Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

EPPLER 863 STRUT AIRFOIL (e863-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 863 STRUT AIRFOIL (e863-il)
Reynolds number: 1,000,000
Max Cl/Cd: 62.01 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e863-il-1000000-n5.txt
Download as CSV file: xf-e863-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.750  -1.1478   0.09362   0.08854   0.0003   0.6124   0.2037
 -18.500  -1.1534   0.09017   0.08504  -0.0003   0.6034   0.2078
 -18.250  -1.1488   0.08783   0.08265  -0.0008   0.5954   0.2110
 -18.000  -1.1434   0.08558   0.08035  -0.0014   0.5873   0.2140
 -17.750  -1.1533   0.08180   0.07654  -0.0017   0.5804   0.2184
 -17.500  -1.1522   0.07917   0.07387  -0.0022   0.5730   0.2222
 -17.250  -1.1452   0.07709   0.07175  -0.0026   0.5669   0.2251
 -17.000  -1.1570   0.07322   0.06785  -0.0028   0.5618   0.2295
 -16.750  -1.1583   0.07041   0.06501  -0.0031   0.5553   0.2336
 -16.500  -1.1550   0.06806   0.06260  -0.0034   0.5484   0.2370
 -16.250  -1.1623   0.06471   0.05922  -0.0035   0.5443   0.2408
 -16.000  -1.1688   0.06151   0.05600  -0.0035   0.5395   0.2452
 -15.750  -1.1728   0.05854   0.05296  -0.0035   0.5341   0.2492
 -15.500  -1.1689   0.05634   0.05070  -0.0037   0.5277   0.2522
 -15.250  -1.1848   0.05239   0.04672  -0.0033   0.5238   0.2569
 -15.000  -1.1877   0.04963   0.04393  -0.0032   0.5206   0.2610
 -14.750  -1.1863   0.04725   0.04150  -0.0032   0.5168   0.2642
 -14.500  -1.1955   0.04404   0.03825  -0.0028   0.5133   0.2680
 -14.250  -1.1999   0.04128   0.03545  -0.0025   0.5095   0.2719
 -14.000  -1.2005   0.03884   0.03296  -0.0022   0.5052   0.2755
 -13.750  -1.1927   0.03713   0.03118  -0.0022   0.5008   0.2782
 -13.500  -1.1985   0.03438   0.02841  -0.0016   0.4987   0.2818
 -13.250  -1.2000   0.03200   0.02600  -0.0011   0.4961   0.2854
 -13.000  -1.1945   0.03021   0.02417  -0.0008   0.4930   0.2886
 -12.750  -1.1837   0.02883   0.02274  -0.0007   0.4894   0.2913
 -12.500  -1.1769   0.02717   0.02102  -0.0004   0.4857   0.2940
 -12.250  -1.1718   0.02544   0.01926   0.0001   0.4819   0.2973
 -12.000  -1.1614   0.02411   0.01789   0.0004   0.4782   0.3004
 -11.750  -1.1481   0.02298   0.01673   0.0005   0.4760   0.3033
 -11.500  -1.1311   0.02211   0.01582   0.0005   0.4734   0.3056
 -11.250  -1.1167   0.02110   0.01478   0.0007   0.4708   0.3080
 -11.000  -1.1049   0.01999   0.01365   0.0012   0.4682   0.3110
 -10.750  -1.0894   0.01915   0.01278   0.0015   0.4654   0.3138
 -10.500  -1.0712   0.01849   0.01207   0.0017   0.4624   0.3164
 -10.250  -1.0517   0.01792   0.01146   0.0019   0.4593   0.3187
 -10.000  -1.0303   0.01746   0.01096   0.0019   0.4569   0.3206
  -9.750  -1.0134   0.01682   0.01031   0.0024   0.4555   0.3231
  -9.500  -0.9957   0.01626   0.00975   0.0030   0.4539   0.3257
  -9.250  -0.9762   0.01580   0.00927   0.0034   0.4519   0.3282
  -9.000  -0.9552   0.01543   0.00888   0.0037   0.4496   0.3306
  -8.750  -0.9330   0.01512   0.00853   0.0040   0.4471   0.3327
  -8.500  -0.9098   0.01487   0.00824   0.0041   0.4446   0.3345
  -8.250  -0.8871   0.01461   0.00794   0.0044   0.4423   0.3362
  -8.000  -0.8671   0.01428   0.00760   0.0051   0.4399   0.3386
  -7.750  -0.8461   0.01401   0.00731   0.0057   0.4375   0.3407
  -7.500  -0.8240   0.01377   0.00707   0.0062   0.4364   0.3429
  -7.250  -0.8020   0.01357   0.00686   0.0068   0.4353   0.3450
