Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

EPPLER 715 AIRFOIL (e715-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 715 AIRFOIL (e715-il)
Reynolds number: 500,000
Max Cl/Cd: 113.28 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e715-il-500000.txt
Download as CSV file: xf-e715-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 715 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.5984   0.12260   0.12040  -0.0031   1.0000   0.0096
 -14.250  -0.6592   0.10230   0.09995  -0.0140   1.0000   0.0089
 -14.000  -0.7131   0.08526   0.08265  -0.0248   1.0000   0.0086
 -13.750  -0.7442   0.07488   0.07205  -0.0318   1.0000   0.0084
 -13.500  -0.7851   0.06424   0.06109  -0.0389   1.0000   0.0081
 -13.250  -0.7959   0.05922   0.05596  -0.0422   1.0000   0.0082
 -13.000  -0.8191   0.05270   0.04919  -0.0459   1.0000   0.0080
 -12.750  -0.8254   0.04882   0.04522  -0.0483   1.0000   0.0081
 -12.500  -0.8378   0.04421   0.04041  -0.0505   1.0000   0.0079
 -12.250  -0.8301   0.03986   0.03570  -0.0562   0.8783   0.0079
 -12.000  -0.8370   0.03744   0.03284  -0.0559   0.7952   0.0080
 -11.750  -0.8416   0.03476   0.02987  -0.0563   0.7616   0.0080
 -11.250  -0.8459   0.03087   0.02558  -0.0550   0.7221   0.0083
 -11.000  -0.8447   0.02936   0.02386  -0.0530   0.7089   0.0083
 -10.750  -0.8358   0.02793   0.02225  -0.0519   0.6977   0.0085
 -10.500  -0.8236   0.02664   0.02079  -0.0508   0.6882   0.0088
 -10.250  -0.8096   0.02536   0.01933  -0.0498   0.6797   0.0091
 -10.000  -0.7935   0.02418   0.01799  -0.0489   0.6722   0.0093
  -9.750  -0.7753   0.02319   0.01682  -0.0481   0.6651   0.0096
  -9.500  -0.7568   0.02214   0.01563  -0.0474   0.6590   0.0099
  -9.250  -0.7415   0.02064   0.01404  -0.0464   0.6528   0.0104
  -9.000  -0.7210   0.01979   0.01308  -0.0458   0.6475   0.0108
  -8.750  -0.6989   0.01905   0.01226  -0.0453   0.6425   0.0114
  -8.500  -0.6764   0.01829   0.01141  -0.0448   0.6376   0.0121
  -8.250  -0.6532   0.01763   0.01062  -0.0443   0.6333   0.0128
  -8.000  -0.6315   0.01675   0.00967  -0.0438   0.6294   0.0143
  -7.750  -0.6062   0.01627   0.00911  -0.0435   0.6254   0.0161
  -7.500  -0.5825   0.01555   0.00836  -0.0431   0.6216   0.0188
  -7.250  -0.5581   0.01492   0.00767  -0.0428   0.6179   0.0227
  -7.000  -0.5331   0.01440   0.00708  -0.0425   0.6144   0.0278
  -6.750  -0.5073   0.01387   0.00656  -0.0423   0.6111   0.0344
  -6.500  -0.4814   0.01340   0.00610  -0.0421   0.6079   0.0436
  -6.250  -0.4552   0.01296   0.00568  -0.0419   0.6048   0.0562
  -6.000  -0.4292   0.01252   0.00528  -0.0418   0.6020   0.0746
  -5.750  -0.4032   0.01211   0.00493  -0.0417   0.5992   0.0998
  -5.500  -0.3768   0.01164   0.00460  -0.0416   0.5966   0.1319
  -5.250  -0.3501   0.01122   0.00430  -0.0416   0.5937   0.1674
  -5.000  -0.3235   0.01079   0.00401  -0.0415   0.5909   0.2077
  -4.750  -0.2968   0.01039   0.00374  -0.0415   0.5884   0.2530
