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GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il)
Reynolds number: 100,000
Max Cl/Cd: 50.38 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe318-il-100000.txt
Download as CSV file: xf-goe318-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 318 (HANSA-BRANDENBURG VI.5) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4210   0.10687   0.10263   0.0067   1.0000   0.0699
  -8.250  -0.4191   0.10436   0.10021   0.0015   1.0000   0.0723
  -8.000  -0.4207   0.10253   0.09850  -0.0092   1.0000   0.0733
  -7.750  -0.4112   0.09756   0.09357  -0.0153   1.0000   0.0741
  -7.500  -0.3948   0.09239   0.08845  -0.0067   1.0000   0.0768
  -7.250  -0.3806   0.08885   0.08496  -0.0090   1.0000   0.0807
  -7.000  -0.3649   0.08533   0.08147  -0.0196   1.0000   0.0861
  -6.750  -0.3494   0.08118   0.07727  -0.0331   1.0000   0.0884
  -6.500  -0.3335   0.07672   0.07290  -0.0297   0.9862   0.0909
  -6.250  -0.3033   0.07244   0.06855  -0.0350   0.9653   0.0966
  -6.000  -0.2678   0.06738   0.06320  -0.0490   0.9450   0.1038
  -5.750  -0.2513   0.06403   0.05990  -0.0471   0.9300   0.1079
  -5.500  -0.2239   0.06086   0.05636  -0.0552   0.9140   0.1188
  -5.250  -0.2116   0.05770   0.05329  -0.0527   0.9013   0.1225
  -5.000  -0.1856   0.05511   0.05034  -0.0578   0.8888   0.1342
  -4.750  -0.1720   0.05210   0.04740  -0.0558   0.8785   0.1383
  -4.500  -0.1484   0.04951   0.04456  -0.0582   0.8677   0.1508
  -4.250  -0.1258   0.04733   0.04218  -0.0596   0.8577   0.1653
  -4.000  -0.1063   0.04512   0.03985  -0.0595   0.8491   0.1808
  -3.750  -0.0848   0.04277   0.03744  -0.0597   0.8395   0.1970
  -3.500  -0.0640   0.04062   0.03521  -0.0595   0.8312   0.2141
  -3.250  -0.0417   0.03890   0.03334  -0.0597   0.8226   0.2428
  -2.250   0.0977   0.02994   0.02205  -0.0635   0.7914   0.1326
  -2.000   0.1277   0.02740   0.01923  -0.0636   0.7832   0.1147
  -1.750   0.1558   0.02577   0.01722  -0.0628   0.7760   0.1068
  -1.500   0.1855   0.02483   0.01590  -0.0627   0.7674   0.1044
  -1.250   0.2116   0.02394   0.01482  -0.0617   0.7601   0.1056
  -1.000   0.2402   0.02319   0.01390  -0.0615   0.7501   0.1047
  -0.750   0.2662   0.02245   0.01303  -0.0604   0.7413   0.1050
  -0.500   0.2920   0.02174   0.01226  -0.0593   0.7308   0.1066
  -0.250   0.3178   0.02115   0.01166  -0.0583   0.7190   0.1096
   0.000   0.3430   0.02068   0.01112  -0.0570   0.7080   0.1162
   0.250   0.3673   0.02006   0.01053  -0.0555   0.6987   0.1251
   0.500   0.3942   0.01972   0.01020  -0.0550   0.6879   0.1375
   0.750   0.4210   0.01918   0.00979  -0.0543   0.6799   0.1845
   1.000   0.4510   0.01701   0.00939  -0.0537   0.6703   1.0000
   1.250   0.4778   0.01720   0.00937  -0.0532   0.6604   1.0000
   1.500   0.5037   0.01726   0.00921  -0.0522   0.6523   1.0000
   1.750   0.5307   0.01748   0.00934  -0.0520   0.6411   1.0000
   2.000   0.5572   0.01762   0.00936  -0.0515   0.6316   1.0000
   2.250   0.5836   0.01768   0.00928  -0.0507   0.6222   1.0000
   2.500   0.6104   0.01786   0.00940  -0.0504   0.6104   1.0000
   2.750   0.6369   0.01795   0.00942  -0.0498   0.5993   1.0000
   3.000   0.6632   0.01790   0.00922  -0.0488   0.5900   1.0000
   3.250   0.6900   0.01799   0.00928  -0.0484   0.5766   1.0000
   3.500   0.7167   0.01806   0.00931  -0.0480   0.5631   1.0000
   3.750   0.7433   0.01812   0.00933  -0.0474   0.5494   1.0000
   4.000   0.7700   0.01817   0.00933  -0.0469   0.5354   1.0000
