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GOE 140 (MVA H.17) AIRFOIL (goe140-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 140 (MVA H.17) AIRFOIL (goe140-il)
Reynolds number: 50,000
Max Cl/Cd: 37.33 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe140-il-50000-n5.txt
Download as CSV file: xf-goe140-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 140 (MVA H.17) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2910   0.10571   0.09931  -0.0235   1.0000   0.0782
  -7.750  -0.2962   0.10488   0.09863  -0.0260   1.0000   0.0797
  -7.500  -0.2972   0.10407   0.09793  -0.0314   1.0000   0.0804
  -7.250  -0.2865   0.09796   0.09188  -0.0268   1.0000   0.0824
  -7.000  -0.2806   0.09472   0.08871  -0.0261   1.0000   0.0847
  -6.750  -0.2776   0.09214   0.08621  -0.0264   1.0000   0.0868
  -6.500  -0.2755   0.08981   0.08398  -0.0274   1.0000   0.0892
  -6.250  -0.2737   0.08794   0.08219  -0.0297   1.0000   0.0918
  -6.000  -0.2689   0.08711   0.08136  -0.0360   1.0000   0.0936
  -5.750  -0.2675   0.08370   0.07806  -0.0348   1.0000   0.0947
  -5.500  -0.2693   0.08047   0.07493  -0.0301   1.0000   0.0973
  -5.250  -0.2608   0.07784   0.07233  -0.0307   0.9977   0.1025
  -5.000  -0.2135   0.07302   0.06731  -0.0436   0.9853   0.1106
  -4.750  -0.1815   0.06857   0.06282  -0.0476   0.9745   0.1170
  -4.500  -0.1360   0.06417   0.05820  -0.0576   0.9620   0.1266
  -4.250  -0.0964   0.06026   0.05411  -0.0643   0.9494   0.1409
  -4.000  -0.0628   0.05653   0.05032  -0.0684   0.9366   0.1582
  -3.500   0.0088   0.04987   0.04342  -0.0775   0.9099   0.2154
  -3.000   0.1289   0.04361   0.03568  -0.0929   0.8821   0.1240
  -2.750   0.1657   0.04005   0.03193  -0.0951   0.8671   0.1064
  -2.500   0.2052   0.03739   0.02884  -0.0975   0.8512   0.0965
  -2.250   0.2413   0.03532   0.02639  -0.0990   0.8344   0.0894
  -2.000   0.2764   0.03342   0.02409  -0.1001   0.8172   0.0855
  -1.750   0.3115   0.03192   0.02204  -0.1008   0.7998   0.0821
  -1.500   0.3436   0.03089   0.02047  -0.1008   0.7809   0.0803
  -1.250   0.3726   0.02964   0.01895  -0.1007   0.7614   0.0800
  -1.000   0.4021   0.02871   0.01763  -0.1003   0.7423   0.0805
  -0.750   0.4290   0.02755   0.01639  -0.1001   0.7236   0.0842
  -0.500   0.4565   0.02686   0.01544  -0.0996   0.7046   0.0880
  -0.250   0.4839   0.02620   0.01450  -0.0989   0.6856   0.0894
   0.000   0.5108   0.02561   0.01361  -0.0979   0.6677   0.0904
   0.250   0.5383   0.02512   0.01281  -0.0971   0.6503   0.0919
   0.500   0.5653   0.02474   0.01213  -0.0962   0.6337   0.0939
   0.750   0.5914   0.02426   0.01153  -0.0954   0.6176   0.0972
   1.000   0.6178   0.02398   0.01109  -0.0948   0.6020   0.1019
   1.250   0.6446   0.02380   0.01076  -0.0944   0.5870   0.1123
   1.500   0.6716   0.02365   0.01053  -0.0942   0.5725   0.1295
   1.750   0.6992   0.02350   0.01031  -0.0940   0.5585   0.1547
   2.000   0.7207   0.02154   0.01022  -0.0928   0.5462   1.0000
   2.250   0.7479   0.02194   0.01020  -0.0923   0.5340   1.0000
