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GOE 279 (DAIMLER X) AIRFOIL (goe279-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 279 (DAIMLER X) AIRFOIL (goe279-il)
Reynolds number: 1,000,000
Max Cl/Cd: 113.89 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe279-il-1000000.txt
Download as CSV file: xf-goe279-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2643   0.09586   0.09433  -0.0283   1.0000   0.0107
  -9.250  -0.2663   0.09310   0.09160  -0.0275   1.0000   0.0112
  -9.000  -0.2685   0.08983   0.08834  -0.0281   0.9996   0.0116
  -8.750  -0.2622   0.08540   0.08391  -0.0314   0.9983   0.0117
  -8.500  -0.2552   0.08096   0.07948  -0.0348   0.9968   0.0117
  -8.250  -0.2466   0.07656   0.07507  -0.0381   0.9952   0.0117
  -8.000  -0.2398   0.07146   0.06998  -0.0406   0.9934   0.0118
  -7.750  -0.2283   0.06786   0.06638  -0.0423   0.9908   0.0120
  -7.500  -0.2166   0.06413   0.06265  -0.0453   0.9879   0.0122
  -7.250  -0.2041   0.06015   0.05867  -0.0493   0.9842   0.0124
  -7.000  -0.1932   0.05618   0.05471  -0.0534   0.9759   0.0126
  -6.750  -0.1793   0.05190   0.05041  -0.0582   0.9688   0.0129
  -6.500  -0.1665   0.04777   0.04624  -0.0623   0.9588   0.0133
  -6.250  -0.1524   0.04351   0.04194  -0.0663   0.9483   0.0140
  -6.000  -0.1279   0.03713   0.03542  -0.0750   0.9393   0.0147
  -5.750  -0.1082   0.03247   0.03066  -0.0784   0.9307   0.0148
  -5.500  -0.0941   0.02772   0.02582  -0.0805   0.9217   0.0151
  -5.250  -0.0751   0.02525   0.02327  -0.0815   0.9138   0.0154
  -5.000  -0.0534   0.02276   0.02071  -0.0829   0.9061   0.0159
  -4.750  -0.0300   0.02006   0.01788  -0.0844   0.8992   0.0167
  -4.500   0.0035   0.01619   0.01372  -0.0868   0.8930   0.0184
  -4.250   0.0286   0.01295   0.01025  -0.0877   0.8864   0.0184
  -4.000   0.0500   0.00978   0.00688  -0.0889   0.8799   0.0190
  -3.750   0.0740   0.00885   0.00586  -0.0891   0.8718   0.0196
  -3.500   0.0997   0.00778   0.00465  -0.0894   0.8640   0.0209
  -3.250   0.1306   0.00632   0.00280  -0.0890   0.8571   0.0227
  -3.000   0.1608   0.01692   0.01296  -0.0938   0.8661   0.0217
  -2.750   0.1904   0.01378   0.00935  -0.0935   0.8584   0.0222
  -2.500   0.2183   0.01246   0.00779  -0.0935   0.8514   0.0239
  -2.250   0.2454   0.01290   0.00830  -0.0936   0.8423   0.0255
  -2.000   0.2740   0.01179   0.00697  -0.0934   0.8335   0.0267
  -1.500   0.3305   0.00996   0.00476  -0.0931   0.8136   0.0295
  -1.250   0.3581   0.00982   0.00462  -0.0931   0.8014   0.0310
  -1.000   0.3858   0.00923   0.00391  -0.0929   0.7829   0.0313
  -0.750   0.4131   0.00886   0.00341  -0.0926   0.7579   0.0321
  -0.500   0.4399   0.00869   0.00310  -0.0922   0.7212   0.0335
  -0.250   0.4655   0.00865   0.00280  -0.0917   0.6656   0.0342
   0.000   0.4917   0.00863   0.00257  -0.0913   0.6245   0.0347
   0.250   0.5185   0.00859   0.00241  -0.0910   0.5958   0.0351
   0.500   0.5457   0.00857   0.00228  -0.0909   0.5715   0.0357
   0.750   0.5731   0.00824   0.00187  -0.0909   0.5486   0.0376
   1.000   0.6005   0.00823   0.00177  -0.0908   0.5250   0.0388
   1.250   0.6280   0.00826   0.00171  -0.0907   0.5020   0.0400
   1.500   0.6552   0.00833   0.00168  -0.0906   0.4757   0.0413
   1.750   0.6821   0.00846   0.00168  -0.0904   0.4438   0.0430
   2.000   0.7086   0.00866   0.00174  -0.0902   0.4073   0.0447
   2.250   0.7352   0.00882   0.00174  -0.0901   0.3757   0.0492
   2.500   0.7618   0.00901   0.00181  -0.0899   0.3494   0.0546
   2.750   0.7823   0.00733   0.00210  -0.0889   0.3302   1.0000
   3.000   0.8093   0.00754   0.00219  -0.0888   0.3151   1.0000
   3.250   0.8366   0.00771   0.00229  -0.0887   0.3035   1.0000
   3.500   0.8639   0.00787   0.00240  -0.0886   0.2941   1.0000
