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GOE 377 AIRFOIL (goe377-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 377 AIRFOIL (goe377-il)
Reynolds number: 1,000,000
Max Cl/Cd: 115.81 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe377-il-1000000.txt
Download as CSV file: xf-goe377-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 377 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3847   0.08684   0.08530  -0.0237   1.0000   0.0091
  -7.750  -0.3869   0.08499   0.08348  -0.0226   1.0000   0.0093
  -7.500  -0.3991   0.08347   0.08200  -0.0200   1.0000   0.0093
  -7.250  -0.3942   0.08052   0.07908  -0.0220   0.9990   0.0095
  -7.000  -0.3691   0.07578   0.07432  -0.0298   0.9962   0.0098
  -6.750  -0.3438   0.07100   0.06951  -0.0373   0.9930   0.0103
  -6.500  -0.3183   0.06620   0.06468  -0.0444   0.9889   0.0108
  -6.250  -0.2822   0.06022   0.05862  -0.0543   0.9853   0.0123
  -6.000  -0.2492   0.05517   0.05349  -0.0612   0.9832   0.0124
  -5.750  -0.2223   0.04979   0.04802  -0.0662   0.9772   0.0125
  -5.500  -0.2171   0.01527   0.01168  -0.0760   0.9641   0.0096
  -5.000  -0.1571   0.01345   0.00954  -0.0773   0.9568   0.0112
  -4.750  -0.1323   0.01218   0.00800  -0.0766   0.9501   0.0121
  -4.500  -0.1040   0.01135   0.00696  -0.0767   0.9448   0.0126
  -4.250  -0.0793   0.00976   0.00508  -0.0761   0.9384   0.0142
  -4.000  -0.0513   0.00966   0.00495  -0.0760   0.9320   0.0154
  -3.750  -0.0234   0.00943   0.00465  -0.0758   0.9259   0.0169
  -3.500   0.0042   0.00955   0.00473  -0.0756   0.9188   0.0178
  -3.250   0.0299   0.00885   0.00395  -0.0752   0.9118   0.0205
  -3.000   0.0568   0.00884   0.00390  -0.0748   0.9028   0.0225
  -2.750   0.0830   0.00874   0.00374  -0.0743   0.8916   0.0242
  -2.500   0.1101   0.00900   0.00396  -0.0739   0.8795   0.0252
  -2.250   0.1336   0.00802   0.00287  -0.0729   0.8675   0.0289
  -2.000   0.1596   0.00787   0.00266  -0.0724   0.8562   0.0308
  -1.750   0.1855   0.00772   0.00245  -0.0718   0.8445   0.0327
  -1.500   0.2115   0.00756   0.00224  -0.0713   0.8323   0.0342
  -1.250   0.2374   0.00744   0.00206  -0.0708   0.8192   0.0352
  -1.000   0.2619   0.00710   0.00163  -0.0700   0.8045   0.0374
  -0.750   0.2869   0.00690   0.00135  -0.0692   0.7885   0.0395
  -0.500   0.3123   0.00680   0.00118  -0.0685   0.7705   0.0411
  -0.250   0.3377   0.00675   0.00105  -0.0679   0.7521   0.0428
   0.000   0.3629   0.00673   0.00095  -0.0672   0.7328   0.0453
   0.250   0.3883   0.00674   0.00088  -0.0666   0.7121   0.0481
   0.500   0.4128   0.00669   0.00080  -0.0658   0.6900   0.0686
   0.750   0.4359   0.00642   0.00082  -0.0649   0.6671   0.2131
   1.000   0.4419   0.00493   0.00091  -0.0607   0.6475   0.8223
   1.250   0.5587   0.00501   0.00108  -0.0809   0.6002   1.0000
   1.500   0.5820   0.00517   0.00110  -0.0799   0.5731   1.0000
   1.750   0.6055   0.00533   0.00114  -0.0790   0.5483   1.0000
   2.000   0.6293   0.00548   0.00119  -0.0781   0.5254   1.0000
   2.250   0.6530   0.00564   0.00125  -0.0773   0.5032   1.0000
