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E186 (10.27%) (e186-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E186 (10.27%) (e186-il)
Reynolds number: 200,000
Max Cl/Cd: 58.14 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e186-il-200000-n5.txt
Download as CSV file: xf-e186-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E186  (10.27%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.7263   0.06803   0.06503   0.0029   1.0000   0.0150
  -9.250  -0.7468   0.06279   0.05970   0.0009   1.0000   0.0147
  -9.000  -0.7675   0.05793   0.05466   0.0017   1.0000   0.0148
  -8.750  -0.7808   0.05303   0.04949   0.0027   1.0000   0.0149
  -8.500  -0.7878   0.04831   0.04442   0.0042   1.0000   0.0150
  -8.250  -0.7890   0.04396   0.03968   0.0058   1.0000   0.0151
  -8.000  -0.7849   0.03999   0.03529   0.0076   1.0000   0.0151
  -7.750  -0.7757   0.03662   0.03147   0.0093   1.0000   0.0152
  -7.500  -0.7621   0.03326   0.02759   0.0105   0.9225   0.0154
  -7.250  -0.7530   0.03021   0.02401   0.0133   0.8747   0.0157
  -7.000  -0.7398   0.02777   0.02114   0.0157   0.8447   0.0161
  -6.750  -0.7222   0.02594   0.01898   0.0175   0.8207   0.0165
  -6.500  -0.7023   0.02476   0.01758   0.0188   0.8005   0.0174
  -6.250  -0.6808   0.02369   0.01627   0.0199   0.7826   0.0184
  -6.000  -0.6583   0.02240   0.01471   0.0210   0.7671   0.0190
  -5.750  -0.6349   0.02109   0.01315   0.0221   0.7531   0.0193
  -5.500  -0.6112   0.01993   0.01176   0.0230   0.7404   0.0197
  -5.250  -0.5876   0.01893   0.01058   0.0239   0.7288   0.0202
  -4.750  -0.5400   0.01728   0.00862   0.0257   0.7076   0.0214
  -4.500  -0.5159   0.01662   0.00782   0.0265   0.6981   0.0221
  -4.250  -0.4916   0.01604   0.00710   0.0273   0.6895   0.0228
  -4.000  -0.4674   0.01540   0.00634   0.0280   0.6806   0.0255
  -3.750  -0.4420   0.01499   0.00582   0.0286   0.6728   0.0283
  -3.500  -0.4164   0.01460   0.00530   0.0291   0.6649   0.0310
  -3.250  -0.3910   0.01415   0.00483   0.0297   0.6577   0.0399
  -3.000  -0.3665   0.01360   0.00440   0.0304   0.6506   0.0760
  -2.750  -0.3424   0.01304   0.00407   0.0309   0.6440   0.1381
  -2.500  -0.3181   0.01254   0.00378   0.0315   0.6372   0.2028
  -2.250  -0.2940   0.01209   0.00354   0.0321   0.6312   0.2724
  -2.000  -0.2753   0.01117   0.00333   0.0336   0.6249   0.4340
  -1.750  -0.2617   0.01010   0.00318   0.0366   0.6198   0.6404
  -1.500  -0.2139   0.00951   0.00327   0.0333   0.6129   0.8280
  -1.250  -0.1416   0.00973   0.00342   0.0246   0.6062   0.8908
  -1.000  -0.0991   0.00994   0.00351   0.0220   0.5997   0.9177
  -0.750  -0.0622   0.01014   0.00360   0.0204   0.5937   0.9356
  -0.500  -0.0273   0.01031   0.00365   0.0192   0.5881   0.9500
  -0.250   0.0088   0.01046   0.00371   0.0176   0.5819   0.9623
   0.000   0.0459   0.01060   0.00373   0.0158   0.5767   0.9729
   0.250   0.0841   0.01069   0.00377   0.0136   0.5704   0.9817
   0.500   0.1254   0.01070   0.00369   0.0107   0.5647   0.9881
   0.750   0.1653   0.01071   0.00364   0.0081   0.5589   0.9946
   1.000   0.2061   0.01062   0.00352   0.0052   0.5528   0.9998
   1.250   0.2315   0.01064   0.00347   0.0056   0.5480   1.0000
   1.500   0.2569   0.01064   0.00348   0.0059   0.5420   1.0000
   1.750   0.2822   0.01066   0.00348   0.0063   0.5367   1.0000
   2.000   0.3076   0.01069   0.00351   0.0067   0.5314   1.0000
   2.250   0.3333   0.01072   0.00355   0.0070   0.5253   1.0000
