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GOE 286 AIRFOIL (goe286-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 286 AIRFOIL (goe286-il)
Reynolds number: 200,000
Max Cl/Cd: 72.25 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe286-il-200000.txt
Download as CSV file: xf-goe286-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 286 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3699   0.08853   0.08522  -0.0210   1.0000   0.0478
  -7.500  -0.3661   0.08414   0.08083  -0.0366   1.0000   0.0492
  -7.250  -0.3627   0.07894   0.07566  -0.0382   1.0000   0.0497
  -7.000  -0.3571   0.07613   0.07291  -0.0342   1.0000   0.0504
  -6.750  -0.3516   0.07378   0.07060  -0.0322   1.0000   0.0513
  -6.500  -0.3480   0.07141   0.06826  -0.0315   1.0000   0.0525
  -6.250  -0.3460   0.06900   0.06587  -0.0311   1.0000   0.0538
  -6.000  -0.3449   0.06652   0.06340  -0.0311   1.0000   0.0556
  -5.500  -0.2964   0.05660   0.05320  -0.0439   0.9941   0.0619
  -5.250  -0.2604   0.05327   0.04984  -0.0481   0.9878   0.0649
  -5.000  -0.2046   0.04724   0.04317  -0.0597   0.9815   0.0733
  -4.750  -0.1720   0.04348   0.03951  -0.0629   0.9754   0.0752
  -4.500  -0.1318   0.04063   0.03659  -0.0672   0.9712   0.0799
  -4.250  -0.0921   0.03683   0.03236  -0.0718   0.9618   0.0888
  -4.000  -0.0597   0.03442   0.02995  -0.0738   0.9526   0.0922
  -3.750  -0.0241   0.03209   0.02712  -0.0760   0.9413   0.1031
  -3.500  -0.0002   0.02985   0.02493  -0.0758   0.9254   0.1061
  -3.250   0.0262   0.02863   0.02331  -0.0752   0.9065   0.1184
  -3.000   0.0475   0.02654   0.02128  -0.0742   0.8869   0.1225
  -2.750   0.0710   0.02519   0.01968  -0.0732   0.8675   0.1361
  -2.500   0.1088   0.02004   0.01328  -0.0711   0.8512   0.0702
  -2.250   0.1344   0.01817   0.01109  -0.0700   0.8303   0.0663
  -2.000   0.1611   0.01677   0.00927  -0.0688   0.8105   0.0635
  -1.750   0.1875   0.01600   0.00828  -0.0679   0.7915   0.0641
  -1.500   0.2144   0.01537   0.00750  -0.0673   0.7724   0.0655
  -1.250   0.2417   0.01467   0.00666  -0.0667   0.7531   0.0656
  -1.000   0.2689   0.01409   0.00596  -0.0661   0.7341   0.0662
  -0.750   0.2959   0.01361   0.00538  -0.0656   0.7152   0.0676
  -0.500   0.3228   0.01323   0.00489  -0.0650   0.6959   0.0696
  -0.250   0.3498   0.01297   0.00450  -0.0645   0.6758   0.0721
   0.000   0.3765   0.01264   0.00412  -0.0641   0.6566   0.0786
   0.250   0.4037   0.01250   0.00386  -0.0637   0.6385   0.0890
   0.500   0.4288   0.01126   0.00367  -0.0636   0.6221   0.4220
   0.750   0.4598   0.00998   0.00355  -0.0634   0.6048   1.0000
   1.000   0.4870   0.01016   0.00353  -0.0631   0.5880   1.0000
   1.250   0.5144   0.01030   0.00353  -0.0628   0.5704   1.0000
   1.500   0.5417   0.01044   0.00354  -0.0626   0.5519   1.0000
   1.750   0.5691   0.01057   0.00355  -0.0624   0.5328   1.0000
   2.000   0.5963   0.01072   0.00356  -0.0622   0.5137   1.0000
   2.250   0.6233   0.01090   0.00360  -0.0620   0.4958   1.0000
   2.500   0.6504   0.01110   0.00366  -0.0618   0.4791   1.0000
   2.750   0.6774   0.01133   0.00376  -0.0616   0.4640   1.0000
   3.000   0.7042   0.01158   0.00389  -0.0614   0.4493   1.0000
   3.250   0.7310   0.01184   0.00404  -0.0612   0.4357   1.0000
   3.500   0.7578   0.01210   0.00420  -0.0610   0.4223   1.0000
   3.750   0.7844   0.01236   0.00438  -0.0609   0.4091   1.0000
   4.000   0.8111   0.01262   0.00458  -0.0607   0.3967   1.0000
   4.250   0.8376   0.01290   0.00479  -0.0605   0.3868   1.0000
   4.500   0.8646   0.01312   0.00502  -0.0604   0.3779   1.0000
   4.750   0.8912   0.01340   0.00526  -0.0602   0.3703   1.0000
