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EPPLER E853 AIRFOIL (e853-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER E853 AIRFOIL (e853-il)
Reynolds number: 50,000
Max Cl/Cd: 35.56 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e853-il-50000.txt
Download as CSV file: xf-e853-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E853 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3603   0.10342   0.09689  -0.0287   1.0000   0.2949
  -8.250  -0.3688   0.10148   0.09508  -0.0278   1.0000   0.3054
  -8.000  -0.3800   0.09999   0.09374  -0.0262   1.0000   0.3178
  -7.750  -0.3761   0.09716   0.09097  -0.0245   1.0000   0.3306
  -7.500  -0.3859   0.09553   0.08947  -0.0220   1.0000   0.3451
  -7.250  -0.3672   0.09110   0.08505  -0.0206   1.0000   0.3558
  -7.000  -0.3795   0.08912   0.08322  -0.0184   1.0000   0.3611
  -6.500  -0.4704   0.06772   0.06287  -0.0310   1.0000   0.1608
  -6.250  -0.5275   0.06408   0.05838  -0.0469   1.0000   0.1340
  -6.000  -0.5259   0.05770   0.05160  -0.0503   1.0000   0.1190
  -5.750  -0.5149   0.05175   0.04496  -0.0535   1.0000   0.1076
  -5.500  -0.4982   0.04692   0.03963  -0.0550   1.0000   0.1018
  -5.250  -0.4733   0.04272   0.03427  -0.0568   1.0000   0.0965
  -5.000  -0.4496   0.03937   0.03042  -0.0571   1.0000   0.0964
  -4.750  -0.4284   0.03661   0.02755  -0.0571   1.0000   0.1034
  -4.500  -0.4020   0.03423   0.02449  -0.0572   1.0000   0.1111
  -4.250  -0.3788   0.03200   0.02219  -0.0564   1.0000   0.1204
  -4.000  -0.3560   0.03018   0.02030  -0.0557   1.0000   0.1406
  -3.750  -0.3334   0.02845   0.01860  -0.0545   1.0000   0.1665
  -3.500  -0.3103   0.02651   0.01702  -0.0539   1.0000   0.2198
  -3.250  -0.2931   0.02501   0.01779  -0.0505   1.0000   0.5344
  -3.000  -0.2922   0.02625   0.01909  -0.0429   1.0000   0.6232
  -2.750  -0.2915   0.02695   0.01981  -0.0357   1.0000   0.6713
  -2.500  -0.2889   0.02732   0.02011  -0.0295   1.0000   0.7122
  -2.250  -0.2847   0.02746   0.02009  -0.0240   1.0000   0.7498
  -2.000  -0.2829   0.02743   0.01999  -0.0180   1.0000   0.7849
  -1.750  -0.2808   0.02725   0.01973  -0.0124   1.0000   0.8209
  -1.500  -0.2784   0.02693   0.01932  -0.0070   1.0000   0.8572
  -1.250  -0.2721   0.02652   0.01883  -0.0028   1.0000   0.8930
  -1.000  -0.2505   0.02626   0.01841  -0.0023   1.0000   0.9294
  -0.750  -0.2005   0.02638   0.01825  -0.0085   1.0000   0.9636
  -0.500  -0.1612   0.02623   0.01783  -0.0139   1.0000   1.0000
  -0.250  -0.1402   0.02613   0.01751  -0.0163   1.0000   1.0000
   0.000  -0.1105   0.02639   0.01753  -0.0202   1.0000   1.0000
   0.250  -0.0779   0.02687   0.01776  -0.0243   1.0000   1.0000
   0.500  -0.0451   0.02748   0.01809  -0.0283   1.0000   1.0000
   0.750  -0.0136   0.02817   0.01856  -0.0318   1.0000   1.0000
   1.000   0.0158   0.02892   0.01910  -0.0346   1.0000   1.0000
   1.250   0.0431   0.02971   0.01971  -0.0369   1.0000   1.0000
   1.500   0.0686   0.03054   0.02034  -0.0387   1.0000   1.0000
