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=5


Details Polar file
Airfoil: EPPLER 715 AIRFOIL (e715-il)
Reynolds number: 500,000
Max Cl/Cd: 98 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e715-il-500000-n5.txt
Download as CSV file: xf-e715-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.250  -0.7405   0.12272   0.12003  -0.0008   1.0000   0.0044
 -16.000  -0.7688   0.11173   0.10887  -0.0069   1.0000   0.0042
 -15.750  -0.7905   0.10257   0.09958  -0.0121   1.0000   0.0042
 -15.500  -0.8130   0.09363   0.09051  -0.0172   1.0000   0.0041
 -15.250  -0.8320   0.08562   0.08238  -0.0220   1.0000   0.0042
 -15.000  -0.8480   0.07852   0.07514  -0.0262   1.0000   0.0041
 -14.750  -0.8624   0.07189   0.06840  -0.0302   1.0000   0.0042
 -14.500  -0.8750   0.06604   0.06243  -0.0337   1.0000   0.0043
 -14.250  -0.8895   0.06039   0.05665  -0.0370   1.0000   0.0041
 -14.000  -0.8874   0.05478   0.05055  -0.0437   0.8215   0.0043
 -13.750  -0.8967   0.05102   0.04652  -0.0451   0.7769   0.0043
 -13.500  -0.9079   0.04694   0.04223  -0.0468   0.7517   0.0042
 -13.250  -0.9119   0.04375   0.03887  -0.0481   0.7316   0.0044
 -13.000  -0.9188   0.04032   0.03525  -0.0494   0.7156   0.0043
 -12.750  -0.9204   0.03749   0.03227  -0.0504   0.7021   0.0044
 -12.500  -0.9245   0.03441   0.02903  -0.0516   0.6903   0.0044
 -12.250  -0.9257   0.03170   0.02616  -0.0527   0.6794   0.0044
 -12.000  -0.9285   0.02932   0.02363  -0.0531   0.6699   0.0045
 -11.750  -0.9304   0.02775   0.02191  -0.0514   0.6611   0.0045
 -11.500  -0.9234   0.02649   0.02051  -0.0501   0.6529   0.0046
 -11.250  -0.9117   0.02533   0.01920  -0.0491   0.6454   0.0048
 -11.000  -0.8976   0.02424   0.01797  -0.0483   0.6384   0.0049
 -10.750  -0.8815   0.02325   0.01684  -0.0475   0.6320   0.0051
 -10.500  -0.8633   0.02236   0.01581  -0.0468   0.6266   0.0052
 -10.250  -0.8442   0.02148   0.01482  -0.0462   0.6211   0.0054
 -10.000  -0.8251   0.02055   0.01377  -0.0455   0.6162   0.0056
  -9.750  -0.8039   0.01980   0.01293  -0.0450   0.6118   0.0059
  -9.500  -0.7815   0.01914   0.01218  -0.0446   0.6072   0.0061
  -9.250  -0.7587   0.01851   0.01145  -0.0442   0.6027   0.0065
  -9.000  -0.7352   0.01793   0.01075  -0.0438   0.5986   0.0069
  -8.750  -0.7111   0.01738   0.01010  -0.0435   0.5947   0.0073
  -8.500  -0.6872   0.01677   0.00944  -0.0432   0.5908   0.0080
  -8.250  -0.6624   0.01630   0.00889  -0.0429   0.5873   0.0089
  -8.000  -0.6373   0.01584   0.00835  -0.0426   0.5842   0.0102
  -7.750  -0.6120   0.01537   0.00783  -0.0424   0.5813   0.0118
  -7.500  -0.5863   0.01493   0.00735  -0.0422   0.5784   0.0136
  -7.250  -0.5602   0.01454   0.00691  -0.0420   0.5754   0.0160
  -7.000  -0.5342   0.01414   0.00647  -0.0418   0.5725   0.0190
  -6.750  -0.5079   0.01379   0.00608  -0.0417   0.5697   0.0227
  -6.500  -0.4814   0.01344   0.00570  -0.0416   0.5671   0.0282
  -6.250  -0.4548   0.01307   0.00535  -0.0415   0.5645   0.0353
  -6.000  -0.4280   0.01272   0.00502  -0.0414   0.5620   0.0448
  -5.750  -0.4012   0.01238   0.00470  -0.0413   0.5596   0.0567
  -5.500  -0.3742   0.01205   0.00439  -0.0413   0.5573   0.0715
  -5.250  -0.3473   0.01172   0.00410  -0.0412   0.5552   0.0896
