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GOE 279 (DAIMLER X) AIRFOIL (goe279-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 279 (DAIMLER X) AIRFOIL (goe279-il)
Reynolds number: 100,000
Max Cl/Cd: 59.05 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe279-il-100000-n5.txt
Download as CSV file: xf-goe279-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3400   0.11021   0.10538  -0.0305   1.0000   0.0308
  -8.250  -0.3459   0.10849   0.10375  -0.0296   1.0000   0.0308
  -8.000  -0.3486   0.10640   0.10173  -0.0297   1.0000   0.0308
  -7.750  -0.3506   0.10423   0.09962  -0.0300   1.0000   0.0309
  -7.500  -0.3516   0.10199   0.09743  -0.0305   1.0000   0.0309
  -7.250  -0.3505   0.09654   0.09205  -0.0255   1.0000   0.0315
  -7.000  -0.3492   0.09320   0.08876  -0.0221   1.0000   0.0323
  -6.750  -0.3505   0.09081   0.08641  -0.0208   1.0000   0.0330
  -6.500  -0.3513   0.08847   0.08412  -0.0203   1.0000   0.0337
  -6.250  -0.3506   0.08604   0.08173  -0.0203   1.0000   0.0344
  -6.000  -0.3283   0.08197   0.07762  -0.0259   0.9961   0.0357
  -5.750  -0.2968   0.07733   0.07291  -0.0337   0.9902   0.0373
  -5.500  -0.2592   0.07273   0.06821  -0.0432   0.9846   0.0394
  -5.250  -0.2092   0.06854   0.06374  -0.0556   0.9786   0.0407
  -5.000  -0.1710   0.06451   0.05947  -0.0625   0.9736   0.0410
  -4.750  -0.1472   0.05926   0.05419  -0.0656   0.9691   0.0416
  -4.500  -0.1295   0.05542   0.05044  -0.0664   0.9659   0.0441
  -4.250  -0.0996   0.05219   0.04708  -0.0699   0.9603   0.0480
  -4.000  -0.0417   0.04961   0.04380  -0.0780   0.9553   0.0523
  -3.750  -0.0138   0.04441   0.03867  -0.0812   0.9525   0.0537
  -3.500   0.0115   0.04152   0.03572  -0.0826   0.9462   0.0560
  -3.000   0.0994   0.03565   0.02881  -0.0894   0.9386   0.0520
  -2.750   0.1287   0.03204   0.02516  -0.0912   0.9333   0.0465
  -2.500   0.1657   0.02986   0.02259  -0.0931   0.9280   0.0492
  -2.250   0.2076   0.02743   0.01973  -0.0957   0.9244   0.0483
  -2.000   0.2450   0.02566   0.01752  -0.0972   0.9180   0.0499
  -1.750   0.2841   0.02424   0.01561  -0.0986   0.9108   0.0518
  -1.500   0.3209   0.02283   0.01385  -0.0997   0.9023   0.0522
  -1.250   0.3584   0.02116   0.01213  -0.1015   0.8935   0.0561
  -1.000   0.3900   0.02015   0.01096  -0.1016   0.8819   0.0576
  -0.750   0.4220   0.01923   0.00990  -0.1018   0.8714   0.0583
  -0.500   0.4560   0.01839   0.00896  -0.1025   0.8629   0.0594
  -0.250   0.4840   0.01788   0.00839  -0.1020   0.8506   0.0628
   0.000   0.5125   0.01731   0.00780  -0.1017   0.8382   0.0648
   0.250   0.5406   0.01670   0.00722  -0.1014   0.8250   0.0661
   0.500   0.5688   0.01627   0.00676  -0.1010   0.8104   0.0680
   0.750   0.5970   0.01595   0.00638  -0.1006   0.7942   0.0705
   1.000   0.6255   0.01571   0.00604  -0.1003   0.7763   0.0739
   1.250   0.6534   0.01550   0.00577  -0.0999   0.7559   0.0820
   1.500   0.6810   0.01532   0.00556  -0.0994   0.7320   0.0960
   1.750   0.7035   0.01332   0.00544  -0.0979   0.7073   1.0000
   2.000   0.7316   0.01338   0.00521  -0.0973   0.6797   1.0000
   2.250   0.7593   0.01351   0.00507  -0.0968   0.6523   1.0000
   2.500   0.7860   0.01373   0.00504  -0.0962   0.6256   1.0000