   2.500   0.7748   0.02234   0.01029  -0.0919   0.5230   1.0000
   2.750   0.8013   0.02276   0.01050  -0.0916   0.5117   1.0000
   3.000   0.8275   0.02323   0.01082  -0.0914   0.5008   1.0000
   3.250   0.8539   0.02369   0.01114  -0.0911   0.4915   1.0000
   3.500   0.8801   0.02418   0.01151  -0.0909   0.4822   1.0000
   3.750   0.9060   0.02472   0.01200  -0.0907   0.4732   1.0000
   4.000   0.9324   0.02521   0.01240  -0.0904   0.4656   1.0000
   4.250   0.9577   0.02584   0.01306  -0.0902   0.4574   1.0000
   4.500   0.9840   0.02639   0.01355  -0.0900   0.4509   1.0000
   4.750   1.0090   0.02708   0.01429  -0.0898   0.4437   1.0000
   5.000   1.0345   0.02771   0.01495  -0.0896   0.4372   1.0000
   5.250   1.0598   0.02839   0.01567  -0.0893   0.4313   1.0000
   5.500   1.0840   0.02918   0.01658  -0.0891   0.4249   1.0000
   5.750   1.1099   0.02983   0.01728  -0.0889   0.4202   1.0000
   6.000   1.1334   0.03077   0.01838  -0.0886   0.4150   1.0000
   6.250   1.1567   0.03172   0.01950  -0.0883   0.4100   1.0000
   6.500   1.1816   0.03252   0.02040  -0.0881   0.4059   1.0000
   6.750   1.2052   0.03346   0.02153  -0.0878   0.4018   1.0000
   7.000   1.2253   0.03470   0.02305  -0.0873   0.3966   1.0000
   7.250   1.2482   0.03565   0.02417  -0.0869   0.3922   1.0000
   7.500   1.2717   0.03638   0.02503  -0.0863   0.3869   1.0000
   7.750   1.2909   0.03690   0.02576  -0.0852   0.3763   1.0000
   8.000   1.3091   0.03721   0.02622  -0.0838   0.3638   1.0000
   8.250   1.3276   0.03743   0.02656  -0.0823   0.3517   1.0000
   8.500   1.3441   0.03736   0.02659  -0.0805   0.3362   1.0000
   8.750   1.3611   0.03769   0.02705  -0.0790   0.3248   1.0000
   9.000   1.3774   0.03796   0.02748  -0.0773   0.3132   1.0000
   9.250   1.3885   0.03888   0.02869  -0.0755   0.3022   1.0000
   9.500   1.3998   0.03990   0.02998  -0.0738   0.2931   1.0000
   9.750   1.4054   0.04078   0.03105  -0.0714   0.2783   1.0000
  10.000   1.4089   0.04198   0.03244  -0.0690   0.2644   1.0000
  10.250   1.4098   0.04336   0.03401  -0.0664   0.2527   1.0000
  10.500   1.4068   0.04543   0.03635  -0.0641   0.2421   1.0000
  10.750   1.4007   0.04807   0.03925  -0.0624   0.2301   1.0000
  11.000   1.3909   0.05148   0.04296  -0.0615   0.2165   1.0000
  11.250   1.3784   0.05577   0.04752  -0.0615   0.2049   1.0000
  11.500   1.3617   0.06116   0.05317  -0.0624   0.1954   1.0000
  11.750   1.3321   0.06914   0.06143  -0.0648   0.1914   1.0000
  12.000   1.2980   0.07834   0.07077  -0.0679   0.1896   1.0000
  12.250   1.2674   0.08728   0.07984  -0.0708   0.1876   1.0000
  12.500   1.2438   0.09500   0.08764  -0.0732   0.1800   1.0000
  12.750   1.2227   0.10233   0.09505  -0.0755   0.1695   1.0000
  13.000   1.2597   0.09609   0.08778  -0.0710   0.0921   1.0000
  13.250   1.2444   0.10222   0.09396  -0.0728   0.0753   1.0000
  13.500   1.2285   0.10845   0.10008  -0.0748   0.0612   1.0000
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