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EPPLER E852 AIRFOIL (e852-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER E852 AIRFOIL (e852-il)
Reynolds number: 50,000
Max Cl/Cd: 35.63 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e852-il-50000-n5.txt
Download as CSV file: xf-e852-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E852 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4235   0.10249   0.09556  -0.0442   1.0000   0.0384
  -9.250  -0.4258   0.09869   0.09185  -0.0450   1.0000   0.0375
  -9.000  -0.4300   0.09486   0.08812  -0.0460   1.0000   0.0376
  -8.750  -0.4352   0.09100   0.08436  -0.0468   1.0000   0.0368
  -8.250  -0.4742   0.07898   0.07254  -0.0538   1.0000   0.0308
  -8.000  -0.4861   0.07578   0.06943  -0.0537   1.0000   0.0306
  -7.750  -0.4977   0.07246   0.06615  -0.0536   1.0000   0.0304
  -7.500  -0.5086   0.06920   0.06288  -0.0532   1.0000   0.0301
  -7.250  -0.5184   0.06583   0.05945  -0.0527   1.0000   0.0301
  -7.000  -0.5257   0.06236   0.05583  -0.0524   1.0000   0.0302
  -6.750  -0.5287   0.05881   0.05207  -0.0520   1.0000   0.0302
  -6.500  -0.5276   0.05522   0.04813  -0.0519   1.0000   0.0306
  -6.250  -0.5224   0.05149   0.04408  -0.0519   1.0000   0.0311
  -6.000  -0.5135   0.04775   0.04004  -0.0518   1.0000   0.0317
  -5.750  -0.5008   0.04442   0.03637  -0.0518   1.0000   0.0325
  -5.500  -0.4843   0.04125   0.03262  -0.0517   1.0000   0.0331
  -5.250  -0.4652   0.03833   0.02928  -0.0514   1.0000   0.0339
  -5.000  -0.4440   0.03570   0.02623  -0.0510   1.0000   0.0352
  -4.750  -0.4217   0.03344   0.02358  -0.0503   1.0000   0.0370
  -4.500  -0.3989   0.03159   0.02128  -0.0493   1.0000   0.0414
  -4.250  -0.3700   0.02993   0.01948  -0.0501   0.9969   0.0509
  -4.000  -0.3402   0.02820   0.01753  -0.0501   0.9939   0.0587
  -3.750  -0.3105   0.02682   0.01603  -0.0510   0.9901   0.0788
  -3.500  -0.2791   0.02516   0.01440  -0.0525   0.9865   0.1120
  -3.250  -0.2470   0.02245   0.01326  -0.0556   0.9843   0.3488
  -3.000  -0.2221   0.02256   0.01378  -0.0545   0.9798   0.5450
  -2.750  -0.1995   0.02286   0.01389  -0.0528   0.9743   0.6141
  -2.500  -0.1769   0.02322   0.01419  -0.0508   0.9695   0.6705
  -2.250  -0.1573   0.02334   0.01422  -0.0485   0.9640   0.7086
  -2.000  -0.1314   0.02339   0.01406  -0.0480   0.9591   0.7338
  -1.750  -0.1020   0.02342   0.01384  -0.0486   0.9549   0.7535
  -1.500  -0.0772   0.02338   0.01364  -0.0484   0.9495   0.7704
  -1.250  -0.0479   0.02340   0.01349  -0.0490   0.9451   0.7888
  -1.000  -0.0215   0.02341   0.01330  -0.0492   0.9403   0.8082
  -0.750   0.0041   0.02340   0.01320  -0.0491   0.9350   0.8293
  -0.500   0.0344   0.02344   0.01316  -0.0499   0.9309   0.8541
  -0.250   0.0603   0.02342   0.01311  -0.0500   0.9254   0.8858
   0.000   0.1000   0.02345   0.01304  -0.0531   0.9209   0.9346
   0.250   0.1428   0.02358   0.01303  -0.0573   0.9168   1.0000