  -5.000  -0.3202   0.01142   0.00384  -0.0412   0.5530   0.1107
  -4.750  -0.2931   0.01108   0.00358  -0.0412   0.5509   0.1382
  -4.500  -0.2659   0.01073   0.00334  -0.0412   0.5486   0.1696
  -4.250  -0.2385   0.01040   0.00312  -0.0412   0.5464   0.2023
  -4.000  -0.2110   0.01012   0.00292  -0.0412   0.5443   0.2354
  -3.750  -0.1835   0.00983   0.00273  -0.0412   0.5424   0.2728
  -3.500  -0.1562   0.00955   0.00257  -0.0413   0.5404   0.3165
  -3.250  -0.1284   0.00936   0.00247  -0.0413   0.5385   0.3540
  -3.000  -0.1003   0.00925   0.00242  -0.0413   0.5365   0.3832
  -2.750  -0.0716   0.00919   0.00239  -0.0414   0.5346   0.4043
  -2.500  -0.0427   0.00916   0.00237  -0.0414   0.5327   0.4210
  -2.250  -0.0138   0.00915   0.00236  -0.0415   0.5308   0.4336
  -2.000   0.0151   0.00916   0.00234  -0.0416   0.5289   0.4440
  -1.750   0.0442   0.00918   0.00232  -0.0418   0.5269   0.4529
  -1.500   0.0730   0.00920   0.00231  -0.0418   0.5250   0.4596
  -1.250   0.1020   0.00923   0.00230  -0.0420   0.5231   0.4661
  -1.000   0.1309   0.00927   0.00229  -0.0421   0.5215   0.4719
  -0.750   0.1599   0.00928   0.00231  -0.0422   0.5199   0.4776
  -0.500   0.1890   0.00930   0.00232  -0.0424   0.5180   0.4832
  -0.250   0.2181   0.00931   0.00232  -0.0425   0.5159   0.4873
   0.000   0.2470   0.00932   0.00233  -0.0426   0.5139   0.4913
   0.250   0.2759   0.00934   0.00235  -0.0428   0.5120   0.4956
   0.500   0.3049   0.00939   0.00236  -0.0429   0.5103   0.5001
   0.750   0.3337   0.00941   0.00238  -0.0430   0.5085   0.5037
   1.000   0.3623   0.00946   0.00241  -0.0432   0.5066   0.5072
   1.250   0.3913   0.00947   0.00246  -0.0433   0.5048   0.5105
   1.500   0.4203   0.00950   0.00250  -0.0435   0.5029   0.5138
   1.750   0.4493   0.00954   0.00254  -0.0437   0.5007   0.5167
   2.000   0.4780   0.00954   0.00259  -0.0438   0.4985   0.5195
   2.250   0.5067   0.00956   0.00264  -0.0439   0.4964   0.5224
   2.500   0.5354   0.00960   0.00268  -0.0441   0.4943   0.5253
   2.750   0.5640   0.00966   0.00274  -0.0442   0.4921   0.5285
   3.000   0.5927   0.00971   0.00281  -0.0444   0.4897   0.5315
   3.250   0.6214   0.00972   0.00289  -0.0445   0.4867   0.5341
   3.500   0.6499   0.00973   0.00296  -0.0446   0.4833   0.5372
   3.750   0.6784   0.00976   0.00302  -0.0447   0.4800   0.5406
   4.000   0.7067   0.00982   0.00307  -0.0448   0.4768   0.5440
   4.250   0.7353   0.00985   0.00317  -0.0450   0.4730   0.5471
   4.500   0.7637   0.00987   0.00326  -0.0451   0.4686   0.5505
   4.750   0.7918   0.00990   0.00334  -0.0452   0.4643   0.5544
   5.000   0.8199   0.00995   0.00343  -0.0453   0.4598   0.5587
   5.250   0.8482   0.00999   0.00354  -0.0454   0.4544   0.5627
   5.500   0.8760   0.01004   0.00364  -0.0454   0.4489   0.5670
   5.750   0.9039   0.01009   0.00377  -0.0455   0.4430   0.5723
   6.000   0.9316   0.01015   0.00389  -0.0455   0.4353   0.5784
   6.250   0.9590   0.01022   0.00403  -0.0455   0.4262   0.5852
   6.500   0.9860   0.01032   0.00417  -0.0454   0.4159   0.5931
   6.750   1.0125   0.01044   0.00434  -0.0453   0.4030   0.6024
   7.000   1.0385   0.01061   0.00454  -0.0452   0.3871   0.6145
