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GOE 770 AIRFOIL (goe770-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 770 AIRFOIL (goe770-il)
Reynolds number: 100,000
Max Cl/Cd: 36.56 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe770-il-100000-n5.txt
Download as CSV file: xf-goe770-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 770 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
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.6175   0.08620   0.08028  -0.0574   1.0000   0.0571
 -14.500  -0.6962   0.07161   0.06523  -0.0673   1.0000   0.0568
 -14.250  -0.7268   0.06505   0.05842  -0.0709   1.0000   0.0570
 -14.000  -0.7479   0.06013   0.05326  -0.0731   1.0000   0.0575
 -13.750  -0.7644   0.05604   0.04894  -0.0743   1.0000   0.0580
 -13.500  -0.7780   0.05251   0.04518  -0.0747   1.0000   0.0586
 -13.250  -0.7898   0.04942   0.04183  -0.0745   1.0000   0.0593
 -13.000  -0.7950   0.04699   0.03921  -0.0736   1.0000   0.0599
 -12.750  -0.7789   0.04545   0.03768  -0.0743   0.9570   0.0607
 -12.500  -0.7581   0.04370   0.03577  -0.0758   0.8950   0.0617
 -12.000  -0.7387   0.04077   0.03232  -0.0734   0.8210   0.0638
 -11.750  -0.7313   0.03934   0.03056  -0.0716   0.7977   0.0652
 -11.500  -0.7211   0.03805   0.02900  -0.0700   0.7789   0.0665
 -11.250  -0.7051   0.03717   0.02805  -0.0688   0.7631   0.0676
 -11.000  -0.6893   0.03625   0.02701  -0.0676   0.7490   0.0689
 -10.750  -0.6723   0.03524   0.02585  -0.0665   0.7370   0.0704
 -10.500  -0.6547   0.03420   0.02459  -0.0655   0.7266   0.0722
 -10.250  -0.6355   0.03327   0.02354  -0.0647   0.7176   0.0740
 -10.000  -0.6158   0.03249   0.02274  -0.0639   0.7087   0.0758
  -9.500  -0.5759   0.03090   0.02086  -0.0622   0.6933   0.0805
  -9.250  -0.5553   0.03013   0.02009  -0.0614   0.6860   0.0826
  -9.000  -0.5351   0.02946   0.01935  -0.0605   0.6801   0.0852
  -8.750  -0.5140   0.02880   0.01858  -0.0597   0.6737   0.0886
  -8.500  -0.4936   0.02810   0.01789  -0.0589   0.6678   0.0915
  -8.250  -0.4734   0.02748   0.01723  -0.0580   0.6624   0.0950
  -7.750  -0.4329   0.02628   0.01593  -0.0561   0.6520   0.1030
  -7.500  -0.4122   0.02574   0.01534  -0.0552   0.6465   0.1080
  -7.250  -0.3927   0.02514   0.01474  -0.0542   0.6418   0.1131
  -7.000  -0.3721   0.02464   0.01416  -0.0532   0.6377   0.1195
  -6.750  -0.3525   0.02408   0.01362  -0.0521   0.6336   0.1264
  -6.500  -0.3319   0.02357   0.01314  -0.0512   0.6285   0.1351
  -6.250  -0.3117   0.02304   0.01265  -0.0502   0.6237   0.1466
  -6.000  -0.2923   0.02243   0.01217  -0.0491   0.6195   0.1642
  -5.750  -0.2735   0.02180   0.01177  -0.0479   0.6159   0.2007
  -5.500  -0.2530   0.02135   0.01149  -0.0470   0.6121   0.2558
  -5.250  -0.2311   0.02101   0.01126  -0.0462   0.6073   0.2951
  -5.000  -0.2094   0.02065   0.01103  -0.0453   0.6027   0.3269
  -4.750  -0.1876   0.02033   0.01086  -0.0443   0.5986   0.3609
  -4.500  -0.1653   0.02014   0.01087  -0.0431   0.5949   0.4022
  -4.250  -0.1412   0.02013   0.01092  -0.0423   0.5913   0.4460
  -4.000  -0.1173   0.02019   0.01106  -0.0415   0.5863   0.4812
  -3.750  -0.0925   0.02027   0.01112  -0.0408   0.5815   0.5079
  -3.500  -0.0671   0.02033   0.01112  -0.0401   0.5772   0.5296
  -3.250  -0.0409   0.02037   0.01109  -0.0395   0.5733   0.5485
  -3.000  -0.0149   0.02045   0.01110  -0.0389   0.5695   0.5653
  -2.750   0.0099   0.02055   0.01119  -0.0384   0.5643   0.5815
  -2.500   0.0355   0.02063   0.01129  -0.0377   0.5594   0.5964
