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GOE 279 (DAIMLER X) AIRFOIL (goe279-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 279 (DAIMLER X) AIRFOIL (goe279-il)
Reynolds number: 500,000
Max Cl/Cd: 96.88 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe279-il-500000.txt
Download as CSV file: xf-goe279-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 279 (DAIMLER X) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3446   0.09219   0.08999  -0.0244   1.0000   0.0158
  -7.750  -0.3554   0.09088   0.08874  -0.0215   1.0000   0.0160
  -7.500  -0.3763   0.09043   0.08837  -0.0165   1.0000   0.0161
  -7.250  -0.3568   0.08624   0.08417  -0.0223   0.9972   0.0167
  -7.000  -0.3314   0.08148   0.07940  -0.0302   0.9945   0.0174
  -6.750  -0.2984   0.07606   0.07394  -0.0418   0.9897   0.0182
  -6.500  -0.2559   0.06966   0.06744  -0.0563   0.9860   0.0184
  -6.250  -0.2219   0.06364   0.06133  -0.0649   0.9841   0.0185
  -6.000  -0.2080   0.06017   0.05788  -0.0653   0.9800   0.0188
  -5.750  -0.1822   0.05677   0.05445  -0.0689   0.9770   0.0193
  -5.500  -0.1494   0.05297   0.05057  -0.0744   0.9748   0.0201
  -5.250  -0.1097   0.04859   0.04608  -0.0812   0.9730   0.0217
  -5.000  -0.0545   0.04340   0.04049  -0.0893   0.9698   0.0228
  -4.750  -0.0329   0.03873   0.03576  -0.0917   0.9638   0.0233
  -4.500  -0.0044   0.03612   0.03310  -0.0940   0.9598   0.0239
  -4.250   0.0244   0.03364   0.03051  -0.0957   0.9550   0.0248
  -0.750   0.1541   0.00265   0.00022  -0.0531   0.8601   0.0475
  -0.500   0.4442   0.01089   0.00493  -0.0947   0.8305   0.0522
  -0.250   0.4719   0.01010   0.00396  -0.0940   0.8158   0.0465
   0.000   0.4988   0.00971   0.00349  -0.0935   0.7967   0.0463
   0.250   0.5254   0.00931   0.00305  -0.0930   0.7736   0.0475
   0.500   0.5520   0.00907   0.00273  -0.0926   0.7448   0.0488
   0.750   0.5780   0.00894   0.00245  -0.0920   0.7040   0.0497
   1.000   0.6030   0.00900   0.00227  -0.0913   0.6564   0.0509
   1.250   0.6284   0.00913   0.00219  -0.0907   0.6175   0.0524
   1.500   0.6544   0.00926   0.00216  -0.0903   0.5867   0.0547
   1.750   0.6810   0.00931   0.00211  -0.0900   0.5614   0.0574
   2.000   0.7077   0.00939   0.00208  -0.0898   0.5370   0.0625
   2.250   0.7343   0.00950   0.00210  -0.0895   0.5100   0.0723
   2.500   0.7537   0.00778   0.00230  -0.0881   0.4820   1.0000
   2.750   0.7794   0.00809   0.00240  -0.0877   0.4459   1.0000
   3.000   0.8051   0.00841   0.00252  -0.0873   0.4123   1.0000
   3.250   0.8306   0.00874   0.00268  -0.0869   0.3821   1.0000
   3.500   0.8560   0.00909   0.00285  -0.0866   0.3572   1.0000
   3.750   0.8821   0.00937   0.00304  -0.0863   0.3398   1.0000
   4.000   0.9083   0.00963   0.00322  -0.0861   0.3261   1.0000
   4.250   0.9346   0.00987   0.00341  -0.0859   0.3147   1.0000
   4.500   0.9611   0.01008   0.00359  -0.0857   0.3047   1.0000
   4.750   0.9873   0.01031   0.00380  -0.0854   0.2949   1.0000
