  -0.0264   1.0000   0.0599
  -6.750  -0.3323   0.09396   0.08977  -0.0265   1.0000   0.0604
  -6.500  -0.3388   0.09404   0.08989  -0.0291   1.0000   0.0607
  -6.250  -0.3387   0.09238   0.08825  -0.0315   1.0000   0.0611
  -6.000  -0.3466   0.08707   0.08305  -0.0227   1.0000   0.0624
  -5.750  -0.3483   0.08452   0.08054  -0.0199   1.0000   0.0640
  -5.500  -0.3471   0.08228   0.07832  -0.0192   1.0000   0.0658
  -5.250  -0.3408   0.07986   0.07590  -0.0204   0.9997   0.0682
  -5.000  -0.2741   0.07557   0.07131  -0.0414   0.9927   0.0740
  -4.750  -0.2642   0.07067   0.06648  -0.0389   0.9884   0.0760
  -4.500  -0.2308   0.06677   0.06252  -0.0440   0.9837   0.0816
  -4.250  -0.1889   0.06259   0.05816  -0.0532   0.9772   0.0890
  -3.750  -0.1135   0.05519   0.05051  -0.0644   0.9651   0.1048
  -3.500  -0.0632   0.05144   0.04653  -0.0725   0.9586   0.1167
  -3.250  -0.0215   0.04842   0.04332  -0.0780   0.9508   0.1303
  -3.000   0.0207   0.04527   0.04003  -0.0829   0.9448   0.1456
  -2.750   0.0584   0.04265   0.03723  -0.0867   0.9381   0.1601
  -2.500   0.0963   0.04010   0.03456  -0.0902   0.9319   0.1766
  -2.250   0.1444   0.03741   0.03168  -0.0956   0.9283   0.2040
  -1.250   0.3229   0.02912   0.02141  -0.1075   0.9019   0.1277
  -1.000   0.3605   0.02663   0.01866  -0.1089   0.8954   0.1092
  -0.750   0.3964   0.02525   0.01695  -0.1098   0.8877   0.1060
  -0.500   0.4314   0.02414   0.01539  -0.1102   0.8801   0.1010
  -0.250   0.4651   0.02315   0.01425  -0.1105   0.8722   0.0993
   0.000   0.4940   0.02239   0.01341  -0.1102   0.8625   0.0991
   0.250   0.5276   0.02153   0.01245  -0.1102   0.8555   0.1002
   0.500   0.5533   0.02088   0.01191  -0.1092   0.8440   0.1037
   0.750   0.5803   0.02034   0.01138  -0.1080   0.8325   0.1109
   1.000   0.6084   0.01975   0.01078  -0.1067   0.8206   0.1285
   1.250   0.6368   0.01874   0.01003  -0.1052   0.8091   0.2111
   1.500   0.6660   0.01680   0.00937  -0.1041   0.7965   1.0000
   1.750   0.6906   0.01673   0.00912  -0.1025   0.7830   1.0000
   2.000   0.7154   0.01669   0.00896  -0.1012   0.7696   1.0000
   2.250   0.7404   0.01665   0.00882  -0.0998   0.7559   1.0000
   2.500   0.7654   0.01659   0.00867  -0.0985   0.7418   1.0000
   2.750   0.7905   0.01655   0.00854  -0.0973   0.7271   1.0000
   3.000   0.8158   0.01651   0.00844  -0.0960   0.7118   1.0000
   3.250   0.8412   0.01650   0.00838  -0.0949   0.6960   1.0000
   3.500   0.8667   0.01648   0.00829  -0.0938   0.6795   1.0000
   3.750   0.8921   0.01648   0.00822  -0.0927   0.6621   1.0000
   4.000   0.9170   0.01656   0.00830  -0.0918   0.6415   1.0000
   4.250   0.9425   0.01659   0.00831  -0.0908   0.6220   1.0000
   4.500   0.9678   0.01669   0.00836  -0.0899   0.6016   1.0000
   4.750   0.9928   0.01687   0.00849  -0.0890   0.5798   1.0000