   1.750   0.1047   0.03187   0.02150  -0.0424   0.9947   1.0000
   2.000   0.1405   0.03315   0.02266  -0.0460   0.9868   1.0000
   2.250   0.1771   0.03455   0.02395  -0.0496   0.9785   1.0000
   2.500   0.2167   0.03612   0.02543  -0.0536   0.9699   1.0000
   2.750   0.2411   0.03705   0.02632  -0.0550   0.9626   1.0000
   3.000   0.2742   0.03839   0.02763  -0.0577   0.9535   1.0000
   3.250   0.3112   0.03989   0.02913  -0.0611   0.9436   1.0000
   3.500   0.3351   0.04094   0.03019  -0.0623   0.9344   1.0000
   3.750   0.3639   0.04222   0.03149  -0.0642   0.9238   1.0000
   4.000   0.3948   0.04356   0.03288  -0.0664   0.9120   1.0000
   4.250   0.4260   0.04491   0.03435  -0.0685   0.8993   1.0000
   4.500   0.4567   0.04624   0.03576  -0.0705   0.8856   1.0000
   4.750   0.4867   0.04756   0.03719  -0.0722   0.8710   1.0000
   5.000   0.5171   0.04887   0.03862  -0.0739   0.8553   1.0000
   5.250   0.5524   0.05017   0.04012  -0.0761   0.8382   1.0000
   5.500   0.5893   0.05140   0.04154  -0.0782   0.8196   1.0000
   5.750   0.6158   0.05249   0.04281  -0.0788   0.7996   1.0000
   6.000   0.6590   0.05336   0.04394  -0.0810   0.7783   1.0000
   6.250   0.6929   0.05406   0.04495  -0.0818   0.7551   1.0000
   6.500   0.7286   0.05446   0.04564  -0.0823   0.7299   1.0000
   6.750   0.7773   0.05386   0.04543  -0.0829   0.7015   1.0000
   7.000   0.8536   0.05042   0.04268  -0.0836   0.6679   1.0000
   7.250   0.9699   0.04027   0.03357  -0.0819   0.6233   1.0000
   7.500   1.0472   0.02945   0.02342  -0.0738   0.5162   1.0000
   7.750   1.0385   0.02953   0.02167  -0.0637   0.3232   1.0000
   8.000   1.0304   0.03282   0.02395  -0.0587   0.2441   1.0000
   8.250   1.0410   0.03587   0.02638  -0.0561   0.1849   1.0000
   8.500   1.0960   0.03996   0.03001  -0.0588   0.1302   1.0000
   8.750   1.1447   0.04446   0.03452  -0.0609   0.1052   1.0000
   9.000   1.1760   0.04881   0.03908  -0.0609   0.0935   1.0000
   9.250   1.1923   0.05262   0.04344  -0.0589   0.0876   1.0000
   9.500   1.2076   0.05689   0.04786  -0.0578   0.0813   1.0000
   9.750   1.2083   0.06060   0.05216  -0.0545   0.0794   1.0000
  10.000   1.2083   0.06489   0.05693  -0.0516   0.0792   1.0000
  10.250   1.2034   0.06925   0.06169  -0.0486   0.0796   1.0000
  10.500   1.1947   0.07355   0.06634  -0.0457   0.0802   1.0000
  10.750   1.1833   0.07781   0.07087  -0.0429   0.0810   1.0000
  11.000   1.1723   0.08235   0.07562  -0.0407   0.0817   1.0000
  11.250   1.1661   0.08761   0.08102  -0.0393   0.0825   1.0000
  11.500   1.1216   0.09008   0.08390  -0.0366   0.0843   1.0000
  11.750   1.0757   0.09534   0.08946  -0.0374   0.0862   1.0000
  12.000   1.0357   0.10246   0.09675  -0.0407   0.0886   1.0000
  12.250   1.0054   0.11052   0.10490  -0.0452   0.0910   1.0000
  12.500   0.9884   0.11837   0.11276  -0.0491   0.0934   1.0000
  12.750   0.9902   0.12480   0.11920  -0.0505   0.0953   1.0000
  13.000   0.9549   0.13948   0.13389  -0.0615   0.1093   1.0000
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