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GOE 280 (DAIMLER XI) AIRFOIL (goe280-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 280 (DAIMLER XI) AIRFOIL (goe280-il)
Reynolds number: 50,000
Max Cl/Cd: 41.08 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe280-il-50000-n5.txt
Download as CSV file: xf-goe280-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3241   0.10090   0.09462  -0.0236   1.0000   0.0615
  -7.250  -0.3243   0.09864   0.09247  -0.0248   1.0000   0.0634
  -7.000  -0.3244   0.09685   0.09077  -0.0276   1.0000   0.0651
  -6.750  -0.3217   0.09536   0.08933  -0.0321   1.0000   0.0661
  -6.500  -0.3148   0.09366   0.08762  -0.0367   1.0000   0.0666
  -6.250  -0.3141   0.08776   0.08187  -0.0306   1.0000   0.0685
  -6.000  -0.3102   0.08450   0.07867  -0.0288   1.0000   0.0714
  -5.750  -0.3045   0.08169   0.07590  -0.0294   1.0000   0.0749
  -5.500  -0.2880   0.08003   0.07411  -0.0367   1.0000   0.0808
  -5.250  -0.2842   0.07582   0.07002  -0.0350   1.0000   0.0833
  -5.000  -0.2784   0.07281   0.06706  -0.0334   1.0000   0.0900
  -4.750  -0.2615   0.06977   0.06394  -0.0375   1.0000   0.0979
  -4.250  -0.2373   0.06363   0.05778  -0.0385   1.0000   0.1151
  -4.000  -0.2198   0.06069   0.05475  -0.0406   1.0000   0.1281
  -3.750  -0.2042   0.05781   0.05181  -0.0415   1.0000   0.1435
  -3.500  -0.1809   0.05479   0.04869  -0.0442   0.9979   0.1718
  -3.250  -0.1548   0.05115   0.04512  -0.0464   0.9909   0.2321
  -2.750  -0.0147   0.04269   0.03493  -0.0644   0.9776   0.0941
  -2.500   0.0283   0.03939   0.03127  -0.0683   0.9698   0.0906
  -2.250   0.0780   0.03677   0.02791  -0.0720   0.9623   0.0795
  -2.000   0.1218   0.03422   0.02496  -0.0754   0.9544   0.0765
  -1.750   0.1650   0.03277   0.02287  -0.0780   0.9448   0.0806
  -1.500   0.2105   0.03084   0.02055  -0.0813   0.9376   0.0796
  -1.250   0.2500   0.02940   0.01878  -0.0834   0.9270   0.0786
  -1.000   0.2898   0.02819   0.01728  -0.0853   0.9164   0.0781
  -0.750   0.3306   0.02711   0.01593  -0.0873   0.9064   0.0781
  -0.500   0.3708   0.02622   0.01478  -0.0889   0.8960   0.0795
  -0.250   0.4057   0.02542   0.01388  -0.0899   0.8829   0.0861
   0.000   0.4399   0.02476   0.01310  -0.0906   0.8690   0.0901
   0.250   0.4735   0.02420   0.01240  -0.0911   0.8545   0.0917
   0.500   0.5066   0.02371   0.01176  -0.0915   0.8395   0.0938
   0.750   0.5362   0.02337   0.01133  -0.0914   0.8216   0.0964
   1.000   0.5670   0.02299   0.01089  -0.0915   0.8041   0.1011
   1.250   0.5983   0.02265   0.01048  -0.0915   0.7867   0.1093
   1.750   0.6529   0.02025   0.00987  -0.0897   0.7519   1.0000
   2.000   0.6810   0.02033   0.00969  -0.0890   0.7316   1.0000
   2.250   0.7094   0.02041   0.00952  -0.0883   0.7117   1.0000
   2.500   0.7365   0.02057   0.00947  -0.0876   0.6906   1.0000
   2.750   0.7628   0.02078   0.00953  -0.0868   0.6685   1.0000
   3.000   0.7887   0.02102   0.00964  -0.0860   0.6464   1.0000
   3.250   0.8140   0.02127   0.00978  -0.0852   0.6237   1.0000
   3.500   0.8388   0.02154   0.00994  -0.0843   0.5998   1.0000
   3.750   0.8636   0.02180   0.01008  -0.0832   0.5757   1.0000
   4.000   0.8876   0.02212   0.01028  -0.0822   0.5503   1.0000
   4.250   0.9112   0.02250   0.01055  -0.0812   0.5249   1.0000
   4.500   0.9349   0.02293   0.01091  -0.0803   0.5008   1.0000
   4.750   0.9581   0.02340   0.01134  -0.0794   0.4770   1.0000
   5.000   0.9812   0.02391   0.01184  -0.0786   0.4539   1.0000
   5.250   1.0041   0.02444   0.01236  -0.0777   0.4317   1.0000
   5.500   1.0266   0.02500   0.01301  -0.0769   0.4092   1.0000
   5.750   1.0489   0.02560   0.01361  -0.0760   0.3879   1.0000
   6.000   1.0708   0.02624   0.01430  -0.0751   0.3667   1.0000
   6.250   1.0924   0.02693   0.01502  -0.0742   0.3466   1.0000
   6.500   1.1136   0.02766   0.01579  -0.0733   0.3283   1.0000
   6.750   1.1307   0.02840   0.01647  -0.0719   0.3010   1.0000
   7.000   1.1442   0.02924   0.01711  -0.0701   0.2660   1.0000
   7.250   1.1606   0.03015   0.01795  -0.0689   0.2427   1.0000
   7.500   1.1774   0.03110   0.01888  -0.0676   0.2230   1.0000
   7.750   1.1948   0.03205   0.01996  -0.0665   0.2087   1.0000
   8.000   1.2112   0.03305   0.02104  -0.0653   0.1928   1.0000
   8.250   1.2271   0.03409   0.02217  -0.0640   0.1800   1.0000
   8.500   1.2437   0.03510   0.02339  -0.0627   0.1709   1.0000
   8.750   1.2589   0.03617   0.02463  -0.0613   0.1602   1.0000
   9.000   1.2713   0.03738   0.02595  -0.0598   0.1460   1.0000
   9.250   1.2816   0.03873   0.02736  -0.0580   0.1297   1.0000
   9.500   1.2927   0.03996   0.02881  -0.0562   0.1218   1.0000
   9.750   1.3023   0.04131   0.03046  -0.0543   0.1139   1.0000
  10.000   1.3134   0.04266   0.03213  -0.0526   0.1034   1.0000
  10.750   1.2878   0.05293   0.04190  -0.0472   0.0264   1.0000
  11.000   1.2812   0.05664   0.04580  -0.0465   0.0254   1.0000
  11.250   1.2735   0.06072   0.05010  -0.0463   0.0246   1.0000
  11.500   1.2645   0.06525   0.05487  -0.0468   0.0241   1.0000
  11.750   1.2544   0.07021   0.06008  -0.0479   0.0238   1.0000
  12.000   1.2429   0.07569   0.06582  -0.0495   0.0236   1.0000
  12.250   1.2306   0.08157   0.07195  -0.0515   0.0235   1.0000
  12.500   1.2173   0.08787   0.07850  -0.0540   0.0234   1.0000
  12.750   1.2036   0.09441   0.08529  -0.0566   0.0234   1.0000
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