  -7.000  -0.7808   0.01343   0.00670   0.0076   0.4340   0.3469
  -6.750  -0.7606   0.01333   0.00657   0.0087   0.4326   0.3485
  -6.500  -0.7392   0.01325   0.00647   0.0096   0.4311   0.3500
  -6.250  -0.7151   0.01315   0.00635   0.0100   0.4292   0.3515
  -6.000  -0.6916   0.01302   0.00620   0.0104   0.4273   0.3536
  -5.750  -0.6666   0.01291   0.00609   0.0106   0.4253   0.3555
  -5.500  -0.6407   0.01282   0.00599   0.0106   0.4235   0.3574
  -5.250  -0.6139   0.01275   0.00590   0.0105   0.4216   0.3594
  -5.000  -0.5865   0.01270   0.00583   0.0103   0.4196   0.3612
  -4.750  -0.5586   0.01265   0.00576   0.0101   0.4178   0.3627
  -4.500  -0.5299   0.01259   0.00569   0.0097   0.4170   0.3641
  -4.250  -0.5009   0.01254   0.00562   0.0092   0.4159   0.3654
  -4.000  -0.4716   0.01250   0.00556   0.0087   0.4146   0.3665
  -3.750  -0.4438   0.01240   0.00548   0.0084   0.4131   0.3685
  -3.500  -0.4155   0.01233   0.00541   0.0081   0.4117   0.3703
  -3.250  -0.3867   0.01228   0.00535   0.0076   0.4103   0.3719
  -3.000  -0.3576   0.01223   0.00530   0.0072   0.4088   0.3735
  -2.750  -0.3283   0.01220   0.00526   0.0067   0.4072   0.3752
  -2.500  -0.2989   0.01218   0.00523   0.0061   0.4055   0.3769
  -2.250  -0.2693   0.01217   0.00520   0.0055   0.4036   0.3785
  -2.000  -0.2397   0.01217   0.00518   0.0050   0.4015   0.3798
  -1.750  -0.2099   0.01218   0.00517   0.0044   0.3998   0.3809
  -1.500  -0.1796   0.01216   0.00514   0.0037   0.3991   0.3818
  -1.250  -0.1491   0.01215   0.00513   0.0030   0.3982   0.3827
  -1.000  -0.1196   0.01209   0.00509   0.0025   0.3971   0.3847
  -0.750  -0.0899   0.01205   0.00506   0.0019   0.3957   0.3866
  -0.500  -0.0600   0.01203   0.00505   0.0013   0.3942   0.3883
  -0.250  -0.0300   0.01201   0.00504   0.0006   0.3927   0.3898
   0.000   0.0000   0.01201   0.00504   0.0000   0.3912   0.3912
   0.250   0.0300   0.01201   0.00504  -0.0006   0.3898   0.3927
   0.500   0.0600   0.01203   0.00505  -0.0013   0.3883   0.3942
   0.750   0.0899   0.01205   0.00506  -0.0019   0.3866   0.3957
   1.000   0.1196   0.01209   0.00509  -0.0025   0.3847   0.3970
   1.250   0.1491   0.01215   0.00513  -0.0030   0.3827   0.3982
   1.500   0.1796   0.01216   0.00514  -0.0037   0.3818   0.3991
   1.750   0.2099   0.01218   0.00517  -0.0044   0.3809   0.3998
   2.000   0.2397   0.01217   0.00518  -0.0050   0.3797   0.4015
   2.250   0.2693   0.01217   0.00520  -0.0055   0.3785   0.4036
   2.500   0.2989   0.01218   0.00523  -0.0061   0.3769   0.4055
   2.750   0.3284   0.01220   0.00526  -0.0067   0.3753   0.4072
   3.000   0.3577   0.01223   0.00530  -0.0072   0.3735   0.4088
   3.250   0.3868   0.01227   0.00535  -0.0077   0.3719   0.4103
   3.500   0.4155   0.01233   0.00541  -0.0081   0.3703   0.4117
   3.750   0.4439   0.01240   0.00548  -0.0084   0.3685   0.4131
   4.000   0.4717   0.01250   0.00556  -0.0087   0.3665   0.4146
   4.250   0.5010   0.01254   0.00562  -0.0092   0.3654   0.4159
   4.500   0.5301   0.01259   0.00569  -0.0097   0.3641   0.4170
   4.750   0.5587   0.01265   0.00576  -0.0101   0.3627   0.4178
   5.000   0.5867   0.01270   0.00583  -0.0104   0.3612   0.4196
   5.250   0.6141   0.01275   0.00590  -0.0106   0.3594   0.4216
   5.500   0.6409   0.01282   0.00599  -0.0107   0.3574   0.4235
   5.750   0.6669   0.01291   0.00609  -0.0107   0.3555   0.4253
   6.000   0.6919   0.01301   0.00620  -0.0105   0.3536   0.4273
