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GOE 415 AIRFOIL (goe415-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 415 AIRFOIL (goe415-il)
Reynolds number: 100,000
Max Cl/Cd: 52.03 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe415-il-100000.txt
Download as CSV file: xf-goe415-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 415 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  -0.4272   0.10556   0.10094  -0.0034   1.0000   0.0606
  -8.250  -0.4288   0.10319   0.09866  -0.0083   1.0000   0.0620
  -8.000  -0.4309   0.10074   0.09629  -0.0144   1.0000   0.0625
  -7.750  -0.4251   0.09716   0.09274  -0.0235   1.0000   0.0628
  -7.500  -0.4105   0.09143   0.08704  -0.0099   1.0000   0.0670
  -7.250  -0.4046   0.08823   0.08389  -0.0112   1.0000   0.0700
  -7.000  -0.3980   0.08466   0.08036  -0.0161   1.0000   0.0737
  -6.750  -0.3857   0.08045   0.07606  -0.0331   1.0000   0.0764
  -6.500  -0.3805   0.07613   0.07191  -0.0254   1.0000   0.0791
  -6.250  -0.3697   0.07312   0.06889  -0.0248   1.0000   0.0839
  -6.000  -0.3528   0.06806   0.06361  -0.0383   1.0000   0.0908
  -5.750  -0.3460   0.06520   0.06097  -0.0317   1.0000   0.0946
  -5.500  -0.3296   0.06096   0.05651  -0.0392   1.0000   0.1049
  -5.250  -0.3213   0.05851   0.05425  -0.0346   1.0000   0.1100
  -5.000  -0.3078   0.05499   0.05065  -0.0369   1.0000   0.1212
  -4.750  -0.2943   0.05203   0.04762  -0.0377   1.0000   0.1346
  -4.500  -0.2817   0.04942   0.04500  -0.0373   1.0000   0.1492
  -4.250  -0.2695   0.04710   0.04270  -0.0362   1.0000   0.1656
  -4.000  -0.2572   0.04496   0.04056  -0.0354   1.0000   0.1920
  -3.750  -0.2470   0.04333   0.03900  -0.0329   1.0000   0.2215
  -2.750  -0.1348   0.02886   0.02293  -0.0409   1.0000   0.1663
  -2.500  -0.0891   0.02435   0.01695  -0.0408   1.0000   0.0843
  -2.250  -0.0311   0.02191   0.01384  -0.0451   0.9900   0.0728
  -2.000   0.0262   0.02005   0.01160  -0.0499   0.9770   0.0745
  -1.750   0.0819   0.01827   0.00969  -0.0543   0.9629   0.0747
  -1.500   0.1357   0.01665   0.00819  -0.0588   0.9474   0.0838
  -1.250   0.1856   0.01552   0.00700  -0.0622   0.9285   0.0968
  -1.000   0.2245   0.01366   0.00633  -0.0638   0.9037   0.3782
  -0.750   0.2704   0.01181   0.00575  -0.0650   0.8766   1.0000
  -0.500   0.2985   0.01180   0.00538  -0.0639   0.8413   1.0000
  -0.250   0.3239   0.01182   0.00507  -0.0624   0.8049   1.0000
   0.000   0.3490   0.01188   0.00480  -0.0610   0.7724   1.0000
   0.250   0.3740   0.01204   0.00464  -0.0597   0.7416   1.0000
   0.500   0.3992   0.01228   0.00457  -0.0586   0.7138   1.0000
   0.750   0.4246   0.01258   0.00455  -0.0576   0.6885   1.0000
   1.000   0.4501   0.01289   0.00463  -0.0569   0.6637   1.0000
   1.250   0.4758   0.01321   0.00474  -0.0562   0.6413   1.0000
   1.500   0.5015   0.01354   0.00486  -0.0555   0.6205   1.0000
   1.750   0.5274   0.01389   0.00503  -0.0549   0.6009   1.0000
   2.000   0.5534   0.01424   0.00523  -0.0544   0.5816   1.0000
   2.250   0.5793   0.01463   0.00545  -0.0539   0.5639   1.0000
   2.500   0.6054   0.01504   0.00570  -0.0534   0.5476   1.0000
   2.750   0.6315   0.01547   0.00605  -0.0530   0.5318   1.0000
   3.000   0.6576   0.01592   0.00641  -0.0526   0.5167   1.0000