   5.000   1.0135   0.01055   0.00401  -0.0852   0.2845   1.0000
   5.250   1.0398   0.01076   0.00420  -0.0850   0.2728   1.0000
   5.500   1.0658   0.01101   0.00443  -0.0848   0.2592   1.0000
   5.750   1.0916   0.01127   0.00465  -0.0845   0.2447   1.0000
   6.000   1.1168   0.01157   0.00489  -0.0842   0.2267   1.0000
   6.250   1.1416   0.01193   0.00516  -0.0838   0.2039   1.0000
   6.500   1.1655   0.01239   0.00550  -0.0833   0.1765   1.0000
   6.750   1.1886   0.01293   0.00591  -0.0827   0.1511   1.0000
   7.000   1.2116   0.01349   0.00635  -0.0820   0.1319   1.0000
   7.250   1.2349   0.01399   0.00680  -0.0814   0.1182   1.0000
   7.500   1.2575   0.01455   0.00731  -0.0807   0.1016   1.0000
   7.750   1.2775   0.01542   0.00791  -0.0797   0.0598   1.0000
   8.000   1.2980   0.01621   0.00862  -0.0786   0.0487   1.0000
   8.250   1.3198   0.01681   0.00927  -0.0778   0.0447   1.0000
   8.500   1.3416   0.01739   0.00994  -0.0769   0.0426   1.0000
   8.750   1.3619   0.01809   0.01070  -0.0758   0.0403   1.0000
   9.000   1.3803   0.01895   0.01162  -0.0745   0.0380   1.0000
   9.250   1.3965   0.01995   0.01273  -0.0728   0.0359   1.0000
   9.500   1.4161   0.02058   0.01346  -0.0716   0.0349   1.0000
   9.750   1.4339   0.02132   0.01429  -0.0702   0.0333   1.0000
  10.000   1.4500   0.02216   0.01521  -0.0686   0.0316   1.0000
  10.250   1.4625   0.02323   0.01635  -0.0665   0.0299   1.0000
  10.500   1.4621   0.02505   0.01829  -0.0624   0.0282   1.0000
  10.750   1.4745   0.02585   0.01920  -0.0603   0.0272   1.0000
  11.000   1.4884   0.02656   0.02001  -0.0584   0.0258   1.0000
  11.250   1.4999   0.02744   0.02097  -0.0564   0.0243   1.0000
  11.500   1.5090   0.02851   0.02210  -0.0543   0.0231   1.0000
  11.750   1.5097   0.03027   0.02394  -0.0514   0.0220   1.0000
  12.000   1.5067   0.03249   0.02628  -0.0483   0.0210   1.0000
  12.250   1.5187   0.03348   0.02741  -0.0470   0.0201   1.0000
  12.500   1.5273   0.03480   0.02884  -0.0455   0.0191   1.0000
  12.750   1.5357   0.03617   0.03029  -0.0442   0.0181   1.0000
  13.000   1.5428   0.03772   0.03190  -0.0431   0.0173   1.0000
  13.250   1.5391   0.04040   0.03466  -0.0415   0.0166   1.0000
  13.500   1.5339   0.04342   0.03782  -0.0402   0.0160   1.0000
  13.750   1.5369   0.04575   0.04030  -0.0395   0.0155   1.0000
  14.000   1.5367   0.04853   0.04324  -0.0391   0.0150   1.0000
  14.250   1.5354   0.05162   0.04646  -0.0390   0.0145   1.0000
  14.500   1.5334   0.05496   0.04991  -0.0393   0.0140   1.0000
  14.750   1.5305   0.05859   0.05367  -0.0399   0.0137   1.0000
  15.000   1.5261   0.06260   0.05778  -0.0409   0.0134   1.0000
  15.250   1.5192   0.06709   0.06238  -0.0422   0.0131   1.0000
  15.500   1.5089   0.07213   0.06753  -0.0437   0.0128   1.0000
  15.750   1.4948   0.07774   0.07327  -0.0452   0.0126   1.0000
  16.000   1.4775   0.08383   0.07949  -0.0467   0.0124   1.0000
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