   2.500   0.3587   0.01077   0.00356   0.0075   0.5202   1.0000
   2.750   0.3846   0.01080   0.00365   0.0078   0.5131   1.0000
   3.000   0.4102   0.01085   0.00370   0.0082   0.5067   1.0000
   3.250   0.4362   0.01089   0.00379   0.0085   0.4982   1.0000
   3.500   0.4619   0.01094   0.00384   0.0089   0.4904   1.0000
   3.750   0.4878   0.01099   0.00394   0.0092   0.4809   1.0000
   4.000   0.5137   0.01105   0.00404   0.0095   0.4708   1.0000
   4.250   0.5395   0.01112   0.00417   0.0099   0.4604   1.0000
   4.500   0.5653   0.01120   0.00427   0.0103   0.4489   1.0000
   4.750   0.5911   0.01129   0.00441   0.0106   0.4354   1.0000
   5.000   0.6170   0.01139   0.00457   0.0109   0.4206   1.0000
   5.250   0.6427   0.01152   0.00475   0.0112   0.4025   1.0000
   5.500   0.6683   0.01169   0.00496   0.0116   0.3800   1.0000
   5.750   0.6936   0.01193   0.00518   0.0119   0.3482   1.0000
   6.000   0.7181   0.01239   0.00547   0.0121   0.2957   1.0000
   6.250   0.7409   0.01337   0.00604   0.0120   0.2142   1.0000
   6.500   0.7628   0.01447   0.00680   0.0120   0.1471   1.0000
   6.750   0.7846   0.01542   0.00757   0.0122   0.1021   1.0000
   7.000   0.8057   0.01640   0.00836   0.0125   0.0663   1.0000
   7.250   0.8260   0.01742   0.00924   0.0129   0.0365   1.0000
   7.500   0.8454   0.01850   0.01024   0.0136   0.0200   1.0000
   7.750   0.8645   0.01952   0.01131   0.0144   0.0153   1.0000
   8.000   0.8835   0.02044   0.01235   0.0153   0.0136   1.0000
   8.250   0.9010   0.02144   0.01346   0.0163   0.0124   1.0000
   8.500   0.9155   0.02273   0.01490   0.0175   0.0115   1.0000
   8.750   0.9284   0.02404   0.01634   0.0189   0.0111   1.0000
   9.000   0.9405   0.02531   0.01774   0.0204   0.0107   1.0000
   9.250   0.9515   0.02657   0.01913   0.0220   0.0101   1.0000
   9.500   0.9608   0.02786   0.02053   0.0236   0.0096   1.0000
   9.750   0.9682   0.02925   0.02203   0.0254   0.0093   1.0000
  10.000   0.9721   0.03062   0.02350   0.0274   0.0086   1.0000
  10.250   0.9712   0.03220   0.02518   0.0297   0.0084   1.0000
  10.500   0.9726   0.03395   0.02704   0.0313   0.0083   1.0000
  10.750   0.9741   0.03592   0.02911   0.0326   0.0080   1.0000
  11.000   0.9763   0.03798   0.03129   0.0336   0.0078   1.0000
  11.250   0.9789   0.04012   0.03356   0.0344   0.0078   1.0000
  11.500   0.9801   0.04254   0.03615   0.0350   0.0076   1.0000
  11.750   0.9802   0.04514   0.03889   0.0355   0.0075   1.0000
  12.000   0.9796   0.04792   0.04183   0.0357   0.0075   1.0000
  12.250   0.9764   0.05109   0.04516   0.0356   0.0074   1.0000
  12.500   0.9718   0.05452   0.04878   0.0352   0.0073   1.0000
  12.750   0.9651   0.05831   0.05274   0.0344   0.0072   1.0000
  13.000   0.9579   0.06226   0.05687   0.0333   0.0072   1.0000
  13.250   0.9489   0.06662   0.06141   0.0318   0.0072   1.0000
  13.500   0.9371   0.07157   0.06654   0.0298   0.0072   1.0000
  13.750   0.9244   0.07689   0.07204   0.0274   0.0072   1.0000
  14.000   0.9109   0.08272   0.07804   0.0245   0.0072   1.0000
  14.250   0.8973   0.08902   0.08450   0.0212   0.0072   1.0000
  14.500   0.8802   0.09645   0.09211   0.0171   0.0073   1.0000
  14.750   0.8652   0.10404   0.09985   0.0128   0.0074   1.0000
  15.000   0.8425   0.11407   0.11007   0.0072   0.0075   1.0000
  15.250   0.8059   0.12916   0.12535  -0.0008   0.0077   1.0000
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