   4.250   0.7967   0.01822   0.00934  -0.0464   0.5208   1.0000
   4.500   0.8234   0.01831   0.00939  -0.0459   0.5057   1.0000
   4.750   0.8501   0.01846   0.00948  -0.0455   0.4906   1.0000
   5.000   0.8767   0.01870   0.00965  -0.0451   0.4759   1.0000
   5.250   0.9033   0.01903   0.00994  -0.0448   0.4621   1.0000
   5.500   0.9299   0.01943   0.01031  -0.0445   0.4498   1.0000
   5.750   0.9566   0.01982   0.01060  -0.0442   0.4396   1.0000
   6.000   0.9829   0.02039   0.01123  -0.0442   0.4286   1.0000
   6.250   1.0092   0.02104   0.01196  -0.0441   0.4199   1.0000
   6.500   1.0358   0.02163   0.01257  -0.0440   0.4129   1.0000
   6.750   1.0618   0.02242   0.01347  -0.0441   0.4064   1.0000
   7.000   1.0878   0.02319   0.01440  -0.0441   0.4004   1.0000
   7.250   1.1148   0.02388   0.01508  -0.0440   0.3962   1.0000
   7.500   1.1392   0.02497   0.01646  -0.0441   0.3909   1.0000
   7.750   1.1645   0.02581   0.01746  -0.0441   0.3855   1.0000
   8.000   1.1913   0.02638   0.01806  -0.0439   0.3804   1.0000
   8.250   1.2138   0.02724   0.01923  -0.0437   0.3719   1.0000
   8.500   1.2383   0.02731   0.01935  -0.0431   0.3599   1.0000
   8.750   1.2621   0.02676   0.01876  -0.0421   0.3417   1.0000
   9.000   1.2856   0.02623   0.01809  -0.0411   0.3223   1.0000
   9.250   1.3065   0.02632   0.01831  -0.0403   0.3057   1.0000
   9.500   1.3253   0.02649   0.01873  -0.0394   0.2872   1.0000
   9.750   1.3411   0.02662   0.01896  -0.0382   0.2616   1.0000
  10.250   1.3255   0.03176   0.02342  -0.0345   0.1025   1.0000
  10.500   1.3109   0.03533   0.02688  -0.0324   0.0876   1.0000
  10.750   1.3016   0.03884   0.03045  -0.0318   0.0785   1.0000
  11.000   1.2927   0.04255   0.03423  -0.0316   0.0730   1.0000
  11.250   1.2860   0.04615   0.03791  -0.0316   0.0688   1.0000
  11.500   1.2776   0.04991   0.04168  -0.0315   0.0659   1.0000
  11.750   1.2752   0.05294   0.04475  -0.0307   0.0630   1.0000
  12.000   1.2772   0.05550   0.04740  -0.0298   0.0598   1.0000
  12.250   1.2811   0.05777   0.04962  -0.0286   0.0566   1.0000
  12.500   1.2985   0.05861   0.05029  -0.0252   0.0529   1.0000
  12.750   1.3146   0.06013   0.05199  -0.0232   0.0509   1.0000
  13.000   1.3321   0.06188   0.05387  -0.0213   0.0492   1.0000
  13.250   1.3455   0.06418   0.05631  -0.0199   0.0477   1.0000
  13.500   1.3567   0.06675   0.05897  -0.0188   0.0460   1.0000
  13.750   1.3841   0.07047   0.06266  -0.0165   0.0437   1.0000
  14.000   1.3764   0.07430   0.06677  -0.0166   0.0436   1.0000
  14.250   1.3685   0.07854   0.07129  -0.0169   0.0435   1.0000
  14.500   1.3581   0.08316   0.07619  -0.0175   0.0435   1.0000
  14.750   1.3456   0.08814   0.08143  -0.0185   0.0435   1.0000
  15.000   1.3317   0.09350   0.08702  -0.0199   0.0436   1.0000
  15.250   1.3172   0.09923   0.09297  -0.0216   0.0438   1.0000
  15.500   1.2984   0.10467   0.09866  -0.0244   0.0440   1.0000
  15.750   1.2761   0.11076   0.10500  -0.0281   0.0443   1.0000
  16.000   1.2484   0.11847   0.11297  -0.0335   0.0448   1.0000
  16.250   1.2026   0.13125   0.12612  -0.0434   0.0461   1.0000
  16.500   1.0653   0.17711   0.17227  -0.0755   0.0572   1.0000
  16.750   1.0776   0.17757   0.17277  -0.0749   0.0555   1.0000
  17.000   1.0844   0.18017   0.17538  -0.0754   0.0544   1.0000
  17.250   0.7743   0.17978   0.17514  -0.0559   0.0751   1.0000
  17.500   0.7385   0.19533   0.19065  -0.0638   0.1247   1.0000
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