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GOE 275 (DAIMLER VI) AIRFOIL (goe275-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 275 (DAIMLER VI) AIRFOIL (goe275-il)
Reynolds number: 500,000
Max Cl/Cd: 99.72 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe275-il-500000.txt
Download as CSV file: xf-goe275-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 275 (DAIMLER VI) AIRFOIL                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3323   0.09046   0.08831  -0.0197   1.0000   0.0178
  -7.500  -0.3425   0.08898   0.08690  -0.0172   1.0000   0.0183
  -7.250  -0.3496   0.08725   0.08520  -0.0161   0.9991   0.0185
  -7.000  -0.3145   0.08133   0.07926  -0.0292   0.9942   0.0195
  -6.750  -0.2754   0.07439   0.07224  -0.0462   0.9879   0.0197
  -6.500  -0.2519   0.06923   0.06706  -0.0511   0.9853   0.0198
  -6.250  -0.2329   0.06594   0.06378  -0.0525   0.9822   0.0201
  -6.000  -0.2094   0.06244   0.06026  -0.0564   0.9774   0.0205
  -5.750  -0.1773   0.05831   0.05608  -0.0629   0.9741   0.0211
  -5.500  -0.1456   0.05414   0.05183  -0.0691   0.9696   0.0220
  -5.250  -0.0884   0.04718   0.04446  -0.0815   0.9632   0.0236
  -5.000  -0.0624   0.04261   0.03988  -0.0850   0.9604   0.0239
  -4.750  -0.0383   0.03998   0.03722  -0.0866   0.9538   0.0242
  -4.500  -0.0078   0.03725   0.03441  -0.0895   0.9492   0.0249
  -4.250   0.0294   0.03416   0.03117  -0.0933   0.9460   0.0260
  -4.000   0.0719   0.03130   0.02767  -0.0952   0.9386   0.0283
  -3.750   0.1004   0.02711   0.02347  -0.0978   0.9335   0.0289
  -3.500   0.1300   0.02518   0.02149  -0.0995   0.9265   0.0294
  -3.250   0.1626   0.02337   0.01954  -0.1012   0.9190   0.0304
  -3.000   0.1939   0.02170   0.01765  -0.1019   0.9098   0.0323
  -2.750   0.2281   0.01981   0.01524  -0.1024   0.9005   0.0347
  -2.500   0.2540   0.01828   0.01366  -0.1025   0.8874   0.0355
  -2.250   0.2803   0.01721   0.01246  -0.1023   0.8717   0.0367
  -2.000   0.3070   0.01644   0.01147  -0.1017   0.8547   0.0392
  -1.750   0.3331   0.01557   0.01022  -0.1007   0.8369   0.0422
  -1.500   0.3574   0.01447   0.00908  -0.1001   0.8170   0.0436
  -1.250   0.3824   0.01390   0.00837  -0.0993   0.7929   0.0464
  -1.000   0.4071   0.01340   0.00755  -0.0982   0.7621   0.0520
  -0.750   0.4301   0.01277   0.00678  -0.0972   0.7224   0.0547
  -0.500   0.4536   0.01373   0.00741  -0.0956   0.6766   0.0610
  -0.250   0.4748   0.01216   0.00568  -0.0946   0.6391   0.0683
   0.000   0.4974   0.01183   0.00517  -0.0936   0.6039   0.0809
   1.250   0.6192   0.01138   0.00364  -0.0877   0.4372   0.0503
   1.500   0.6427   0.01093   0.00312  -0.0867   0.4146   0.0467
   1.750   0.6672   0.01086   0.00296  -0.0859   0.3961   0.0453
   2.000   0.6919   0.01085   0.00286  -0.0852   0.3808   0.0450
   2.250   0.7170   0.01087   0.00281  -0.0845   0.3687   0.0453
   2.500   0.7423   0.01091   0.00281  -0.0839   0.3600   0.0469
   2.750   0.7681   0.01093   0.00282  -0.0834   0.3527   0.0480
   3.000   0.7937   0.01100   0.00285  -0.0829   0.3460   0.0485
   3.250   0.8193   0.01109   0.00290  -0.0824   0.3398   0.0498
   3.500   0.8454   0.01116   0.00295  -0.0819   0.3341   0.0533
   3.750   0.8781   0.00962   0.00330  -0.0835   0.3276   1.0000
