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GOE 802 A AIRFOIL (goe802a-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 802 A AIRFOIL (goe802a-il)
Reynolds number: 100,000
Max Cl/Cd: 52.59 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe802a-il-100000.txt
Download as CSV file: xf-goe802a-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 802 A 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3084   0.09401   0.08933  -0.0275   1.0000   0.0633
  -7.500  -0.3162   0.09241   0.08783  -0.0278   1.0000   0.0638
  -7.250  -0.3253   0.09102   0.08653  -0.0284   1.0000   0.0641
  -7.000  -0.3337   0.08956   0.08512  -0.0289   1.0000   0.0643
  -6.750  -0.3354   0.08659   0.08222  -0.0255   1.0000   0.0647
  -6.500  -0.3388   0.08433   0.08001  -0.0235   1.0000   0.0653
  -6.250  -0.3415   0.08220   0.07792  -0.0225   1.0000   0.0661
  -6.000  -0.3424   0.08002   0.07577  -0.0221   1.0000   0.0671
  -5.750  -0.3407   0.07777   0.07351  -0.0226   1.0000   0.0684
  -5.500  -0.3312   0.07572   0.07136  -0.0264   1.0000   0.0697
  -5.250  -0.3284   0.07282   0.06850  -0.0254   1.0000   0.0702
  -5.000  -0.3085   0.06932   0.06497  -0.0278   0.9967   0.0718
  -4.750  -0.2588   0.06524   0.06063  -0.0377   0.9890   0.0745
  -4.500  -0.2186   0.06077   0.05603  -0.0442   0.9822   0.0754
  -4.250  -0.1818   0.05702   0.05217  -0.0493   0.9738   0.0773
  -4.000  -0.1230   0.05416   0.04877  -0.0583   0.9667   0.0794
  -3.750  -0.0942   0.05009   0.04475  -0.0610   0.9573   0.0803
  -3.500  -0.0448   0.04686   0.04124  -0.0671   0.9509   0.0832
  -3.250  -0.0057   0.04424   0.03831  -0.0707   0.9400   0.0844
  -3.000   0.0429   0.04089   0.03479  -0.0761   0.9341   0.0864
  -2.750   0.0859   0.03965   0.03301  -0.0789   0.9225   0.0884
  -2.500   0.1346   0.03598   0.02925  -0.0840   0.9171   0.0901
  -2.250   0.1724   0.03436   0.02731  -0.0859   0.9054   0.0927
  -2.000   0.2179   0.03201   0.02470  -0.0891   0.8986   0.0949
  -1.750   0.2513   0.03120   0.02346  -0.0896   0.8854   0.0984
  -1.500   0.2868   0.02892   0.02107  -0.0909   0.8757   0.1016
  -1.250   0.3205   0.02767   0.01952  -0.0912   0.8638   0.1042
  -1.000   0.3497   0.02689   0.01841  -0.0906   0.8496   0.1082
  -0.750   0.3787   0.02519   0.01655  -0.0903   0.8368   0.1140
  -0.500   0.4088   0.02324   0.01441  -0.0901   0.8258   0.1249
  -0.250   0.4349   0.02207   0.01316  -0.0892   0.8104   0.1307
   0.000   0.4615   0.02118   0.01220  -0.0882   0.7954   0.1354
   0.250   0.4882   0.02028   0.01130  -0.0873   0.7808   0.1416
   0.500   0.5149   0.01947   0.01050  -0.0862   0.7665   0.1487
   0.750   0.5416   0.01872   0.00979  -0.0850   0.7528   0.1529
   1.000   0.5673   0.01828   0.00931  -0.0838   0.7370   0.1549
   1.250   0.5932   0.01799   0.00894  -0.0826   0.7209   0.1556
   1.500   0.6201   0.01786   0.00867  -0.0817   0.7049   0.1516
   1.750   0.6470   0.01776   0.00844  -0.0808   0.6891   0.1514
   2.000   0.6741   0.01767   0.00827  -0.0801   0.6738   0.1580
   2.250   0.7058   0.01582   0.00828  -0.0802   0.6595   1.0000
   2.500   0.7326   0.01603   0.00820  -0.0794   0.6458   1.0000
   2.750   0.7584   0.01630   0.00830  -0.0787   0.6307   1.0000
   3.000   0.7840   0.01662   0.00851  -0.0781   0.6157   1.0000
   3.250   0.8097   0.01698   0.00875  -0.0776   0.6019   1.0000
   3.500   0.8358   0.01732   0.00895  -0.0770   0.5889   1.0000