   2.500   0.6763   0.00584   0.00133  -0.0763   0.4744   1.0000
   2.750   0.6993   0.00606   0.00142  -0.0753   0.4404   1.0000
   3.000   0.7222   0.00631   0.00152  -0.0743   0.4074   1.0000
   3.250   0.7452   0.00655   0.00163  -0.0734   0.3777   1.0000
   3.500   0.7682   0.00680   0.00177  -0.0725   0.3508   1.0000
   4.000   0.8135   0.00736   0.00208  -0.0705   0.2946   1.0000
   4.250   0.8369   0.00759   0.00223  -0.0696   0.2746   1.0000
   4.500   0.8604   0.00781   0.00239  -0.0688   0.2579   1.0000
   4.750   0.8835   0.00806   0.00258  -0.0679   0.2376   1.0000
   5.000   0.9062   0.00835   0.00276  -0.0670   0.2153   1.0000
   5.250   0.9289   0.00864   0.00297  -0.0660   0.1925   1.0000
   5.500   0.9481   0.00924   0.00329  -0.0646   0.1392   1.0000
   5.750   0.9636   0.01020   0.00386  -0.0625   0.0672   1.0000
   6.000   0.9803   0.01110   0.00449  -0.0605   0.0201   1.0000
   6.250   1.0023   0.01148   0.00490  -0.0594   0.0151   1.0000
   6.500   1.0238   0.01194   0.00539  -0.0581   0.0128   1.0000
   6.750   1.0431   0.01262   0.00621  -0.0565   0.0110   1.0000
   7.000   1.0650   0.01300   0.00662  -0.0554   0.0106   1.0000
   7.250   1.0867   0.01339   0.00707  -0.0543   0.0098   1.0000
   7.500   1.1070   0.01392   0.00766  -0.0530   0.0090   1.0000
   7.750   1.1265   0.01450   0.00830  -0.0515   0.0085   1.0000
   8.000   1.1446   0.01519   0.00906  -0.0499   0.0079   1.0000
   8.250   1.1595   0.01616   0.01012  -0.0477   0.0075   1.0000
   8.500   1.1630   0.01816   0.01230  -0.0436   0.0070   1.0000
   8.750   1.1828   0.01862   0.01283  -0.0423   0.0069   1.0000
   9.000   1.1987   0.01945   0.01374  -0.0403   0.0067   1.0000
   9.250   1.2158   0.02013   0.01451  -0.0386   0.0062   1.0000
   9.500   1.2290   0.02120   0.01567  -0.0363   0.0061   1.0000
   9.750   1.2439   0.02202   0.01656  -0.0344   0.0057   1.0000
  10.000   1.2566   0.02301   0.01763  -0.0322   0.0054   1.0000
  10.250   1.2673   0.02399   0.01870  -0.0297   0.0053   1.0000
  10.500   1.2743   0.02526   0.02009  -0.0266   0.0052   1.0000
  10.750   1.2809   0.02658   0.02152  -0.0236   0.0051   1.0000
  11.000   1.2883   0.02772   0.02277  -0.0209   0.0050   1.0000
  11.250   1.2925   0.02934   0.02450  -0.0181   0.0049   1.0000
  11.500   1.2960   0.03098   0.02626  -0.0154   0.0048   1.0000
  11.750   1.2972   0.03291   0.02832  -0.0128   0.0047   1.0000
  12.000   1.2959   0.03519   0.03076  -0.0103   0.0046   1.0000
  12.250   1.2899   0.03810   0.03385  -0.0077   0.0045   1.0000
  12.500   1.2815   0.04128   0.03723  -0.0055   0.0045   1.0000
  12.750   1.2699   0.04487   0.04103  -0.0038   0.0045   1.0000
  13.000   1.2463   0.05024   0.04667  -0.0025   0.0044   1.0000
  13.250   1.2420   0.05315   0.04971  -0.0025   0.0044   1.0000
  13.500   1.2154   0.05931   0.05615  -0.0039   0.0043   1.0000
  13.750   1.1994   0.06472   0.06173  -0.0057   0.0043   1.0000
  14.250   1.1760   0.07539   0.07269  -0.0110   0.0042   1.0000
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