   5.000   1.0180   0.01709   0.00864  -0.0882   0.5587   1.0000
   5.250   1.0427   0.01744   0.00896  -0.0874   0.5360   1.0000
   5.500   1.0675   0.01787   0.00930  -0.0866   0.5146   1.0000
   5.750   1.0915   0.01835   0.00972  -0.0858   0.4915   1.0000
   6.000   1.1150   0.01886   0.01016  -0.0849   0.4683   1.0000
   6.250   1.1381   0.01936   0.01061  -0.0840   0.4456   1.0000
   6.500   1.1602   0.01986   0.01112  -0.0830   0.4226   1.0000
   6.750   1.1829   0.02036   0.01165  -0.0821   0.4032   1.0000
   7.000   1.2037   0.02074   0.01209  -0.0810   0.3800   1.0000
   7.250   1.2225   0.02102   0.01248  -0.0796   0.3511   1.0000
   7.500   1.2382   0.02135   0.01285  -0.0777   0.3058   1.0000
   7.750   1.2474   0.02263   0.01367  -0.0751   0.2149   1.0000
   8.000   1.2445   0.02593   0.01582  -0.0717   0.0866   1.0000
   8.250   1.2523   0.02800   0.01791  -0.0692   0.0731   1.0000
   8.500   1.2560   0.03014   0.02013  -0.0662   0.0673   1.0000
   8.750   1.2641   0.03172   0.02191  -0.0636   0.0638   1.0000
   9.000   1.2679   0.03343   0.02376  -0.0606   0.0606   1.0000
   9.250   1.2695   0.03540   0.02574  -0.0577   0.0575   1.0000
   9.500   1.2754   0.03768   0.02796  -0.0551   0.0547   1.0000
   9.750   1.2944   0.03939   0.02973  -0.0535   0.0528   1.0000
  10.000   1.3271   0.04151   0.03189  -0.0533   0.0511   1.0000
  10.250   1.3622   0.04412   0.03459  -0.0538   0.0492   1.0000
  10.500   1.3883   0.04690   0.03748  -0.0536   0.0466   1.0000
  10.750   1.4163   0.05035   0.04115  -0.0535   0.0461   1.0000
  11.000   1.4337   0.05360   0.04479  -0.0519   0.0468   1.0000
  11.250   1.4371   0.05690   0.04865  -0.0491   0.0481   1.0000
  11.500   1.4357   0.06061   0.05285  -0.0461   0.0497   1.0000
  11.750   1.4324   0.06461   0.05724  -0.0433   0.0514   1.0000
  12.000   1.4269   0.06889   0.06183  -0.0408   0.0528   1.0000
  12.250   1.4226   0.07400   0.06718  -0.0389   0.0541   1.0000
  12.500   1.4354   0.07915   0.07254  -0.0382   0.0562   1.0000
  12.750   1.4049   0.08071   0.07445  -0.0345   0.0571   1.0000
  13.000   1.3650   0.08425   0.07837  -0.0330   0.0580   1.0000
  13.250   1.3273   0.08961   0.08408  -0.0336   0.0591   1.0000
  13.500   1.2949   0.09598   0.09072  -0.0358   0.0600   1.0000
  13.750   1.2638   0.10315   0.09811  -0.0392   0.0606   1.0000
  14.000   1.2328   0.11122   0.10636  -0.0440   0.0608   1.0000
  14.250   1.2011   0.12051   0.11580  -0.0503   0.0607   1.0000
  14.500   1.1654   0.13242   0.12783  -0.0590   0.0608   1.0000
  14.750   1.1229   0.14939   0.14480  -0.0711   0.0626   1.0000
  15.000   1.0990   0.16874   0.16412  -0.0809   0.0816   1.0000
  15.250   0.8722   0.14720   0.14281  -0.0531   0.0650   1.0000
  15.500   0.8674   0.15190   0.14751  -0.0543   0.0667   1.0000
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