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=9


Details Polar file
Airfoil: EPPLER 863 STRUT AIRFOIL (e863-il)
Reynolds number: 1,000,000
Max Cl/Cd: 64.15 at α=10°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e863-il-1000000.txt
Download as CSV file: xf-e863-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -1.2469   0.09286   0.08923   0.0011   1.0000   0.2193
 -19.500  -1.2449   0.09025   0.08660   0.0005   1.0000   0.2229
 -19.000  -1.2472   0.08442   0.08077  -0.0006   1.0000   0.2302
 -18.750  -1.2476   0.08162   0.07797  -0.0011   1.0000   0.2342
 -18.500  -1.2453   0.07906   0.07537  -0.0016   1.0000   0.2375
 -18.250  -1.2586   0.07649   0.07243   0.0002   0.8381   0.2414
 -18.000  -1.2613   0.07373   0.06947   0.0001   0.7806   0.2455
 -17.750  -1.2613   0.07107   0.06665  -0.0002   0.7469   0.2493
 -17.500  -1.2648   0.06807   0.06352  -0.0004   0.7239   0.2529
 -17.250  -1.2694   0.06510   0.06050  -0.0006   0.7046   0.2574
 -17.000  -1.2763   0.06182   0.05713  -0.0007   0.6877   0.2616
 -16.750  -1.2744   0.05936   0.05455  -0.0010   0.6723   0.2647
 -16.500  -1.2845   0.05598   0.05113  -0.0008   0.6588   0.2694
 -16.250  -1.2863   0.05332   0.04843  -0.0008   0.6469   0.2733
 -16.000  -1.2895   0.05046   0.04546  -0.0009   0.6349   0.2769
 -15.750  -1.2869   0.04823   0.04316  -0.0009   0.6234   0.2802
 -15.500  -1.2980   0.04490   0.03980  -0.0005   0.6148   0.2847
 -15.250  -1.2963   0.04263   0.03746  -0.0004   0.6035   0.2883
 -15.000  -1.2939   0.04037   0.03510  -0.0004   0.5951   0.2913
 -14.750  -1.2913   0.03826   0.03295  -0.0002   0.5868   0.2946
 -14.500  -1.2954   0.03568   0.03033   0.0002   0.5784   0.2984
 -14.250  -1.2931   0.03356   0.02815   0.0005   0.5713   0.3018
 -14.000  -1.2831   0.03206   0.02659   0.0005   0.5647   0.3045
 -13.750  -1.2741   0.03048   0.02491   0.0005   0.5573   0.3068
 -13.500  -1.2715   0.02864   0.02304   0.0011   0.5491   0.3106
 -13.250  -1.2649   0.02702   0.02140   0.0014   0.5451   0.3137
 -13.000  -1.2542   0.02567   0.02001   0.0016   0.5398   0.3165
 -12.750  -1.2387   0.02469   0.01895   0.0015   0.5337   0.3189
 -12.500  -1.2230   0.02370   0.01786   0.0014   0.5264   0.3208
 -12.250  -1.2124   0.02252   0.01669   0.0019   0.5224   0.3241
 -12.000  -1.2003   0.02141   0.01557   0.0023   0.5186   0.3269
 -11.750  -1.1849   0.02052   0.01465   0.0025   0.5141   0.3295
 -11.500  -1.1661   0.01986   0.01392   0.0025   0.5093   0.3319
 -11.250  -1.1470   0.01925   0.01323   0.0025   0.5038   0.3339
 -11.000  -1.1263   0.01873   0.01264   0.0025   0.5000   0.3355
 -10.750  -1.1106   0.01800   0.01193   0.0031   0.4978   0.3385
 -10.500  -1.0937   0.01737   0.01129   0.0036   0.4949   0.3410
 -10.250  -1.0746   0.01687   0.01077   0.0039   0.4918   0.3432
 -10.000  -1.0539   0.01647   0.01033   0.0041   0.4884   0.3454
  -9.750  -1.0322   0.01614   0.00995   0.0043   0.4848   0.3473
  -9.500  -1.0100   0.01586   0.00960   0.0045   0.4802   0.3491
  -9.250  -0.9875   0.01558   0.00927   0.0046   0.4778   0.3504
  -9.000  -0.9665   0.01521   0.00891   0.0051   0.4761   0.3528
  -8.750  -0.9469   0.01484   0.00855   0.0058   0.4740   0.3553
