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GOE 534 AIRFOIL (goe534-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 534 AIRFOIL (goe534-il)
Reynolds number: 100,000
Max Cl/Cd: 44.03 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe534-il-100000.txt
Download as CSV file: xf-goe534-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 534 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2184   0.10543   0.10037  -0.0262   1.0000   0.1357
  -9.000  -0.2360   0.10467   0.09972  -0.0285   1.0000   0.1412
  -8.750  -0.2518   0.10245   0.09763  -0.0300   1.0000   0.1429
  -8.500  -0.2184   0.09833   0.09351  -0.0268   1.0000   0.1457
  -8.250  -0.2106   0.09621   0.09146  -0.0256   1.0000   0.1497
  -8.000  -0.2245   0.09518   0.09058  -0.0256   1.0000   0.1548
  -7.750  -0.2783   0.09707   0.09274  -0.0228   1.0000   0.1564
  -7.500  -0.3179   0.09835   0.09419  -0.0167   1.0000   0.1565
  -7.250  -0.3037   0.09412   0.09001  -0.0169   0.9970   0.1584
  -7.000  -0.2549   0.08969   0.08555  -0.0185   0.9930   0.1629
  -6.750  -0.2436   0.08483   0.08068  -0.0370   0.9708   0.1734
  -6.500  -0.2001   0.08133   0.07718  -0.0332   0.9682   0.1775
  -6.250  -0.1735   0.07603   0.07183  -0.0496   0.9515   0.1904
  -6.000  -0.1386   0.07270   0.06851  -0.0476   0.9420   0.1939
  -5.750  -0.1154   0.05924   0.05475  -0.0756   0.9238   0.1735
  -5.500  -0.0742   0.05673   0.05226  -0.0758   0.9173   0.1765
  -5.250  -0.0410   0.05559   0.05112  -0.0762   0.9030   0.1951
  -5.000  -0.0263   0.02869   0.02175  -0.1072   0.8852   0.1575
  -4.750   0.0096   0.02842   0.02176  -0.1076   0.8709   0.1651
  -4.500   0.0440   0.02676   0.01960  -0.1091   0.8567   0.1738
  -4.250   0.0774   0.02612   0.01904  -0.1092   0.8420   0.1797
  -4.000   0.1048   0.02499   0.01763  -0.1088   0.8242   0.1833
  -3.750   0.1318   0.02396   0.01623  -0.1082   0.8067   0.1867
  -3.500   0.1587   0.02309   0.01502  -0.1075   0.7895   0.1898
  -3.250   0.1853   0.02238   0.01424  -0.1067   0.7731   0.1928
  -3.000   0.2128   0.02186   0.01357  -0.1059   0.7578   0.1965
  -2.750   0.2396   0.02141   0.01293  -0.1050   0.7422   0.2015
  -2.500   0.2655   0.02103   0.01233  -0.1041   0.7259   0.2068
  -2.250   0.2913   0.02064   0.01199  -0.1031   0.7111   0.2124
  -2.000   0.3190   0.02031   0.01151  -0.1023   0.6983   0.2203
  -1.750   0.3446   0.01998   0.01118  -0.1013   0.6836   0.2296
  -1.500   0.3705   0.01975   0.01094  -0.1004   0.6697   0.2448
  -1.250   0.3974   0.01952   0.01077  -0.0994   0.6578   0.2690
  -1.000   0.4225   0.01940   0.01079  -0.0983   0.6442   0.3096
  -0.750   0.4474   0.01952   0.01099  -0.0970   0.6313   0.3516
  -0.500   0.4745   0.01963   0.01099  -0.0960   0.6207   0.3838
  -0.250   0.4987   0.01981   0.01123  -0.0948   0.6073   0.4078
   0.000   0.5245   0.01996   0.01133  -0.0938   0.5959   0.4302
   0.250   0.5510   0.02004   0.01133  -0.0928   0.5849   0.4513
   0.500   0.5760   0.02020   0.01149  -0.0919   0.5729   0.4717
   0.750   0.6036   0.02030   0.01142  -0.0911   0.5633   0.4959
   1.000   0.6271   0.02042   0.01165  -0.0899   0.5509   0.5176
