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EPPLER 863 STRUT AIRFOIL (e863-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 863 STRUT AIRFOIL (e863-il)
Reynolds number: 200,000
Max Cl/Cd: 24 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e863-il-200000-n5.txt
Download as CSV file: xf-e863-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 863 STRUT 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
  ------ -------- --------- --------- -------- -------- --------
 -18.250  -0.6898   0.13864   0.13245  -0.0031   0.7533   0.2125
 -17.250  -0.6634   0.12923   0.12254  -0.0068   0.6727   0.2259
 -16.750  -0.6169   0.12891   0.12205  -0.0081   0.6417   0.2270
 -16.500  -0.5952   0.12852   0.12157  -0.0087   0.6293   0.2277
 -16.250  -0.5741   0.12803   0.12103  -0.0095   0.6189   0.2286
 -14.250  -0.5576   0.10363   0.09608  -0.0173   0.5697   0.2653
 -14.000  -0.5323   0.10358   0.09600  -0.0179   0.5629   0.2658
 -13.750  -0.5083   0.10337   0.09575  -0.0185   0.5567   0.2664
 -13.500  -0.4854   0.10304   0.09536  -0.0191   0.5513   0.2672
 -13.250  -0.4631   0.10261   0.09490  -0.0197   0.5467   0.2681
 -13.000  -0.4422   0.10200   0.09428  -0.0204   0.5423   0.2694
 -12.750  -0.4267   0.10072   0.09297  -0.0210   0.5381   0.2719
 -12.250  -0.4268   0.09433   0.08647  -0.0224   0.5319   0.2819
 -10.250  -0.5233   0.06060   0.05228  -0.0250   0.5142   0.3352
 -10.000  -0.4833   0.06193   0.05361  -0.0256   0.5103   0.3346
  -9.750  -0.4444   0.06320   0.05486  -0.0262   0.5067   0.3340
  -9.500  -0.4058   0.06448   0.05611  -0.0269   0.5035   0.3332
  -9.250  -0.7319   0.03460   0.02567  -0.0185   0.5107   0.3664
  -9.000  -0.6986   0.03485   0.02594  -0.0193   0.5074   0.3676
  -8.750  -0.6716   0.03479   0.02586  -0.0197   0.5044   0.3690
  -8.500  -0.6491   0.03449   0.02553  -0.0200   0.5017   0.3706
  -8.250  -0.6346   0.03369   0.02471  -0.0197   0.4995   0.3728
  -8.000  -0.6343   0.03213   0.02310  -0.0185   0.4975   0.3757
  -7.750  -0.6487   0.03005   0.02088  -0.0159   0.4956   0.3791
  -7.500  -0.6717   0.02803   0.01865  -0.0114   0.4939   0.3824
  -7.250  -0.6472   0.02779   0.01843  -0.0115   0.4911   0.3840
  -7.000  -0.6223   0.02763   0.01828  -0.0117   0.4883   0.3855
  -6.750  -0.6009   0.02738   0.01802  -0.0113   0.4857   0.3870
  -6.500  -0.5825   0.02708   0.01768  -0.0106   0.4834   0.3886
  -6.250  -0.5685   0.02680   0.01734  -0.0091   0.4814   0.3905
  -6.000  -0.5595   0.02652   0.01698  -0.0068   0.4795   0.3926
  -5.750  -0.5508   0.02620   0.01659  -0.0044   0.4778   0.3948
  -5.500  -0.5394   0.02582   0.01614  -0.0025   0.4760   0.3970
  -5.250  -0.5274   0.02542   0.01565  -0.0006   0.4742   0.3989
  -5.000  -0.5072   0.02516   0.01535   0.0001   0.4721   0.4005
  -4.750  -0.4795   0.02506   0.01530  -0.0003   0.4697   0.4020
  -4.500  -0.4537   0.02498   0.01524  -0.0004   0.4674   0.4035
  -4.250  -0.4287   0.02490   0.01516  -0.0003   0.4652   0.4051
  -4.000  -0.4042   0.02480   0.01504  -0.0002   0.4632   0.4068
  -3.750  -0.3803   0.02469   0.01488   0.0001   0.4614   0.4085
  -3.500  -0.3566   0.02457   0.01470   0.0003   0.4597   0.4102
  -3.250  -0.3332   0.02446   0.01452   0.0006   0.4580   0.4121
  -3.000  -0.3104   0.02434   0.01435   0.0009   0.4564   0.4141
  -2.750  -0.2882   0.02419   0.01416   0.0014   0.4546   0.4162
  -2.500  -0.2661   0.02405   0.01396   0.0018   0.4526   0.4179
  -2.250  -0.2382   0.02395   0.01392   0.0014   0.4504   0.4194
  -2.000  -0.2107   0.02389   0.01390   0.0011   0.4484   0.4208
  -1.750  -0.1838   0.02385   0.01388   0.0009   0.4465   0.4222
  -1.500  -0.1571   0.02382   0.01386   0.0007   0.4448   0.4238