   3.750   0.8910   0.00805   0.00253  -0.0885   0.2844   1.0000
   4.000   0.9183   0.00819   0.00264  -0.0885   0.2755   1.0000
   4.250   0.9453   0.00838   0.00277  -0.0884   0.2657   1.0000
   4.500   0.9721   0.00857   0.00291  -0.0882   0.2540   1.0000
   4.750   0.9988   0.00877   0.00307  -0.0881   0.2411   1.0000
   5.000   1.0251   0.00902   0.00323  -0.0879   0.2251   1.0000
   5.250   1.0509   0.00932   0.00343  -0.0877   0.2020   1.0000
   5.500   1.0753   0.00979   0.00372  -0.0872   0.1679   1.0000
   5.750   1.0993   0.01031   0.00406  -0.0867   0.1375   1.0000
   6.000   1.1243   0.01068   0.00436  -0.0864   0.1233   1.0000
   6.250   1.1495   0.01102   0.00464  -0.0861   0.1130   1.0000
   6.500   1.1745   0.01138   0.00496  -0.0857   0.1019   1.0000
   6.750   1.1985   0.01184   0.00530  -0.0852   0.0784   1.0000
   7.000   1.2190   0.01275   0.00596  -0.0842   0.0422   1.0000
   7.250   1.2431   0.01319   0.00639  -0.0836   0.0379   1.0000
   7.500   1.2674   0.01358   0.00682  -0.0831   0.0360   1.0000
   7.750   1.2920   0.01392   0.00720  -0.0827   0.0352   1.0000
   8.000   1.3161   0.01429   0.00762  -0.0822   0.0340   1.0000
   8.250   1.3396   0.01471   0.00810  -0.0816   0.0327   1.0000
   8.500   1.3624   0.01520   0.00862  -0.0809   0.0313   1.0000
   8.750   1.3842   0.01579   0.00926  -0.0800   0.0295   1.0000
   9.000   1.4040   0.01657   0.01014  -0.0789   0.0278   1.0000
   9.250   1.4274   0.01690   0.01051  -0.0783   0.0273   1.0000
   9.500   1.4501   0.01728   0.01093  -0.0777   0.0265   1.0000
   9.750   1.4723   0.01769   0.01139  -0.0770   0.0254   1.0000
  10.000   1.4939   0.01814   0.01186  -0.0762   0.0241   1.0000
  10.250   1.5136   0.01874   0.01250  -0.0751   0.0227   1.0000
  10.500   1.5288   0.01971   0.01356  -0.0733   0.0211   1.0000
  10.750   1.5520   0.01991   0.01379  -0.0728   0.0204   1.0000
  11.000   1.5737   0.02022   0.01412  -0.0721   0.0191   1.0000
  11.250   1.5943   0.02060   0.01450  -0.0712   0.0177   1.0000
  11.500   1.6093   0.02140   0.01533  -0.0695   0.0161   1.0000
  11.750   1.6279   0.02183   0.01581  -0.0683   0.0151   1.0000
  12.000   1.6433   0.02236   0.01636  -0.0665   0.0140   1.0000
  12.250   1.6537   0.02318   0.01721  -0.0640   0.0128   1.0000
  12.500   1.6630   0.02410   0.01821  -0.0615   0.0120   1.0000
  12.750   1.6742   0.02492   0.01911  -0.0594   0.0113   1.0000
  13.000   1.6841   0.02585   0.02010  -0.0573   0.0107   1.0000
  13.250   1.6913   0.02702   0.02132  -0.0550   0.0100   1.0000
  13.500   1.6895   0.02891   0.02332  -0.0519   0.0093   1.0000
  13.750   1.6977   0.03010   0.02461  -0.0501   0.0090   1.0000
  14.000   1.7033   0.03158   0.02620  -0.0482   0.0087   1.0000
  14.250   1.7070   0.03328   0.02799  -0.0465   0.0084   1.0000
  14.500   1.7094   0.03519   0.03001  -0.0449   0.0081   1.0000
  14.750   1.7101   0.03736   0.03228  -0.0435   0.0078   1.0000
  15.000   1.7079   0.03994   0.03497  -0.0422   0.0076   1.0000
  15.250   1.7021   0.04310   0.03825  -0.0413   0.0073   1.0000
  15.500   1.6913   0.04708   0.04236  -0.0409   0.0071   1.0000
  15.750   1.6760   0.05206   0.04750  -0.0413   0.0070   1.0000
  16.000   1.6581   0.05785   0.05346  -0.0425   0.0069   1.0000
  16.250   1.6463   0.06307   0.05883  -0.0440   0.0068   1.0000
  16.500   1.6345   0.06849   0.06439  -0.0458   0.0067   1.0000
  16.750   1.6193   0.07457   0.07061  -0.0479   0.0067   1.0000
  17.000   1.6008   0.08133   0.07751  -0.0504   0.0067   1.0000
  17.250   1.5823   0.08825   0.08458  -0.0531   0.0066   1.0000
  17.500   1.5608   0.09575   0.09222  -0.0560   0.0066   1.0000
  17.750   1.5403   0.10320   0.09979  -0.0591   0.0066   1.0000
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