   1.250   0.6530   0.02049   0.01169  -0.0890   0.5407   0.5403
   1.500   0.6778   0.02054   0.01175  -0.0880   0.5293   0.5638
   1.750   0.7029   0.02066   0.01186  -0.0871   0.5187   0.5873
   2.000   0.7308   0.02068   0.01182  -0.0866   0.5081   0.6109
   2.250   0.7572   0.02079   0.01200  -0.0861   0.4966   0.6355
   2.500   0.7869   0.02077   0.01191  -0.0860   0.4868   0.6669
   2.750   0.8116   0.02073   0.01218  -0.0853   0.4751   0.7123
   3.000   0.8548   0.02052   0.01222  -0.0879   0.4640   1.0000
   3.250   0.8818   0.02094   0.01252  -0.0877   0.4525   1.0000
   3.500   0.9087   0.02142   0.01282  -0.0874   0.4426   1.0000
   3.750   0.9348   0.02182   0.01309  -0.0868   0.4325   1.0000
   4.000   0.9600   0.02234   0.01350  -0.0862   0.4230   1.0000
   4.250   0.9855   0.02273   0.01377  -0.0855   0.4134   1.0000
   4.500   1.0101   0.02327   0.01424  -0.0848   0.4044   1.0000
   4.750   1.0348   0.02371   0.01461  -0.0840   0.3954   1.0000
   5.000   1.0599   0.02425   0.01505  -0.0834   0.3875   1.0000
   5.250   1.0827   0.02476   0.01557  -0.0824   0.3786   1.0000
   5.500   1.1105   0.02522   0.01581  -0.0821   0.3718   1.0000
   5.750   1.1298   0.02591   0.01666  -0.0807   0.3629   1.0000
   6.000   1.1568   0.02629   0.01686  -0.0803   0.3562   1.0000
   6.250   1.1770   0.02707   0.01774  -0.0791   0.3486   1.0000
   6.500   1.2002   0.02759   0.01824  -0.0782   0.3415   1.0000
   6.750   1.2273   0.02814   0.01862  -0.0779   0.3356   1.0000
   7.000   1.2438   0.02900   0.01969  -0.0762   0.3279   1.0000
   7.250   1.2693   0.02944   0.02003  -0.0757   0.3219   1.0000
   7.500   1.2907   0.03029   0.02089  -0.0747   0.3158   1.0000
   7.750   1.3082   0.03113   0.02187  -0.0733   0.3091   1.0000
   8.000   1.3353   0.03156   0.02214  -0.0729   0.3036   1.0000
   8.250   1.3521   0.03265   0.02335  -0.0715   0.2976   1.0000
   8.500   1.3686   0.03353   0.02436  -0.0700   0.2914   1.0000
   8.750   1.3969   0.03395   0.02459  -0.0698   0.2861   1.0000
   9.000   1.4097   0.03525   0.02607  -0.0680   0.2805   1.0000
   9.250   1.4234   0.03628   0.02725  -0.0663   0.2746   1.0000
   9.500   1.4517   0.03668   0.02749  -0.0662   0.2694   1.0000
   9.750   1.4622   0.03812   0.02910  -0.0642   0.2643   1.0000
  10.000   1.4703   0.03945   0.03061  -0.0620   0.2588   1.0000
  10.250   1.4960   0.03990   0.03095  -0.0616   0.2537   1.0000
  10.500   1.5100   0.04125   0.03236  -0.0601   0.2489   1.0000
  10.750   1.5073   0.04306   0.03445  -0.0569   0.2440   1.0000
  11.000   1.5228   0.04392   0.03532  -0.0555   0.2392   1.0000
  11.250   1.5565   0.04450   0.03570  -0.0562   0.2342   1.0000
  11.500   1.5345   0.04706   0.03865  -0.0513   0.2306   1.0000
  11.750   1.5210   0.04918   0.04096  -0.0473   0.2269   1.0000
  12.000   1.5356   0.05002   0.04179  -0.0460   0.2227   1.0000
  12.250   1.5687   0.05070   0.04232  -0.0465   0.2180   1.0000
  12.500   1.5212   0.05471   0.04671  -0.0411   0.2161   1.0000
  12.750   1.4470   0.06228   0.05470  -0.0383   0.2146   1.0000
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