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EPPLER E852 AIRFOIL (e852-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER E852 AIRFOIL (e852-il)
Reynolds number: 200,000
Max Cl/Cd: 79.73 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e852-il-200000-n5.txt
Download as CSV file: xf-e852-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3514   0.09048   0.08719  -0.0431   1.0000   0.0120
  -9.500  -0.3601   0.08515   0.08199  -0.0439   1.0000   0.0114
  -9.250  -0.4400   0.08704   0.08368  -0.0453   1.0000   0.0102
  -9.000  -0.4357   0.08396   0.08064  -0.0458   1.0000   0.0095
  -8.750  -0.4458   0.07928   0.07603  -0.0469   1.0000   0.0096
  -8.500  -0.4626   0.07398   0.07083  -0.0481   1.0000   0.0098
  -7.500  -0.4442   0.04914   0.04544  -0.0763   0.9742   0.0091
  -7.250  -0.4339   0.04279   0.03871  -0.0811   0.9654   0.0089
  -7.000  -0.4173   0.03733   0.03280  -0.0844   0.9580   0.0088
  -6.750  -0.3987   0.03284   0.02782  -0.0862   0.9506   0.0087
  -6.500  -0.3737   0.02886   0.02330  -0.0880   0.9457   0.0087
  -6.250  -0.3461   0.02561   0.01947  -0.0894   0.9419   0.0087
  -6.000  -0.3206   0.02306   0.01650  -0.0897   0.9361   0.0087
  -5.750  -0.2900   0.02081   0.01390  -0.0907   0.9329   0.0088
  -5.500  -0.2571   0.01896   0.01177  -0.0921   0.9305   0.0091
  -5.250  -0.2309   0.01736   0.01000  -0.0921   0.9245   0.0095
  -5.000  -0.2009   0.01551   0.00793  -0.0931   0.9206   0.0113
  -4.750  -0.1671   0.01455   0.00683  -0.0947   0.9177   0.0156
  -4.500  -0.1380   0.01381   0.00602  -0.0953   0.9121   0.0294
  -4.250  -0.1065   0.01305   0.00533  -0.0965   0.9078   0.0588
  -4.000  -0.0733   0.01224   0.00475  -0.0983   0.9046   0.1235
  -3.750  -0.0454   0.01132   0.00423  -0.0993   0.8991   0.2498
  -3.500  -0.0159   0.01061   0.00405  -0.1003   0.8944   0.4080
  -3.250   0.0173   0.01043   0.00392  -0.1015   0.8910   0.4697
  -3.000   0.0454   0.01037   0.00384  -0.1016   0.8853   0.5021
  -2.750   0.0761   0.01031   0.00371  -0.1022   0.8807   0.5261
  -2.500   0.1083   0.01025   0.00362  -0.1031   0.8772   0.5529
  -2.250   0.1349   0.01024   0.00358  -0.1029   0.8711   0.5753
  -2.000   0.1650   0.01021   0.00349  -0.1033   0.8667   0.5893
  -1.750   0.1952   0.01016   0.00340  -0.1039   0.8626   0.5992
  -1.500   0.2228   0.01015   0.00336  -0.1039   0.8571   0.6082
  -1.250   0.2525   0.01013   0.00327  -0.1043   0.8529   0.6175
  -1.000   0.2813   0.01011   0.00324  -0.1046   0.8486   0.6261
  -0.750   0.3087   0.01011   0.00324  -0.1046   0.8434   0.6352
  -0.500   0.3379   0.01011   0.00323  -0.1049   0.8393   0.6451
  -0.250   0.3659   0.01011   0.00326  -0.1050   0.8349   0.6544
   0.000   0.3929   0.01013   0.00331  -0.1049   0.8299   0.6646
   0.250   0.4217   0.01013   0.00335  -0.1051   0.8259   0.6754
   0.500   0.4491   0.01016   0.00342  -0.1051   0.8214   0.6870
   0.750   0.4758   0.01019   0.00351  -0.1050   0.8164   0.6991