   7.250   1.0633   0.01085   0.00481  -0.0449   0.3657   0.6326
   7.500   1.0858   0.01121   0.00517  -0.0443   0.3374   0.6633
   7.750   1.1041   0.01150   0.00565  -0.0430   0.3067   0.7652
   8.000   1.1366   0.01199   0.00635  -0.0448   0.2677   1.0000
   8.250   1.1552   0.01278   0.00699  -0.0439   0.2365   1.0000
   8.500   1.1732   0.01355   0.00764  -0.0428   0.2102   1.0000
   8.750   1.1902   0.01435   0.00832  -0.0417   0.1857   1.0000
   9.000   1.2060   0.01515   0.00903  -0.0404   0.1631   1.0000
   9.250   1.2194   0.01603   0.00982  -0.0389   0.1429   1.0000
   9.500   1.2319   0.01688   0.01060  -0.0372   0.1263   1.0000
   9.750   1.2415   0.01776   0.01144  -0.0352   0.1126   1.0000
  10.000   1.2435   0.01877   0.01242  -0.0322   0.1014   1.0000
  10.250   1.2455   0.02002   0.01367  -0.0299   0.0921   1.0000
  10.500   1.2488   0.02154   0.01520  -0.0285   0.0842   1.0000
  10.750   1.2514   0.02335   0.01701  -0.0274   0.0757   1.0000
  11.000   1.2549   0.02522   0.01888  -0.0266   0.0677   1.0000
  11.250   1.2595   0.02706   0.02073  -0.0259   0.0616   1.0000
  11.500   1.2620   0.02910   0.02277  -0.0252   0.0552   1.0000
  11.750   1.2668   0.03097   0.02466  -0.0246   0.0502   1.0000
  12.000   1.2685   0.03312   0.02681  -0.0240   0.0449   1.0000
  12.250   1.2733   0.03502   0.02875  -0.0235   0.0411   1.0000
  12.500   1.2746   0.03725   0.03098  -0.0229   0.0369   1.0000
  12.750   1.2789   0.03923   0.03299  -0.0225   0.0336   1.0000
  13.000   1.2807   0.04146   0.03524  -0.0221   0.0302   1.0000
  13.250   1.2837   0.04361   0.03743  -0.0217   0.0276   1.0000
  13.500   1.2865   0.04580   0.03967  -0.0214   0.0251   1.0000
  13.750   1.2888   0.04815   0.04204  -0.0213   0.0233   1.0000
  14.000   1.2929   0.05038   0.04433  -0.0212   0.0210   1.0000
  14.250   1.2956   0.05283   0.04680  -0.0212   0.0193   1.0000
  14.500   1.2989   0.05526   0.04929  -0.0212   0.0179   1.0000
  14.750   1.3026   0.05769   0.05177  -0.0213   0.0165   1.0000
  15.000   1.3043   0.06040   0.05452  -0.0215   0.0149   1.0000
  15.250   1.3071   0.06302   0.05720  -0.0218   0.0140   1.0000
  15.500   1.3097   0.06574   0.05999  -0.0222   0.0128   1.0000
  15.750   1.3118   0.06855   0.06287  -0.0226   0.0120   1.0000
  16.000   1.3124   0.07164   0.06601  -0.0231   0.0113   1.0000
  16.250   1.3148   0.07450   0.06894  -0.0236   0.0105   1.0000
  16.500   1.3156   0.07767   0.07219  -0.0243   0.0097   1.0000
  16.750   1.3154   0.08100   0.07557  -0.0251   0.0089   1.0000
  17.250   1.3148   0.08789   0.08262  -0.0270   0.0078   1.0000
  17.500   1.3146   0.09142   0.08624  -0.0281   0.0075   1.0000
  17.750   1.3128   0.09525   0.09016  -0.0293   0.0072   1.0000
  18.000   1.3101   0.09926   0.09426  -0.0307   0.0067   1.0000
  18.250   1.3066   0.10346   0.09852  -0.0322   0.0063   1.0000
  18.500   1.3037   0.10765   0.10282  -0.0338   0.0060   1.0000
  18.750   1.3009   0.11189   0.10717  -0.0355   0.0056   1.0000
  19.000   1.2975   0.11629   0.11166  -0.0374   0.0053   1.0000
  19.250   1.2929   0.12096   0.11642  -0.0395   0.0051   1.0000
<< Back to EPPLER 715 AIRFOIL (e715-il)

Polar data table (+)

Polar graphs


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