  -2.250   0.0618   0.02067   0.01130  -0.0372   0.5553   0.6103
  -2.000   0.0887   0.02070   0.01120  -0.0368   0.5518   0.6237
  -1.750   0.1153   0.02075   0.01125  -0.0364   0.5478   0.6329
  -1.500   0.1408   0.02085   0.01136  -0.0360   0.5427   0.6415
  -1.250   0.1673   0.02089   0.01134  -0.0358   0.5381   0.6499
  -1.000   0.1947   0.02089   0.01131  -0.0355   0.5341   0.6578
  -0.750   0.2223   0.02089   0.01119  -0.0354   0.5308   0.6682
  -0.500   0.2479   0.02101   0.01136  -0.0350   0.5264   0.6774
  -0.250   0.2730   0.02114   0.01153  -0.0346   0.5213   0.6866
   0.000   0.2995   0.02119   0.01154  -0.0344   0.5168   0.6954
   0.250   0.3271   0.02119   0.01151  -0.0341   0.5130   0.7046
   0.500   0.3553   0.02118   0.01139  -0.0341   0.5099   0.7153
   0.750   0.3788   0.02141   0.01176  -0.0335   0.5042   0.7239
   1.000   0.4040   0.02155   0.01193  -0.0331   0.4994   0.7348
   1.250   0.4310   0.02160   0.01198  -0.0329   0.4954   0.7455
   1.500   0.4590   0.02160   0.01193  -0.0328   0.4921   0.7583
   1.750   0.4840   0.02177   0.01216  -0.0323   0.4876   0.7711
   2.000   0.5068   0.02201   0.01249  -0.0316   0.4821   0.7862
   2.250   0.5327   0.02211   0.01262  -0.0312   0.4777   0.8009
   2.500   0.5607   0.02212   0.01262  -0.0311   0.4742   0.8155
   2.750   0.5881   0.02223   0.01271  -0.0310   0.4707   0.8320
   3.000   0.6101   0.02265   0.01327  -0.0304   0.4651   0.8511
   3.250   0.6379   0.02287   0.01355  -0.0305   0.4607   0.8705
   3.500   0.6706   0.02298   0.01364  -0.0314   0.4569   0.8906
   3.750   0.7080   0.02303   0.01361  -0.0331   0.4539   0.9102
   4.000   0.7378   0.02365   0.01437  -0.0344   0.4477   0.9324
   4.250   0.7748   0.02398   0.01473  -0.0367   0.4428   0.9518
   4.500   0.8149   0.02416   0.01485  -0.0394   0.4392   0.9693
   4.750   0.8573   0.02428   0.01487  -0.0424   0.4363   0.9842
   5.000   0.8904   0.02504   0.01575  -0.0449   0.4309   1.0000
   5.250   0.8999   0.02549   0.01620  -0.0424   0.4270   1.0000
   5.500   0.9154   0.02579   0.01646  -0.0407   0.4237   1.0000
   5.750   0.9358   0.02596   0.01655  -0.0397   0.4209   1.0000
   6.000   0.9571   0.02618   0.01668  -0.0388   0.4182   1.0000
   6.250   0.9595   0.02716   0.01779  -0.0356   0.4133   1.0000
   6.500   0.9716   0.02780   0.01847  -0.0338   0.4094   1.0000
   6.750   0.9899   0.02824   0.01889  -0.0327   0.4064   1.0000
   7.000   1.0127   0.02852   0.01912  -0.0322   0.4040   1.0000
   7.250   1.0396   0.02871   0.01924  -0.0322   0.4019   1.0000
   7.500   1.0351   0.03018   0.02087  -0.0287   0.3978   1.0000
   7.750   1.0309   0.03155   0.02233  -0.0253   0.3937   1.0000
   8.000   1.0404   0.03242   0.02322  -0.0235   0.3905   1.0000
   8.250   1.0621   0.03279   0.02358  -0.0231   0.3879   1.0000
   8.500   1.0912   0.03287   0.02361  -0.0233   0.3859   1.0000
   8.750   1.0840   0.03482   0.02567  -0.0206   0.3824   1.0000
   9.000   1.0099   0.04213   0.03326  -0.0161   0.3739   1.0000
   9.250   1.0280   0.04291   0.03404  -0.0158   0.3714   1.0000
   9.500   1.0593   0.04255   0.03367  -0.0157   0.3699   1.0000
   9.750   1.0958   0.04183   0.03291  -0.0159   0.3687   1.0000
  10.250   0.9794   0.05861   0.04999  -0.0143   0.3501   1.0000
  10.500   1.0314   0.05549   0.04684  -0.0138   0.3507   1.0000
  13.000   0.8657   0.10755   0.09956  -0.0197   0.2727   1.0000
  13.250   0.8869   0.10769   0.09973  -0.0194   0.2709   1.0000
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