  -4.500  -0.2700   0.01004   0.00353  -0.0415   0.5861   0.3020
  -4.250  -0.2430   0.00981   0.00341  -0.0414   0.5837   0.3487
  -4.000  -0.2150   0.00966   0.00336  -0.0414   0.5816   0.3843
  -3.750  -0.1865   0.00960   0.00334  -0.0414   0.5791   0.4112
  -3.500  -0.1578   0.00962   0.00335  -0.0415   0.5765   0.4314
  -3.250  -0.1289   0.00966   0.00336  -0.0415   0.5741   0.4460
  -3.000  -0.0999   0.00973   0.00336  -0.0416   0.5720   0.4578
  -2.750  -0.0710   0.00983   0.00338  -0.0416   0.5700   0.4676
  -2.500  -0.0422   0.00995   0.00345  -0.0417   0.5678   0.4757
  -2.250  -0.0131   0.01000   0.00346  -0.0418   0.5658   0.4838
  -2.000   0.0158   0.01001   0.00347  -0.0419   0.5635   0.4904
  -1.750   0.0448   0.01006   0.00349  -0.0420   0.5613   0.4969
  -1.500   0.0738   0.01010   0.00348  -0.0421   0.5592   0.5027
  -1.250   0.1027   0.01011   0.00349  -0.0422   0.5572   0.5078
  -1.000   0.1316   0.01018   0.00350  -0.0423   0.5553   0.5134
  -0.750   0.1605   0.01026   0.00352  -0.0424   0.5532   0.5186
  -0.500   0.1893   0.01028   0.00358  -0.0426   0.5512   0.5233
  -0.250   0.2183   0.01030   0.00360  -0.0427   0.5492   0.5281
   0.000   0.2474   0.01036   0.00363  -0.0429   0.5472   0.5323
   0.250   0.2761   0.01032   0.00362  -0.0430   0.5450   0.5363
   0.500   0.3050   0.01034   0.00364  -0.0432   0.5428   0.5407
   0.750   0.3340   0.01038   0.00366  -0.0433   0.5408   0.5453
   1.000   0.3628   0.01044   0.00368  -0.0435   0.5390   0.5491
   1.250   0.3915   0.01053   0.00378  -0.0436   0.5369   0.5528
   1.500   0.4203   0.01052   0.00383  -0.0438   0.5349   0.5565
   1.750   0.4492   0.01055   0.00388  -0.0440   0.5326   0.5604
   2.000   0.4781   0.01058   0.00393  -0.0442   0.5303   0.5638
   2.250   0.5067   0.01056   0.00395  -0.0443   0.5279   0.5674
   2.500   0.5355   0.01058   0.00398  -0.0445   0.5257   0.5711
   2.750   0.5643   0.01064   0.00404  -0.0446   0.5234   0.5749
   3.000   0.5929   0.01076   0.00415  -0.0448   0.5210   0.5787
   3.250   0.6213   0.01071   0.00421  -0.0449   0.5181   0.5827
   3.500   0.6498   0.01070   0.00427  -0.0450   0.5150   0.5868
   3.750   0.6784   0.01070   0.00429  -0.0452   0.5119   0.5913
   4.000   0.7071   0.01070   0.00431  -0.0453   0.5091   0.5959
   4.250   0.7353   0.01077   0.00441  -0.0454   0.5060   0.6009
   4.500   0.7635   0.01074   0.00449  -0.0455   0.5024   0.6064
   4.750   0.7917   0.01070   0.00453  -0.0456   0.4985   0.6122
   5.000   0.8200   0.01066   0.00454  -0.0456   0.4949   0.6194
   5.250   0.8482   0.01071   0.00460  -0.0457   0.4913   0.6277
   5.500   0.8758   0.01064   0.00471  -0.0457   0.4871   0.6379
   5.750   0.9035   0.01057   0.00475  -0.0457   0.4825   0.6517
   6.000   0.9309   0.01048   0.00477  -0.0456   0.4780   0.6744
   6.250   0.9564   0.01028   0.00488  -0.0452   0.4727   0.7350
   6.500   0.9997   0.00975   0.00493  -0.0482   0.4658   1.0000
   6.750   1.0270   0.00981   0.00499  -0.0482   0.4599   1.0000
