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GOE 280 (DAIMLER XI) AIRFOIL (goe280-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 280 (DAIMLER XI) AIRFOIL (goe280-il)
Reynolds number: 200,000
Max Cl/Cd: 70.19 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe280-il-200000-n5.txt
Download as CSV file: xf-goe280-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 280 (DAIMLER XI) AIRFOIL                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3238   0.09906   0.09588  -0.0254   1.0000   0.0180
  -7.500  -0.3254   0.09666   0.09354  -0.0257   1.0000   0.0180
  -7.250  -0.3269   0.09423   0.09116  -0.0259   1.0000   0.0181
  -6.750  -0.3070   0.08715   0.08410  -0.0321   0.9963   0.0181
  -6.500  -0.2776   0.08212   0.07903  -0.0402   0.9912   0.0182
  -6.250  -0.2454   0.07701   0.07383  -0.0480   0.9868   0.0183
  -6.000  -0.2166   0.07197   0.06872  -0.0541   0.9813   0.0183
  -5.750  -0.1855   0.06663   0.06329  -0.0602   0.9774   0.0183
  -5.500  -0.1670   0.06131   0.05797  -0.0629   0.9716   0.0178
  -5.250  -0.1429   0.05667   0.05328  -0.0665   0.9667   0.0168
  -5.000  -0.1117   0.05211   0.04861  -0.0716   0.9602   0.0163
  -4.750  -0.0760   0.04747   0.04380  -0.0770   0.9547   0.0163
  -4.500  -0.0276   0.04261   0.03851  -0.0826   0.9491   0.0182
  -4.000   0.0335   0.03450   0.02999  -0.0883   0.9363   0.0192
  -3.750   0.0611   0.03255   0.02792  -0.0895   0.9279   0.0204
  -3.500   0.0923   0.03053   0.02569  -0.0908   0.9200   0.0237
  -3.250   0.1261   0.02750   0.02228  -0.0918   0.9119   0.0247
  -3.000   0.1595   0.02483   0.01908  -0.0923   0.9025   0.0285
  -2.750   0.1855   0.02371   0.01794  -0.0929   0.8925   0.0319
  -2.500   0.2160   0.02175   0.01563  -0.0930   0.8819   0.0327
  -2.250   0.2453   0.02051   0.01406  -0.0928   0.8695   0.0361
  -2.000   0.2745   0.01929   0.01251  -0.0926   0.8561   0.0372
  -1.750   0.3031   0.01819   0.01112  -0.0923   0.8414   0.0377
  -1.500   0.3314   0.01740   0.01004  -0.0919   0.8248   0.0394
  -1.250   0.3589   0.01612   0.00858  -0.0918   0.8060   0.0410
  -1.000   0.3866   0.01555   0.00777  -0.0913   0.7859   0.0400
  -0.750   0.4140   0.01508   0.00709  -0.0908   0.7655   0.0395
  -0.500   0.4413   0.01460   0.00643  -0.0903   0.7446   0.0393
  -0.250   0.4683   0.01411   0.00576  -0.0899   0.7242   0.0394
   0.000   0.4953   0.01362   0.00514  -0.0896   0.7011   0.0399
   0.250   0.5219   0.01324   0.00464  -0.0892   0.6745   0.0409
   0.500   0.5486   0.01301   0.00429  -0.0889   0.6439   0.0421
   0.750   0.5753   0.01288   0.00403  -0.0887   0.6112   0.0433
   1.000   0.6017   0.01288   0.00388  -0.0884   0.5788   0.0465
   1.250   0.6282   0.01294   0.00376  -0.0882   0.5500   0.0491
   1.500   0.6548   0.01301   0.00366  -0.0880   0.5243   0.0493
   1.750   0.6816   0.01313   0.00360  -0.0878   0.5021   0.0495
   2.000   0.7086   0.01324   0.00359  -0.0877   0.4829   0.0499
   2.250   0.7358   0.01335   0.00361  -0.0877   0.4668   0.0505
   2.500   0.7628   0.01348   0.00365  -0.0876   0.4506   0.0515
   2.750   0.7898   0.01363   0.00374  -0.0875   0.4342   0.0542