  -1.250  -0.1304   0.02380   0.01384   0.0005   0.4431   0.4255
  -1.000  -0.1039   0.02377   0.01379   0.0004   0.4415   0.4274
  -0.750  -0.0774   0.02374   0.01371   0.0002   0.4398   0.4293
  -0.500  -0.0508   0.02373   0.01363   0.0000   0.4381   0.4312
  -0.250  -0.0249   0.02373   0.01359  -0.0001   0.4364   0.4330
   0.000   0.0000   0.02372   0.01359   0.0000   0.4348   0.4348
   0.250   0.0249   0.02373   0.01359   0.0001   0.4330   0.4364
   0.500   0.0508   0.02373   0.01363   0.0000   0.4312   0.4381
   0.750   0.0774   0.02374   0.01371  -0.0002   0.4293   0.4398
   1.000   0.1039   0.02377   0.01379  -0.0004   0.4274   0.4415
   1.250   0.1304   0.02380   0.01384  -0.0005   0.4255   0.4431
   1.500   0.1571   0.02382   0.01386  -0.0007   0.4238   0.4448
   1.750   0.1838   0.02385   0.01388  -0.0009   0.4222   0.4465
   2.000   0.2107   0.02388   0.01390  -0.0011   0.4208   0.4484
   2.250   0.2382   0.02394   0.01391  -0.0014   0.4194   0.4504
   2.500   0.2661   0.02405   0.01396  -0.0018   0.4179   0.4526
   2.750   0.2882   0.02419   0.01416  -0.0014   0.4162   0.4546
   3.000   0.3105   0.02434   0.01435  -0.0009   0.4141   0.4564
   3.250   0.3333   0.02446   0.01452  -0.0006   0.4121   0.4580
   3.500   0.3567   0.02457   0.01470  -0.0003   0.4102   0.4597
   3.750   0.3804   0.02469   0.01488  -0.0001   0.4084   0.4614
   4.000   0.4044   0.02480   0.01504   0.0001   0.4068   0.4632
   4.250   0.4289   0.02490   0.01516   0.0003   0.4051   0.4652
   4.500   0.4539   0.02498   0.01524   0.0003   0.4035   0.4674
   4.750   0.4797   0.02506   0.01530   0.0003   0.4020   0.4697
   5.000   0.5075   0.02516   0.01535  -0.0001   0.4005   0.4721
   5.250   0.5276   0.02542   0.01565   0.0006   0.3989   0.4742
   5.500   0.5397   0.02581   0.01614   0.0024   0.3969   0.4760
   5.750   0.5512   0.02620   0.01659   0.0043   0.3948   0.4778
   6.000   0.5602   0.02652   0.01698   0.0067   0.3926   0.4795
   6.250   0.5693   0.02679   0.01733   0.0090   0.3905   0.4814
   6.500   0.5833   0.02708   0.01767   0.0105   0.3886   0.4834
   6.750   0.6017   0.02737   0.01801   0.0112   0.3870   0.4857
   7.000   0.6231   0.02762   0.01827   0.0115   0.3855   0.4883
   7.250   0.6480   0.02779   0.01842   0.0114   0.3840   0.4911
   7.500   0.6726   0.02802   0.01864   0.0113   0.3824   0.4939
   7.750   0.6500   0.03002   0.02085   0.0157   0.3791   0.4957
   8.000   0.6360   0.03209   0.02305   0.0183   0.3757   0.4975
   8.250   0.6364   0.03364   0.02466   0.0195   0.3728   0.4995
   8.500   0.6510   0.03443   0.02547   0.0197   0.3707   0.5018
   8.750   0.6734   0.03473   0.02581   0.0195   0.3690   0.5045
   9.000   0.7003   0.03481   0.02590   0.0191   0.3676   0.5074
   9.250   0.7335   0.03456   0.02563   0.0183   0.3665   0.5108
   9.500   0.5800   0.04802   0.03951   0.0238   0.3528   0.5087
   9.750   0.6123   0.04756   0.03905   0.0233   0.3520   0.5122
  10.000   0.6460   0.04702   0.03850   0.0227   0.3513   0.5161
  11.500   0.4794   0.07936   0.07126   0.0236   0.3060   0.5259
  12.500   0.4519   0.09471   0.08689   0.0214   0.2810   0.5363
  12.750   0.4413   0.09922   0.09146   0.0207   0.2743   0.5389
  13.000   0.4812   0.09748   0.08971   0.0202   0.2767   0.5445
  13.250   0.5164   0.09637   0.08859   0.0196   0.2777   0.5497
  13.500   0.5510   0.09531   0.08760   0.0191   0.2784   0.5556
  15.500   0.5616   0.11997   0.11275   0.0121   0.2406   0.5973
  15.750   0.5839   0.12036   0.11320   0.0115   0.2399   0.6056
  16.000   0.6071   0.12059   0.11350   0.0108   0.2393   0.6158
  16.250   0.6316   0.12069   0.11363   0.0101   0.2388   0.6265
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