   3.750   0.8620   0.01761   0.00907  -0.0764   0.5755   1.0000
   4.000   0.8867   0.01792   0.00931  -0.0758   0.5599   1.0000
   4.250   0.9114   0.01825   0.00957  -0.0751   0.5449   1.0000
   4.500   0.9365   0.01863   0.00989  -0.0745   0.5317   1.0000
   4.750   0.9628   0.01900   0.01013  -0.0741   0.5207   1.0000
   5.000   0.9872   0.01941   0.01057  -0.0736   0.5080   1.0000
   5.250   1.0120   0.01985   0.01100  -0.0731   0.4964   1.0000
   5.500   1.0383   0.02022   0.01126  -0.0727   0.4860   1.0000
   5.750   1.0618   0.02066   0.01180  -0.0720   0.4735   1.0000
   6.000   1.0864   0.02108   0.01221  -0.0715   0.4620   1.0000
   6.250   1.1120   0.02143   0.01246  -0.0710   0.4508   1.0000
   6.500   1.1348   0.02187   0.01303  -0.0703   0.4378   1.0000
   6.750   1.1587   0.02232   0.01349  -0.0696   0.4257   1.0000
   7.000   1.1837   0.02268   0.01376  -0.0690   0.4136   1.0000
   7.250   1.2062   0.02303   0.01414  -0.0682   0.3987   1.0000
   7.500   1.2278   0.02338   0.01454  -0.0671   0.3826   1.0000
   7.750   1.2489   0.02375   0.01491  -0.0660   0.3659   1.0000
   8.000   1.2695   0.02417   0.01533  -0.0649   0.3489   1.0000
   8.250   1.2894   0.02465   0.01579  -0.0637   0.3317   1.0000
   8.500   1.3090   0.02525   0.01642  -0.0625   0.3153   1.0000
   8.750   1.3281   0.02592   0.01711  -0.0613   0.2996   1.0000
   9.000   1.3469   0.02662   0.01782  -0.0601   0.2849   1.0000
   9.250   1.3656   0.02734   0.01852  -0.0588   0.2713   1.0000
   9.500   1.3848   0.02807   0.01916  -0.0577   0.2588   1.0000
   9.750   1.4003   0.02886   0.02013  -0.0561   0.2459   1.0000
  10.000   1.4158   0.02974   0.02106  -0.0545   0.2338   1.0000
  10.250   1.4310   0.03058   0.02188  -0.0530   0.2225   1.0000
  10.500   1.4448   0.03141   0.02269  -0.0513   0.2114   1.0000
  10.750   1.4559   0.03245   0.02385  -0.0494   0.2007   1.0000
  11.000   1.4689   0.03352   0.02490  -0.0477   0.1914   1.0000
  11.250   1.4784   0.03461   0.02609  -0.0457   0.1824   1.0000
  11.500   1.4899   0.03588   0.02738  -0.0440   0.1748   1.0000
  11.750   1.4972   0.03710   0.02874  -0.0417   0.1680   1.0000
  12.000   1.5151   0.03845   0.02997  -0.0409   0.1616   1.0000
  12.250   1.5160   0.03990   0.03175  -0.0380   0.1567   1.0000
  12.500   1.5212   0.04122   0.03318  -0.0359   0.1512   1.0000
  12.750   1.5298   0.04257   0.03447  -0.0344   0.1452   1.0000
  13.000   1.5243   0.04437   0.03659  -0.0318   0.1405   1.0000
  13.250   1.5250   0.04599   0.03835  -0.0300   0.1355   1.0000
  13.500   1.5342   0.04746   0.03975  -0.0289   0.1305   1.0000
  13.750   1.5263   0.04994   0.04261  -0.0272   0.1269   1.0000
  14.000   1.5202   0.05238   0.04526  -0.0260   0.1221   1.0000
  14.250   1.5192   0.05443   0.04730  -0.0252   0.1170   1.0000
  14.500   1.5084   0.05780   0.05095  -0.0247   0.1125   1.0000
  14.750   1.4974   0.06137   0.05474  -0.0248   0.1075   1.0000
  15.000   1.4914   0.06437   0.05768  -0.0249   0.1019   1.0000
  15.250   1.4739   0.06945   0.06311  -0.0260   0.0973   1.0000
  15.500   1.4591   0.07428   0.06808  -0.0275   0.0918   1.0000
  15.750   1.4446   0.07938   0.07325  -0.0291   0.0865   1.0000
  16.000   1.4265   0.08552   0.07959  -0.0314   0.0812   1.0000
  16.250   1.4139   0.09061   0.08457  -0.0332   0.0758   1.0000
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