   7.000   1.0543   0.00984   0.00509  -0.0481   0.4523   1.0000
   7.250   1.0812   0.00990   0.00517  -0.0480   0.4443   1.0000
   7.500   1.1079   0.00997   0.00527  -0.0479   0.4342   1.0000
   7.750   1.1344   0.01008   0.00542  -0.0477   0.4222   1.0000
   8.000   1.1600   0.01024   0.00559  -0.0474   0.4063   1.0000
   8.250   1.1846   0.01050   0.00581  -0.0471   0.3863   1.0000
   8.500   1.2072   0.01093   0.00615  -0.0465   0.3590   1.0000
   8.750   1.2271   0.01157   0.00664  -0.0456   0.3232   1.0000
   9.000   1.2436   0.01247   0.00736  -0.0443   0.2848   1.0000
   9.250   1.2590   0.01340   0.00813  -0.0430   0.2505   1.0000
   9.500   1.2729   0.01437   0.00895  -0.0415   0.2203   1.0000
   9.750   1.2849   0.01536   0.00982  -0.0398   0.1933   1.0000
  10.000   1.2941   0.01641   0.01075  -0.0377   0.1705   1.0000
  10.250   1.3009   0.01745   0.01171  -0.0354   0.1506   1.0000
  10.500   1.3000   0.01857   0.01280  -0.0320   0.1362   1.0000
  10.750   1.2975   0.02009   0.01430  -0.0294   0.1235   1.0000
  11.000   1.2959   0.02202   0.01620  -0.0279   0.1110   1.0000
  11.250   1.2956   0.02412   0.01828  -0.0269   0.1001   1.0000
  11.500   1.2944   0.02641   0.02054  -0.0260   0.0894   1.0000
  11.750   1.2956   0.02855   0.02268  -0.0252   0.0803   1.0000
  12.000   1.2964   0.03076   0.02488  -0.0245   0.0718   1.0000
  12.250   1.2952   0.03316   0.02727  -0.0238   0.0647   1.0000
  12.500   1.2957   0.03544   0.02955  -0.0232   0.0579   1.0000
  12.750   1.2965   0.03772   0.03184  -0.0226   0.0524   1.0000
  13.000   1.2958   0.04016   0.03428  -0.0221   0.0472   1.0000
  13.250   1.2968   0.04247   0.03663  -0.0217   0.0428   1.0000
  13.500   1.2964   0.04495   0.03912  -0.0213   0.0389   1.0000
  13.750   1.2956   0.04758   0.04179  -0.0211   0.0358   1.0000
  14.000   1.2990   0.04987   0.04411  -0.0210   0.0326   1.0000
  14.250   1.2963   0.05288   0.04713  -0.0210   0.0297   1.0000
  14.500   1.2997   0.05531   0.04963  -0.0210   0.0277   1.0000
  14.750   1.3018   0.05791   0.05227  -0.0211   0.0255   1.0000
  15.000   1.2975   0.06137   0.05574  -0.0215   0.0233   1.0000
  15.250   1.3014   0.06388   0.05834  -0.0217   0.0218   1.0000
  15.500   1.3034   0.06670   0.06121  -0.0221   0.0201   1.0000
  15.750   1.2993   0.07034   0.06490  -0.0227   0.0188   1.0000
  16.000   1.2989   0.07358   0.06823  -0.0233   0.0178   1.0000
  16.250   1.3010   0.07656   0.07129  -0.0239   0.0164   1.0000
  16.500   1.2992   0.08011   0.07488  -0.0247   0.0153   1.0000
  16.750   1.2935   0.08431   0.07914  -0.0258   0.0142   1.0000
  17.000   1.2928   0.08786   0.08280  -0.0268   0.0135   1.0000
  17.250   1.2934   0.09129   0.08629  -0.0278   0.0125   1.0000
  17.500   1.2896   0.09545   0.09053  -0.0292   0.0120   1.0000
  17.750   1.2814   0.10037   0.09552  -0.0309   0.0115   1.0000
<< Back to EPPLER 715 AIRFOIL (e715-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER 715 AIRFOIL (e715-il)