   3.000   0.8166   0.01377   0.00386  -0.0873   0.4173   0.0657
   3.250   0.8359   0.01217   0.00402  -0.0857   0.4015   1.0000
   3.500   0.8624   0.01243   0.00418  -0.0855   0.3829   1.0000
   3.750   0.8887   0.01271   0.00436  -0.0854   0.3632   1.0000
   4.000   0.9146   0.01303   0.00457  -0.0852   0.3420   1.0000
   4.500   0.9652   0.01381   0.00511  -0.0847   0.2892   1.0000
   5.000   1.0122   0.01504   0.00585  -0.0839   0.2127   1.0000
   5.250   1.0352   0.01571   0.00630  -0.0835   0.1766   1.0000
   5.500   1.0575   0.01647   0.00677  -0.0830   0.1414   1.0000
   5.750   1.0799   0.01719   0.00726  -0.0825   0.1144   1.0000
   6.000   1.1006   0.01813   0.00785  -0.0817   0.0623   1.0000
   6.250   1.1186   0.01944   0.00887  -0.0805   0.0214   1.0000
   6.500   1.1420   0.01996   0.00947  -0.0799   0.0167   1.0000
   6.750   1.1654   0.02048   0.01011  -0.0793   0.0152   1.0000
   7.000   1.1877   0.02112   0.01092  -0.0785   0.0136   1.0000
   7.250   1.2093   0.02184   0.01181  -0.0776   0.0125   1.0000
   7.500   1.2300   0.02264   0.01284  -0.0765   0.0117   1.0000
   7.750   1.2491   0.02361   0.01401  -0.0753   0.0111   1.0000
   8.000   1.2639   0.02505   0.01573  -0.0735   0.0103   1.0000
   8.250   1.2813   0.02603   0.01687  -0.0721   0.0095   1.0000
   8.500   1.2976   0.02706   0.01807  -0.0706   0.0090   1.0000
   8.750   1.3108   0.02827   0.01945  -0.0686   0.0087   1.0000
   9.000   1.3207   0.02961   0.02094  -0.0663   0.0085   1.0000
   9.250   1.3265   0.03105   0.02257  -0.0635   0.0083   1.0000
   9.500   1.3277   0.03260   0.02424  -0.0600   0.0082   1.0000
   9.750   1.3280   0.03438   0.02612  -0.0569   0.0081   1.0000
  10.000   1.3277   0.03636   0.02820  -0.0541   0.0080   1.0000
  10.250   1.3276   0.03852   0.03045  -0.0517   0.0079   1.0000
  10.500   1.3272   0.04085   0.03288  -0.0497   0.0078   1.0000
  10.750   1.3260   0.04342   0.03549  -0.0479   0.0075   1.0000
  11.000   1.3254   0.04613   0.03820  -0.0463   0.0072   1.0000
  11.250   1.3313   0.04888   0.04078  -0.0442   0.0068   1.0000
  11.500   1.3312   0.05125   0.04345  -0.0436   0.0066   1.0000
  11.750   1.3347   0.05373   0.04609  -0.0428   0.0064   1.0000
  12.000   1.3394   0.05625   0.04872  -0.0418   0.0063   1.0000
  12.250   1.3441   0.05884   0.05144  -0.0409   0.0062   1.0000
  12.500   1.3480   0.06160   0.05433  -0.0401   0.0062   1.0000
  12.750   1.3506   0.06454   0.05746  -0.0395   0.0062   1.0000
  13.000   1.3516   0.06772   0.06081  -0.0390   0.0061   1.0000
  13.250   1.3509   0.07117   0.06443  -0.0388   0.0061   1.0000
  13.500   1.3481   0.07491   0.06835  -0.0389   0.0061   1.0000
  13.750   1.3438   0.07890   0.07253  -0.0393   0.0062   1.0000
  14.000   1.3382   0.08315   0.07697  -0.0400   0.0062   1.0000
  14.250   1.3311   0.08772   0.08172  -0.0411   0.0062   1.0000
  14.500   1.3236   0.09246   0.08665  -0.0425   0.0062   1.0000
  14.750   1.3152   0.09749   0.09186  -0.0442   0.0063   1.0000
  15.000   1.3063   0.10279   0.09734  -0.0463   0.0063   1.0000
  15.250   1.2972   0.10827   0.10299  -0.0487   0.0063   1.0000
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