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EPPLER 1233 AIRFOIL (e1233-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 1233 AIRFOIL (e1233-il)
Reynolds number: 100,000
Max Cl/Cd: 34.05 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e1233-il-100000.txt
Download as CSV file: xf-e1233-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 1233 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3749   0.10606   0.10224  -0.0476   0.9911   0.1424
  -9.000  -0.3202   0.10187   0.09802  -0.0456   0.9877   0.1448
  -8.750  -0.5012   0.06679   0.06213  -0.0712   0.9623   0.0711
  -8.500  -0.4949   0.06080   0.05584  -0.0741   0.9499   0.0676
  -8.250  -0.5149   0.05160   0.04558  -0.0754   0.9352   0.0627
  -8.000  -0.5038   0.04699   0.04023  -0.0759   0.9224   0.0618
  -7.750  -0.4826   0.04333   0.03615  -0.0766   0.9112   0.0622
  -7.500  -0.4401   0.04089   0.03376  -0.0801   0.9053   0.0648
  -7.250  -0.4156   0.03862   0.03113  -0.0804   0.8930   0.0678
  -7.000  -0.3737   0.03543   0.02747  -0.0834   0.8881   0.0714
  -6.750  -0.3452   0.03375   0.02572  -0.0836   0.8759   0.0746
  -6.500  -0.2977   0.03136   0.02310  -0.0869   0.8716   0.0818
  -6.250  -0.2671   0.02991   0.02143  -0.0871   0.8597   0.0897
  -6.000  -0.2163   0.02781   0.01944  -0.0910   0.8550   0.1035
  -5.750  -0.1801   0.02641   0.01813  -0.0924   0.8444   0.1201
  -5.500  -0.1299   0.02470   0.01648  -0.0964   0.8374   0.1470
  -5.250  -0.0941   0.02361   0.01544  -0.0978   0.8256   0.1732
  -5.000  -0.0457   0.02215   0.01414  -0.1015   0.8171   0.2090
  -4.750  -0.0192   0.02123   0.01345  -0.1013   0.8027   0.2438
  -4.500   0.0082   0.02005   0.01271  -0.1014   0.7899   0.3075
  -4.250   0.0299   0.01873   0.01264  -0.0999   0.7788   0.5034
  -4.000   0.0497   0.01962   0.01372  -0.0960   0.7641   0.6103
  -3.750   0.0770   0.02066   0.01460  -0.0937   0.7509   0.6534
  -3.500   0.1139   0.02167   0.01534  -0.0928   0.7399   0.6824
  -3.250   0.1320   0.02254   0.01610  -0.0892   0.7259   0.7017
  -3.000   0.1570   0.02331   0.01671  -0.0867   0.7138   0.7201
  -2.750   0.1876   0.02395   0.01712  -0.0853   0.7030   0.7380
  -2.500   0.2063   0.02455   0.01763  -0.0820   0.6906   0.7529
  -2.250   0.2431   0.02516   0.01802  -0.0813   0.6807   0.7673
  -2.000   0.2646   0.02554   0.01831  -0.0787   0.6690   0.7823
  -1.750   0.2967   0.02593   0.01853  -0.0778   0.6588   0.7990
  -1.500   0.3287   0.02620   0.01865  -0.0772   0.6484   0.8158
  -1.250   0.3572   0.02638   0.01869  -0.0765   0.6388   0.8315
  -1.000   0.3845   0.02641   0.01857  -0.0760   0.6293   0.8450
  -0.750   0.4309   0.02642   0.01843  -0.0789   0.6193   0.8539
  -0.500   0.4429   0.02632   0.01824  -0.0763   0.6111   0.8651
  -0.250   0.4914   0.02628   0.01803  -0.0802   0.6023   0.8719
   0.000   0.4931   0.02624   0.01797  -0.0758   0.5946   0.8818
   0.250   0.5520   0.02612   0.01757  -0.0818   0.5866   0.8870
   0.500   0.5364   0.02617   0.01774  -0.0743   0.5795   0.8971
   0.750   0.5897   0.02607   0.01745  -0.0794   0.5714   0.9013
   1.000   0.6130   0.02615   0.01746  -0.0791   0.5647   0.9078
   1.250   0.6196   0.02620   0.01754  -0.0758   0.5580   0.9147
   1.500   0.6652   0.02612   0.01727  -0.0795   0.5513   0.9187
   1.750   0.6714   0.02631   0.01749  -0.0762   0.5452   0.9257
   2.000   0.6919   0.02640   0.01759  -0.0755   0.5384   0.9308
   2.250   0.7322   0.02642   0.01745  -0.0784   0.5328   0.9349
   2.500   0.7393   0.02669   0.01775  -0.0752   0.5277   0.9417
   2.750   0.7634   0.02695   0.01806  -0.0754   0.5209   0.9461
   3.000   0.7986   0.02703   0.01804  -0.0773   0.5155   0.9505
   3.250   0.8194   0.02727   0.01821  -0.0767   0.5107   0.9563
   3.500   0.8404   0.02775   0.01882  -0.0766   0.5040   0.9610
   3.750   0.8684   0.02800   0.01904  -0.0773   0.4989   0.9659
   4.000   0.9066   0.02816   0.01907  -0.0798   0.4948   0.9701
   4.250   0.9246   0.02888   0.01994  -0.0794   0.4887   0.9757
   4.500   0.9424   0.02937   0.02049  -0.0785   0.4832   0.9814
   4.750   0.9847   0.02956   0.02060  -0.0819   0.4785   0.9849
   5.000   1.0225   0.03003   0.02101  -0.0847   0.4745   0.9894
   5.250   1.0300   0.03119   0.02241  -0.0828   0.4688   0.9969
   5.500   1.0438   0.03182   0.02310  -0.0814   0.4642   1.0000
   5.750   1.0557   0.03210   0.02335  -0.0793   0.4607   1.0000
   6.000   1.0836   0.03230   0.02342  -0.0797   0.4575   1.0000
   6.250   1.0315   0.03365   0.02504  -0.0675   0.4541   1.0000
   6.500   0.9671   0.03523   0.02684  -0.0541   0.4504   1.0000
   6.750   0.9602   0.03661   0.02829  -0.0504   0.4461   1.0000
   7.000   0.9975   0.03687   0.02850  -0.0524   0.4428   1.0000
   7.250   1.0513   0.03668   0.02819  -0.0566   0.4398   1.0000
   7.500   0.7774   0.05636   0.04855  -0.0350   0.4228   1.0000
   7.750   0.8476   0.05267   0.04479  -0.0364   0.4229   1.0000
   8.000   0.9332   0.04860   0.04063  -0.0397   0.4229   1.0000
   8.250   1.0167   0.04584   0.03776  -0.0445   0.4220   1.0000
   9.500   0.5187   0.11750   0.11024  -0.0488   0.4290   1.0000
   9.750   0.5414   0.11970   0.11244  -0.0496   0.4250   1.0000
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