   6.250   0.7155   0.01315   0.00634  -0.0100   0.3514   0.4292
   6.500   0.7398   0.01325   0.00647  -0.0097   0.3499   0.4311
   6.750   0.7614   0.01333   0.00657  -0.0088   0.3485   0.4326
   7.000   0.7816   0.01343   0.00670  -0.0078   0.3469   0.4340
   7.250   0.8027   0.01357   0.00686  -0.0069   0.3450   0.4353
   7.500   0.8247   0.01377   0.00706  -0.0063   0.3429   0.4364
   7.750   0.8469   0.01400   0.00731  -0.0058   0.3407   0.4375
   8.000   0.8679   0.01428   0.00759  -0.0052   0.3386   0.4399
   8.250   0.8879   0.01460   0.00793  -0.0045   0.3362   0.4423
   8.500   0.9107   0.01486   0.00823  -0.0043   0.3345   0.4446
   8.750   0.9340   0.01511   0.00852  -0.0041   0.3327   0.4471
   9.000   0.9562   0.01542   0.00887  -0.0039   0.3306   0.4496
   9.250   0.9773   0.01579   0.00926  -0.0036   0.3282   0.4519
   9.500   0.9969   0.01625   0.00973  -0.0032   0.3257   0.4539
   9.750   1.0147   0.01680   0.01029  -0.0026   0.3231   0.4555
  10.000   1.0317   0.01744   0.01094  -0.0021   0.3207   0.4569
  10.250   1.0532   0.01789   0.01143  -0.0021   0.3187   0.4593
  10.500   1.0728   0.01846   0.01205  -0.0020   0.3164   0.4625
  10.750   1.0910   0.01912   0.01275  -0.0018   0.3138   0.4654
  11.000   1.1065   0.01997   0.01362  -0.0015   0.3110   0.4682
  11.250   1.1187   0.02106   0.01473  -0.0010   0.3080   0.4709
  11.500   1.1333   0.02206   0.01576  -0.0008   0.3056   0.4735
  11.750   1.1503   0.02293   0.01668  -0.0008   0.3033   0.4761
  12.000   1.1639   0.02405   0.01783  -0.0007   0.3004   0.4783
  12.250   1.1745   0.02536   0.01918  -0.0004   0.2973   0.4820
  12.500   1.1795   0.02711   0.02096   0.0001   0.2940   0.4858
  12.750   1.1866   0.02876   0.02266   0.0003   0.2913   0.4895
  13.000   1.1977   0.03011   0.02407   0.0004   0.2886   0.4931
  13.250   1.2031   0.03192   0.02592   0.0007   0.2853   0.4962
  13.500   1.2020   0.03427   0.02830   0.0012   0.2819   0.4988
  13.750   1.1964   0.03701   0.03106   0.0018   0.2782   0.5009
  14.000   1.2041   0.03873   0.03285   0.0018   0.2755   0.5054
  14.250   1.2038   0.04115   0.03532   0.0020   0.2719   0.5096
  14.500   1.1998   0.04387   0.03808   0.0023   0.2680   0.5136
  14.750   1.1902   0.04715   0.04139   0.0027   0.2642   0.5170
  15.000   1.1922   0.04947   0.04377   0.0027   0.2610   0.5208
  15.250   1.1888   0.05228   0.04661   0.0028   0.2569   0.5240
  15.500   1.1732   0.05621   0.05057   0.0032   0.2523   0.5280
  15.750   1.1771   0.05842   0.05284   0.0030   0.2493   0.5345
  16.000   1.1734   0.06137   0.05585   0.0029   0.2453   0.5399
  16.250   1.1668   0.06459   0.05909   0.0029   0.2409   0.5446
  16.500   1.1597   0.06793   0.06247   0.0028   0.2370   0.5486
  16.750   1.1627   0.07032   0.06491   0.0025   0.2336   0.5556
  17.000   1.1618   0.07309   0.06772   0.0022   0.2295   0.5622
  17.250   1.1497   0.07700   0.07165   0.0020   0.2251   0.5673
  17.500   1.1566   0.07909   0.07378   0.0016   0.2221   0.5733
  17.750   1.1583   0.08167   0.07641   0.0011   0.2184   0.5810
  18.000   1.1477   0.08552   0.08029   0.0008   0.2139   0.5878
  18.250   1.1533   0.08776   0.08258   0.0002   0.2110   0.5959
  18.500   1.1580   0.09010   0.08497  -0.0003   0.2077   0.6040
  18.750   1.1521   0.09358   0.08850  -0.0009   0.2036   0.6130
<< Back to EPPLER 863 STRUT AIRFOIL (e863-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER 863 STRUT AIRFOIL (e863-il)