   2.750   0.8120   0.01402   0.00511  -0.0956   0.5993   1.0000
   3.000   0.8374   0.01435   0.00526  -0.0949   0.5732   1.0000
   3.250   0.8623   0.01470   0.00544  -0.0942   0.5467   1.0000
   3.500   0.8866   0.01507   0.00566  -0.0935   0.5186   1.0000
   3.750   0.9107   0.01544   0.00591  -0.0927   0.4907   1.0000
   4.000   0.9347   0.01583   0.00616  -0.0920   0.4645   1.0000
   4.500   0.9823   0.01667   0.00678  -0.0905   0.4183   1.0000
   4.750   1.0060   0.01711   0.00712  -0.0898   0.3987   1.0000
   5.000   1.0296   0.01757   0.00750  -0.0891   0.3820   1.0000
   5.250   1.0535   0.01803   0.00792  -0.0885   0.3678   1.0000
   5.500   1.0773   0.01849   0.00839  -0.0879   0.3547   1.0000
   5.750   1.1010   0.01897   0.00887  -0.0873   0.3423   1.0000
   6.000   1.1242   0.01946   0.00937  -0.0866   0.3297   1.0000
   6.250   1.1470   0.01998   0.00992  -0.0859   0.3161   1.0000
   6.500   1.1692   0.02049   0.01045  -0.0850   0.3012   1.0000
   6.750   1.1910   0.02100   0.01099  -0.0842   0.2846   1.0000
   7.000   1.2125   0.02151   0.01154  -0.0833   0.2679   1.0000
   7.250   1.2341   0.02203   0.01216  -0.0824   0.2537   1.0000
   7.500   1.2555   0.02257   0.01278  -0.0815   0.2416   1.0000
   7.750   1.2765   0.02314   0.01343  -0.0806   0.2293   1.0000
   8.000   1.2970   0.02372   0.01412  -0.0796   0.2156   1.0000
   8.250   1.3164   0.02437   0.01485  -0.0784   0.2004   1.0000
   8.500   1.3353   0.02505   0.01561  -0.0772   0.1864   1.0000
   8.750   1.3537   0.02579   0.01644  -0.0760   0.1737   1.0000
   9.000   1.3704   0.02661   0.01732  -0.0745   0.1598   1.0000
   9.250   1.3857   0.02753   0.01829  -0.0729   0.1462   1.0000
   9.500   1.3996   0.02856   0.01941  -0.0712   0.1329   1.0000
   9.750   1.4117   0.02970   0.02061  -0.0692   0.1192   1.0000
  10.000   1.4221   0.03089   0.02191  -0.0670   0.1058   1.0000
  10.250   1.4307   0.03212   0.02328  -0.0645   0.0929   1.0000
  10.500   1.4379   0.03349   0.02475  -0.0620   0.0806   1.0000
  10.750   1.4429   0.03502   0.02633  -0.0594   0.0717   1.0000
  11.000   1.4453   0.03679   0.02810  -0.0569   0.0652   1.0000
  11.250   1.4471   0.03866   0.03012  -0.0545   0.0601   1.0000
  11.500   1.4445   0.04095   0.03245  -0.0521   0.0562   1.0000
  11.750   1.4437   0.04322   0.03489  -0.0500   0.0528   1.0000
  12.000   1.4409   0.04578   0.03762  -0.0482   0.0497   1.0000
  12.250   1.4344   0.04882   0.04078  -0.0467   0.0472   1.0000
  12.500   1.4245   0.05237   0.04439  -0.0454   0.0452   1.0000
  12.750   1.4211   0.05551   0.04779  -0.0446   0.0431   1.0000
  13.000   1.4150   0.05909   0.05159  -0.0442   0.0410   1.0000
  13.250   1.4071   0.06307   0.05574  -0.0442   0.0392   1.0000
  13.500   1.3976   0.06745   0.06027  -0.0446   0.0376   1.0000
  13.750   1.3866   0.07212   0.06504  -0.0452   0.0362   1.0000
  14.000   1.3772   0.07662   0.06961  -0.0456   0.0346   1.0000
  14.250   1.3691   0.08141   0.07467  -0.0468   0.0334   1.0000
  14.500   1.3603   0.08640   0.07990  -0.0482   0.0321   1.0000
  14.750   1.3510   0.09161   0.08530  -0.0498   0.0309   1.0000
  15.000   1.3412   0.09703   0.09090  -0.0517   0.0298   1.0000
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