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GOE 182 (MVA H.27) AIRFOIL (goe182-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 182 (MVA H.27) AIRFOIL (goe182-il)
Reynolds number: 100,000
Max Cl/Cd: 51.48 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe182-il-100000-n5.txt
Download as CSV file: xf-goe182-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 182 (MVA H.27) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3068   0.10709   0.10226  -0.0209   1.0000   0.0564
  -8.500  -0.3106   0.10522   0.10047  -0.0243   1.0000   0.0569
  -8.250  -0.3136   0.10303   0.09837  -0.0269   1.0000   0.0571
  -8.000  -0.2914   0.09738   0.09271  -0.0233   1.0000   0.0586
  -7.750  -0.2838   0.09453   0.08990  -0.0230   1.0000   0.0598
  -7.500  -0.2802   0.09203   0.08746  -0.0230   1.0000   0.0610
  -7.250  -0.2796   0.08974   0.08525  -0.0229   1.0000   0.0621
  -7.000  -0.2788   0.08736   0.08295  -0.0233   1.0000   0.0633
  -6.750  -0.2792   0.08515   0.08081  -0.0248   1.0000   0.0657
  -6.500  -0.2808   0.08291   0.07866  -0.0327   1.0000   0.0678
  -6.250  -0.2589   0.07789   0.07364  -0.0406   0.9944   0.0684
  -5.750  -0.1985   0.06614   0.06172  -0.0518   0.9762   0.0563
  -5.500  -0.1582   0.06014   0.05558  -0.0621   0.9650   0.0565
  -5.250  -0.1253   0.05577   0.05113  -0.0675   0.9531   0.0557
  -5.000  -0.0899   0.05106   0.04629  -0.0739   0.9391   0.0544
  -4.750  -0.0503   0.04552   0.04050  -0.0818   0.9223   0.0541
  -4.500  -0.0075   0.03908   0.03363  -0.0901   0.9034   0.0553
  -4.250   0.0306   0.03391   0.02798  -0.0952   0.8828   0.0549
  -4.000   0.0665   0.02958   0.02304  -0.0988   0.8594   0.0550
  -3.750   0.1017   0.02634   0.01905  -0.1010   0.8361   0.0564
  -3.500   0.1325   0.02439   0.01664  -0.1018   0.8119   0.0581
  -3.250   0.1618   0.02296   0.01484  -0.1020   0.7885   0.0591
  -3.000   0.1903   0.02175   0.01324  -0.1019   0.7655   0.0600
  -2.750   0.2186   0.02074   0.01186  -0.1016   0.7441   0.0612
  -2.500   0.2465   0.01989   0.01068  -0.1013   0.7233   0.0627
  -2.250   0.2742   0.01921   0.00970  -0.1009   0.7034   0.0652
  -2.000   0.3019   0.01873   0.00889  -0.1004   0.6842   0.0682
  -1.750   0.3287   0.01804   0.00814  -0.1001   0.6654   0.0710
  -1.500   0.3557   0.01755   0.00754  -0.0996   0.6463   0.0738
  -1.250   0.3827   0.01713   0.00697  -0.0991   0.6263   0.0774
  -1.000   0.4095   0.01674   0.00646  -0.0986   0.6062   0.0820
  -0.750   0.4361   0.01646   0.00610  -0.0981   0.5860   0.0906
  -0.500   0.4630   0.01623   0.00581  -0.0977   0.5654   0.1011
  -0.250   0.4895   0.01610   0.00562  -0.0972   0.5450   0.1182
   0.000   0.5161   0.01600   0.00550  -0.0967   0.5251   0.1518
   0.250   0.5432   0.01588   0.00541  -0.0964   0.5060   0.2067
   0.500   0.5701   0.01580   0.00541  -0.0961   0.4870   0.2767
   0.750   0.5965   0.01566   0.00546  -0.0958   0.4687   0.3704
   1.000   0.6202   0.01514   0.00552  -0.0949   0.4514   0.5942
   1.250   0.6496   0.01475   0.00543  -0.0948   0.4336   1.0000
   1.500   0.6761   0.01503   0.00548  -0.0943   0.4178   1.0000
   1.750   0.7023   0.01533   0.00556  -0.0939   0.4034   1.0000