   1.000   0.5041   0.01020   0.00360  -0.1051   0.8122   0.7120
   1.250   0.5303   0.01023   0.00372  -0.1047   0.8069   0.7259
   1.500   0.5569   0.01025   0.00383  -0.1045   0.8013   0.7408
   1.750   0.5841   0.01025   0.00393  -0.1043   0.7961   0.7571
   2.000   0.6090   0.01027   0.00406  -0.1036   0.7887   0.7753
   2.250   0.6347   0.01025   0.00420  -0.1030   0.7811   0.7956
   2.500   0.6598   0.01021   0.00426  -0.1021   0.7716   0.8188
   2.750   0.6828   0.01015   0.00433  -0.1008   0.7594   0.8464
   3.000   0.7056   0.01005   0.00433  -0.0992   0.7440   0.8817
   3.250   0.7310   0.00992   0.00431  -0.0983   0.7222   0.9386
   3.500   0.7601   0.00991   0.00434  -0.0984   0.6995   1.0000
   3.750   0.7847   0.01000   0.00449  -0.0976   0.6752   1.0000
   4.000   0.8077   0.01013   0.00457  -0.0965   0.6365   1.0000
   4.250   0.8266   0.01047   0.00463  -0.0944   0.5596   1.0000
   4.500   0.8345   0.01147   0.00495  -0.0905   0.4320   1.0000
   4.750   0.8407   0.01280   0.00561  -0.0868   0.3053   1.0000
   5.000   0.8515   0.01401   0.00630  -0.0841   0.2035   1.0000
   5.250   0.8669   0.01498   0.00696  -0.0823   0.1388   1.0000
   5.500   0.8832   0.01591   0.00765  -0.0806   0.0904   1.0000
   5.750   0.9007   0.01676   0.00836  -0.0790   0.0580   1.0000
   6.000   0.9169   0.01774   0.00917  -0.0773   0.0271   1.0000
   6.250   0.9321   0.01888   0.01016  -0.0753   0.0093   1.0000
   6.500   0.9504   0.01976   0.01115  -0.0737   0.0061   1.0000
   6.750   0.9674   0.02078   0.01230  -0.0719   0.0051   1.0000
   7.000   0.9814   0.02218   0.01387  -0.0697   0.0044   1.0000
   7.250   0.9949   0.02374   0.01560  -0.0674   0.0041   1.0000
   7.500   1.0114   0.02519   0.01721  -0.0656   0.0040   1.0000
   7.750   1.0296   0.02689   0.01911  -0.0641   0.0039   1.0000
   8.000   1.0498   0.02896   0.02141  -0.0630   0.0037   1.0000
   8.250   1.0701   0.03130   0.02404  -0.0620   0.0037   1.0000
   8.500   1.0880   0.03394   0.02702  -0.0606   0.0036   1.0000
   8.750   1.1017   0.03679   0.03024  -0.0587   0.0036   1.0000
   9.000   1.1101   0.03988   0.03373  -0.0561   0.0036   1.0000
   9.250   1.1122   0.04304   0.03728  -0.0528   0.0036   1.0000
   9.500   1.1091   0.04618   0.04076  -0.0491   0.0036   1.0000
   9.750   1.1013   0.04947   0.04439  -0.0453   0.0037   1.0000
  10.000   1.0905   0.05285   0.04806  -0.0417   0.0037   1.0000
  10.250   1.0768   0.05648   0.05197  -0.0387   0.0037   1.0000
  10.500   1.0614   0.06036   0.05611  -0.0364   0.0037   1.0000
  10.750   1.0447   0.06458   0.06056  -0.0351   0.0038   1.0000
  11.000   1.0257   0.06946   0.06565  -0.0346   0.0038   1.0000
  11.250   1.0064   0.07482   0.07120  -0.0354   0.0038   1.0000
  11.500   0.9866   0.08090   0.07746  -0.0374   0.0038   1.0000
  11.750   0.9662   0.08802   0.08474  -0.0410   0.0038   1.0000
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