   5.000   0.9181   0.01362   0.00551  -0.0601   0.3619   1.0000
   5.250   0.9446   0.01388   0.00576  -0.0599   0.3536   1.0000
   5.500   0.9711   0.01412   0.00603  -0.0597   0.3455   1.0000
   5.750   0.9975   0.01437   0.00630  -0.0595   0.3375   1.0000
   6.000   1.0237   0.01463   0.00657  -0.0593   0.3291   1.0000
   6.250   1.0499   0.01487   0.00686  -0.0591   0.3196   1.0000
   6.500   1.0755   0.01515   0.00716  -0.0589   0.3099   1.0000
   6.750   1.1014   0.01540   0.00747  -0.0586   0.2995   1.0000
   7.000   1.1270   0.01567   0.00779  -0.0584   0.2886   1.0000
   7.250   1.1522   0.01596   0.00814  -0.0580   0.2756   1.0000
   7.500   1.1770   0.01629   0.00850  -0.0577   0.2616   1.0000
   7.750   1.2014   0.01666   0.00889  -0.0573   0.2452   1.0000
   8.000   1.2246   0.01713   0.00932  -0.0568   0.2237   1.0000
   8.250   1.2466   0.01772   0.00985  -0.0561   0.1973   1.0000
   8.500   1.2673   0.01846   0.01046  -0.0554   0.1731   1.0000
   8.750   1.2872   0.01925   0.01117  -0.0545   0.1572   1.0000
   9.000   1.3070   0.02003   0.01194  -0.0537   0.1473   1.0000
   9.250   1.3257   0.02086   0.01279  -0.0526   0.1397   1.0000
   9.500   1.3444   0.02165   0.01364  -0.0516   0.1332   1.0000
   9.750   1.3601   0.02264   0.01465  -0.0502   0.1266   1.0000
  10.000   1.3774   0.02347   0.01559  -0.0491   0.1191   1.0000
  10.250   1.3909   0.02454   0.01671  -0.0474   0.1123   1.0000
  10.500   1.4074   0.02531   0.01761  -0.0462   0.1034   1.0000
  10.750   1.4264   0.02587   0.01833  -0.0452   0.0909   1.0000
  11.000   1.4408   0.02671   0.01901  -0.0438   0.0665   1.0000
  11.250   1.4354   0.02871   0.02088  -0.0401   0.0583   1.0000
  11.500   1.4280   0.03111   0.02344  -0.0369   0.0524   1.0000
  11.750   1.4164   0.03415   0.02659  -0.0342   0.0475   1.0000
  12.000   1.4119   0.03691   0.02951  -0.0327   0.0427   1.0000
  12.250   1.3998   0.04066   0.03333  -0.0317   0.0402   1.0000
  12.500   1.4027   0.04315   0.03600  -0.0313   0.0369   1.0000
  12.750   1.4012   0.04623   0.03920  -0.0312   0.0347   1.0000
  13.000   1.3972   0.04975   0.04280  -0.0315   0.0333   1.0000
  13.250   1.3897   0.05375   0.04686  -0.0319   0.0322   1.0000
  13.500   1.3880   0.05710   0.05037  -0.0321   0.0311   1.0000
  13.750   1.3852   0.06061   0.05400  -0.0324   0.0300   1.0000
  14.000   1.3821   0.06417   0.05766  -0.0328   0.0291   1.0000
  14.250   1.3788   0.06778   0.06136  -0.0333   0.0283   1.0000
  14.500   1.3754   0.07148   0.06515  -0.0340   0.0275   1.0000
  14.750   1.3714   0.07526   0.06897  -0.0347   0.0268   1.0000
  15.000   1.3681   0.07872   0.07246  -0.0347   0.0261   1.0000
  15.250   1.3663   0.08235   0.07625  -0.0353   0.0255   1.0000
  15.500   1.3644   0.08603   0.08007  -0.0359   0.0248   1.0000
  15.750   1.3627   0.08966   0.08382  -0.0365   0.0243   1.0000
  16.000   1.3614   0.09323   0.08750  -0.0370   0.0238   1.0000
  16.250   1.3594   0.09701   0.09141  -0.0378   0.0234   1.0000
  16.500   1.3563   0.10105   0.09557  -0.0388   0.0231   1.0000
  16.750   1.3528   0.10520   0.09985  -0.0399   0.0228   1.0000
  17.000   1.3488   0.10952   0.10430  -0.0413   0.0225   1.0000
  17.250   1.3440   0.11407   0.10900  -0.0429   0.0223   1.0000
  17.500   1.3379   0.11896   0.11403  -0.0448   0.0221   1.0000
  17.750   1.3302   0.12429   0.11952  -0.0471   0.0220   1.0000
  18.000   1.3200   0.13029   0.12570  -0.0501   0.0220   1.0000
  18.250   1.3064   0.13729   0.13291  -0.0540   0.0220   1.0000
  18.500   1.2886   0.14559   0.14144  -0.0590   0.0221   1.0000
  18.750   1.2606   0.15703   0.15318  -0.0664   0.0225   1.0000
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