   2.000   0.7285   0.01565   0.00568  -0.0935   0.3906   1.0000
   2.250   0.7544   0.01599   0.00582  -0.0930   0.3792   1.0000
   2.500   0.7807   0.01631   0.00601  -0.0926   0.3688   1.0000
   2.750   0.8066   0.01666   0.00621  -0.0922   0.3603   1.0000
   3.000   0.8327   0.01702   0.00645  -0.0918   0.3523   1.0000
   3.250   0.8585   0.01740   0.00670  -0.0914   0.3460   1.0000
   3.500   0.8847   0.01775   0.00701  -0.0910   0.3398   1.0000
   3.750   0.9105   0.01816   0.00732  -0.0906   0.3349   1.0000
   4.000   0.9365   0.01856   0.00765  -0.0902   0.3305   1.0000
   4.250   0.9626   0.01896   0.00804  -0.0899   0.3260   1.0000
   4.500   0.9885   0.01938   0.00843  -0.0895   0.3222   1.0000
   4.750   1.0142   0.01983   0.00882  -0.0892   0.3191   1.0000
   5.000   1.0402   0.02030   0.00926  -0.0888   0.3162   1.0000
   5.250   1.0661   0.02075   0.00978  -0.0885   0.3132   1.0000
   5.500   1.0919   0.02122   0.01029  -0.0882   0.3104   1.0000
   5.750   1.1177   0.02171   0.01081  -0.0879   0.3080   1.0000
   6.000   1.1434   0.02223   0.01136  -0.0875   0.3058   1.0000
   6.250   1.1692   0.02276   0.01191  -0.0872   0.3039   1.0000
   6.500   1.1950   0.02334   0.01248  -0.0870   0.3021   1.0000
   6.750   1.2201   0.02390   0.01319  -0.0866   0.3000   1.0000
   7.000   1.2450   0.02448   0.01394  -0.0862   0.2977   1.0000
   7.250   1.2697   0.02508   0.01467  -0.0858   0.2955   1.0000
   7.500   1.2943   0.02569   0.01540  -0.0854   0.2933   1.0000
   7.750   1.3189   0.02630   0.01614  -0.0850   0.2912   1.0000
   8.000   1.3435   0.02690   0.01681  -0.0846   0.2889   1.0000
   8.250   1.3680   0.02747   0.01742  -0.0842   0.2858   1.0000
   8.500   1.3890   0.02808   0.01832  -0.0834   0.2816   1.0000
   8.750   1.4109   0.02862   0.01907  -0.0826   0.2773   1.0000
   9.000   1.4338   0.02912   0.01967  -0.0820   0.2736   1.0000
   9.250   1.4579   0.02965   0.02023  -0.0815   0.2705   1.0000
   9.500   1.4764   0.03034   0.02128  -0.0804   0.2662   1.0000
   9.750   1.4951   0.03068   0.02181  -0.0792   0.2590   1.0000
  10.000   1.5115   0.03084   0.02213  -0.0777   0.2491   1.0000
  10.250   1.5269   0.03087   0.02220  -0.0760   0.2377   1.0000
  10.500   1.5391   0.03136   0.02302  -0.0741   0.2257   1.0000
  10.750   1.5518   0.03190   0.02379  -0.0723   0.2133   1.0000
  11.000   1.5619   0.03256   0.02468  -0.0703   0.1948   1.0000
  11.250   1.5578   0.03385   0.02575  -0.0670   0.1284   1.0000
  11.500   1.5382   0.03699   0.02859  -0.0632   0.1045   1.0000
  11.750   1.5225   0.04047   0.03210  -0.0608   0.0776   1.0000
  12.000   1.5022   0.04490   0.03656  -0.0596   0.0672   1.0000
  12.250   1.4825   0.04996   0.04173  -0.0598   0.0631   1.0000
  12.500   1.4610   0.05588   0.04782  -0.0611   0.0607   1.0000
  12.750   1.4374   0.06267   0.05481  -0.0633   0.0596   1.0000
  13.000   1.4119   0.07026   0.06263  -0.0661   0.0595   1.0000
  13.250   1.3857   0.07822   0.07081  -0.0691   0.0597   1.0000
  13.500   1.3600   0.08624   0.07903  -0.0720   0.0598   1.0000
  13.750   1.3354   0.09405   0.08697  -0.0747   0.0595   1.0000
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