   3.250   0.6837   0.01636   0.00678  -0.0522   0.5025   1.0000
   3.500   0.7099   0.01682   0.00716  -0.0519   0.4893   1.0000
   3.750   0.7361   0.01727   0.00764  -0.0516   0.4769   1.0000
   4.000   0.7622   0.01774   0.00814  -0.0513   0.4648   1.0000
   4.250   0.7881   0.01820   0.00861  -0.0509   0.4528   1.0000
   4.500   0.8139   0.01862   0.00905  -0.0505   0.4409   1.0000
   4.750   0.8396   0.01900   0.00947  -0.0501   0.4290   1.0000
   5.000   0.8652   0.01933   0.00979  -0.0496   0.4169   1.0000
   5.250   0.8909   0.01968   0.01012  -0.0492   0.4057   1.0000
   5.500   0.9162   0.02013   0.01071  -0.0488   0.3947   1.0000
   5.750   0.9417   0.02065   0.01138  -0.0484   0.3848   1.0000
   6.000   0.9676   0.02114   0.01189  -0.0481   0.3761   1.0000
   6.250   0.9928   0.02166   0.01256  -0.0476   0.3659   1.0000
   6.500   1.0175   0.02218   0.01325  -0.0472   0.3548   1.0000
   6.750   1.0412   0.02199   0.01293  -0.0462   0.3360   1.0000
   7.000   1.0631   0.02194   0.01306  -0.0452   0.3156   1.0000
   7.250   1.0864   0.02219   0.01343  -0.0445   0.3007   1.0000
   7.500   1.1082   0.02211   0.01339  -0.0435   0.2806   1.0000
   7.750   1.1298   0.02219   0.01370  -0.0426   0.2600   1.0000
   8.000   1.1512   0.02230   0.01392  -0.0416   0.2372   1.0000
   8.250   1.1723   0.02253   0.01431  -0.0407   0.1990   1.0000
   8.500   1.1907   0.02354   0.01507  -0.0396   0.1347   1.0000
   8.750   1.1990   0.02615   0.01706  -0.0379   0.0594   1.0000
   9.000   1.2094   0.02839   0.01919  -0.0361   0.0472   1.0000
   9.250   1.2211   0.03024   0.02126  -0.0344   0.0429   1.0000
   9.500   1.2273   0.03245   0.02365  -0.0324   0.0394   1.0000
   9.750   1.2302   0.03471   0.02609  -0.0303   0.0374   1.0000
  10.000   1.2336   0.03673   0.02832  -0.0281   0.0363   1.0000
  10.250   1.2328   0.03883   0.03060  -0.0256   0.0357   1.0000
  10.500   1.2321   0.04114   0.03310  -0.0237   0.0353   1.0000
  10.750   1.2329   0.04356   0.03563  -0.0220   0.0349   1.0000
  11.000   1.2369   0.04594   0.03813  -0.0204   0.0346   1.0000
  11.250   1.2452   0.04826   0.04055  -0.0187   0.0343   1.0000
  11.500   1.2567   0.05070   0.04312  -0.0170   0.0343   1.0000
  11.750   1.2681   0.05350   0.04612  -0.0154   0.0345   1.0000
  12.000   1.2743   0.05671   0.04958  -0.0142   0.0345   1.0000
  12.250   1.2741   0.06028   0.05340  -0.0135   0.0343   1.0000
  12.500   1.2690   0.06421   0.05759  -0.0135   0.0341   1.0000
  12.750   1.2605   0.06857   0.06222  -0.0141   0.0341   1.0000
  13.000   1.2488   0.07344   0.06735  -0.0155   0.0341   1.0000
  13.250   1.2346   0.07886   0.07303  -0.0177   0.0343   1.0000
  13.500   1.2182   0.08485   0.07926  -0.0205   0.0345   1.0000
  13.750   1.1999   0.09144   0.08608  -0.0241   0.0349   1.0000
  14.000   1.1801   0.09856   0.09340  -0.0282   0.0353   1.0000
  14.250   1.1592   0.10623   0.10125  -0.0328   0.0358   1.0000
  14.500   1.1378   0.11445   0.10962  -0.0379   0.0363   1.0000
  14.750   1.1167   0.12314   0.11844  -0.0433   0.0369   1.0000
  15.000   1.0975   0.13200   0.12739  -0.0484   0.0376   1.0000
  15.250   1.0811   0.14074   0.13622  -0.0534   0.0382   1.0000
  15.500   0.8772   0.12799   0.12368  -0.0320   0.0384   1.0000
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