   4.000   0.9038   0.00975   0.00340  -0.0830   0.3216   1.0000
   4.250   0.9291   0.00992   0.00352  -0.0824   0.3151   1.0000
   4.500   0.9542   0.01012   0.00367  -0.0819   0.3092   1.0000
   4.750   0.9799   0.01025   0.00381  -0.0814   0.3032   1.0000
   5.000   1.0047   0.01046   0.00398  -0.0808   0.2966   1.0000
   5.250   1.0303   0.01059   0.00413  -0.0803   0.2901   1.0000
   5.500   1.0551   0.01079   0.00429  -0.0797   0.2812   1.0000
   5.750   1.0805   0.01093   0.00446  -0.0792   0.2717   1.0000
   6.000   1.1053   0.01112   0.00463  -0.0786   0.2608   1.0000
   6.250   1.1298   0.01133   0.00481  -0.0780   0.2473   1.0000
   6.500   1.1539   0.01158   0.00502  -0.0773   0.2300   1.0000
   7.000   1.1990   0.01235   0.00559  -0.0756   0.1904   1.0000
   7.250   1.2210   0.01279   0.00596  -0.0746   0.1775   1.0000
   7.500   1.2427   0.01324   0.00638  -0.0736   0.1666   1.0000
   7.750   1.2647   0.01366   0.00678  -0.0727   0.1545   1.0000
   8.000   1.2862   0.01412   0.00720  -0.0717   0.1387   1.0000
   8.250   1.3075   0.01461   0.00760  -0.0707   0.1172   1.0000
   8.750   1.3465   0.01583   0.00866  -0.0682   0.0921   1.0000
   9.000   1.3649   0.01648   0.00929  -0.0667   0.0864   1.0000
   9.250   1.3853   0.01693   0.00981  -0.0656   0.0838   1.0000
   9.500   1.4044   0.01745   0.01041  -0.0642   0.0810   1.0000
   9.750   1.4217   0.01808   0.01108  -0.0627   0.0781   1.0000
  10.000   1.4361   0.01888   0.01190  -0.0606   0.0745   1.0000
  10.250   1.4558   0.01926   0.01237  -0.0594   0.0721   1.0000
  10.500   1.4749   0.01963   0.01284  -0.0582   0.0692   1.0000
  10.750   1.4909   0.02013   0.01338  -0.0564   0.0660   1.0000
  11.000   1.5014   0.02092   0.01420  -0.0538   0.0622   1.0000
  11.250   1.5237   0.02103   0.01441  -0.0530   0.0580   1.0000
  11.500   1.5399   0.02151   0.01487  -0.0514   0.0502   1.0000
  11.750   1.5488   0.02245   0.01564  -0.0489   0.0321   1.0000
  12.000   1.5493   0.02390   0.01701  -0.0452   0.0227   1.0000
  12.250   1.5541   0.02508   0.01826  -0.0424   0.0203   1.0000
  12.500   1.5556   0.02653   0.01978  -0.0393   0.0185   1.0000
  12.750   1.5580   0.02798   0.02135  -0.0366   0.0175   1.0000
  13.000   1.5607   0.02947   0.02296  -0.0342   0.0169   1.0000
  13.250   1.5610   0.03122   0.02484  -0.0320   0.0162   1.0000
  13.500   1.5585   0.03332   0.02705  -0.0299   0.0156   1.0000
  13.750   1.5533   0.03582   0.02968  -0.0281   0.0151   1.0000
  14.000   1.5445   0.03889   0.03287  -0.0267   0.0147   1.0000
  14.250   1.5332   0.04254   0.03667  -0.0260   0.0144   1.0000
  14.500   1.5219   0.04660   0.04087  -0.0260   0.0141   1.0000
  14.750   1.5160   0.05036   0.04478  -0.0265   0.0139   1.0000
  15.000   1.5078   0.05467   0.04923  -0.0275   0.0137   1.0000
  15.250   1.4986   0.05933   0.05404  -0.0289   0.0134   1.0000
  15.500   1.4867   0.06462   0.05947  -0.0307   0.0133   1.0000
  15.750   1.4734   0.07028   0.06528  -0.0329   0.0132   1.0000
  16.000   1.4613   0.07594   0.07107  -0.0351   0.0130   1.0000
  16.250   1.4476   0.08196   0.07721  -0.0376   0.0129   1.0000
  16.500   1.4342   0.08806   0.08344  -0.0402   0.0127   1.0000
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