   0.500   0.1704   0.02386   0.01316  -0.0586   0.9104   1.0000
   0.750   0.2057   0.02421   0.01337  -0.0612   0.9058   1.0000
   1.000   0.2356   0.02457   0.01363  -0.0626   0.9002   1.0000
   1.250   0.2663   0.02494   0.01393  -0.0641   0.8944   1.0000
   1.500   0.3013   0.02533   0.01426  -0.0662   0.8899   1.0000
   1.750   0.3261   0.02573   0.01464  -0.0665   0.8825   1.0000
   2.000   0.3620   0.02611   0.01502  -0.0686   0.8777   1.0000
   2.250   0.3852   0.02655   0.01552  -0.0685   0.8697   1.0000
   2.500   0.4212   0.02692   0.01594  -0.0705   0.8645   1.0000
   2.750   0.4443   0.02738   0.01645  -0.0703   0.8558   1.0000
   3.000   0.4795   0.02773   0.01690  -0.0720   0.8498   1.0000
   3.250   0.5050   0.02816   0.01744  -0.0721   0.8407   1.0000
   3.500   0.5330   0.02855   0.01807  -0.0726   0.8318   1.0000
   3.750   0.5708   0.02875   0.01847  -0.0744   0.8246   1.0000
   4.000   0.5968   0.02910   0.01900  -0.0743   0.8134   1.0000
   4.250   0.6259   0.02934   0.01946  -0.0745   0.8019   1.0000
   4.500   0.6578   0.02940   0.01979  -0.0748   0.7896   1.0000
   4.750   0.6932   0.02916   0.01998  -0.0753   0.7754   1.0000
   5.000   0.7425   0.02802   0.01927  -0.0767   0.7577   1.0000
   5.250   0.7769   0.02685   0.01846  -0.0753   0.7286   1.0000
   5.500   0.8078   0.02543   0.01738  -0.0727   0.6895   1.0000
   5.750   0.8221   0.02484   0.01704  -0.0685   0.6409   1.0000
   6.000   0.8462   0.02375   0.01596  -0.0647   0.5293   1.0000
   6.250   0.8586   0.02518   0.01558  -0.0602   0.2787   1.0000
   6.500   0.8558   0.02755   0.01715  -0.0562   0.1800   1.0000
   6.750   0.8605   0.02979   0.01905  -0.0534   0.1231   1.0000
   7.000   0.8712   0.03188   0.02101  -0.0511   0.0960   1.0000
   7.250   0.8862   0.03382   0.02287  -0.0495   0.0708   1.0000
   7.500   0.9143   0.03618   0.02532  -0.0489   0.0558   1.0000
   7.750   0.9422   0.03848   0.02764  -0.0491   0.0416   1.0000
   8.000   0.9919   0.04233   0.03199  -0.0509   0.0344   1.0000
   8.250   1.0148   0.04538   0.03522  -0.0505   0.0304   1.0000
   8.500   1.0331   0.04882   0.03918  -0.0492   0.0270   1.0000
   8.750   1.0459   0.05219   0.04309  -0.0473   0.0247   1.0000
   9.000   1.0531   0.05592   0.04730  -0.0450   0.0238   1.0000
   9.250   1.0542   0.05973   0.05154  -0.0424   0.0233   1.0000
   9.500   1.0498   0.06340   0.05560  -0.0395   0.0231   1.0000
   9.750   1.0400   0.06699   0.05951  -0.0364   0.0230   1.0000
  10.000   1.0271   0.07069   0.06349  -0.0337   0.0230   1.0000
  10.250   1.0115   0.07462   0.06769  -0.0317   0.0230   1.0000
  10.500   0.9942   0.07891   0.07220  -0.0307   0.0231   1.0000
  10.750   0.9757   0.08364   0.07714  -0.0307   0.0234   1.0000
  11.000   0.9557   0.08905   0.08273  -0.0319   0.0236   1.0000
  11.250   0.9360   0.09510   0.08892  -0.0344   0.0239   1.0000
  11.500   0.9170   0.10196   0.09587  -0.0381   0.0243   1.0000
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