  -8.500  -0.9255   0.01457   0.00827   0.0063   0.4718   0.3573
  -8.250  -0.9032   0.01434   0.00802   0.0067   0.4695   0.3592
  -8.000  -0.8800   0.01416   0.00781   0.0070   0.4670   0.3610
  -7.750  -0.8570   0.01401   0.00761   0.0074   0.4645   0.3627
  -7.500  -0.8354   0.01390   0.00746   0.0081   0.4615   0.3643
  -7.250  -0.8160   0.01387   0.00736   0.0093   0.4582   0.3655
  -7.000  -0.7964   0.01382   0.00727   0.0105   0.4568   0.3666
  -6.750  -0.7736   0.01359   0.00708   0.0111   0.4556   0.3692
  -6.500  -0.7498   0.01344   0.00694   0.0115   0.4542   0.3713
  -6.250  -0.7245   0.01334   0.00684   0.0116   0.4525   0.3732
  -6.000  -0.6982   0.01326   0.00676   0.0116   0.4507   0.3749
  -5.750  -0.6711   0.01320   0.00668   0.0115   0.4489   0.3765
  -5.500  -0.6436   0.01315   0.00660   0.0112   0.4470   0.3781
  -5.250  -0.6158   0.01312   0.00654   0.0110   0.4451   0.3796
  -5.000  -0.5877   0.01310   0.00648   0.0107   0.4430   0.3809
  -4.750  -0.5596   0.01311   0.00645   0.0103   0.4404   0.3820
  -4.500  -0.5314   0.01317   0.00645   0.0100   0.4373   0.3827
  -4.250  -0.5034   0.01298   0.00629   0.0097   0.4364   0.3853
  -4.000  -0.4753   0.01286   0.00619   0.0093   0.4354   0.3875
  -3.750  -0.4465   0.01279   0.00614   0.0089   0.4342   0.3893
  -3.500  -0.4173   0.01274   0.00610   0.0084   0.4329   0.3908
  -3.250  -0.3878   0.01271   0.00606   0.0079   0.4315   0.3922
  -3.000  -0.3582   0.01268   0.00602   0.0073   0.4300   0.3937
  -2.750  -0.3284   0.01265   0.00599   0.0067   0.4284   0.3951
  -2.500  -0.2985   0.01264   0.00596   0.0061   0.4267   0.3965
  -2.250  -0.2686   0.01265   0.00593   0.0055   0.4249   0.3978
  -2.000  -0.2388   0.01267   0.00593   0.0049   0.4231   0.3988
  -1.750  -0.2091   0.01273   0.00595   0.0043   0.4209   0.3996
  -1.500  -0.1801   0.01276   0.00595   0.0038   0.4183   0.4010
  -1.250  -0.1507   0.01265   0.00587   0.0033   0.4174   0.4033
  -1.000  -0.1210   0.01257   0.00582   0.0027   0.4165   0.4053
  -0.750  -0.0909   0.01253   0.00580   0.0020   0.4154   0.4071
  -0.500  -0.0607   0.01251   0.00579   0.0014   0.4142   0.4087
  -0.250  -0.0303   0.01250   0.00579   0.0007   0.4129   0.4101
   0.000   0.0000   0.01250   0.00579   0.0000   0.4115   0.4115
   0.250   0.0303   0.01250   0.00579  -0.0007   0.4101   0.4129
   0.500   0.0607   0.01251   0.00579  -0.0014   0.4086   0.4142
   0.750   0.0909   0.01253   0.00580  -0.0020   0.4071   0.4154
   1.000   0.1209   0.01257   0.00582  -0.0027   0.4053   0.4165
   1.250   0.1507   0.01265   0.00587  -0.0033   0.4033   0.4174
   1.500   0.1801   0.01276   0.00595  -0.0038   0.4010   0.4183
   1.750   0.2091   0.01273   0.00594  -0.0043   0.3996   0.4209
   2.000   0.2388   0.01267   0.00593  -0.0049   0.3988   0.4231
   2.250   0.2686   0.01265   0.00593  -0.0055   0.3978   0.4249
   2.500   0.2985   0.01264   0.00596  -0.0061   0.3965   0.4267
   2.750   0.3284   0.01265   0.00599  -0.0067   0.3951   0.4284
   3.000   0.3582   0.01268   0.00602  -0.0073   0.3936   0.4300
   3.250   0.3879   0.01271   0.00606  -0.0079   0.3922   0.4315
   3.500   0.4174   0.01274   0.00610  -0.0084   0.3908   0.4329
   3.750   0.4466   0.01279   0.00614  -0.0089   0.3892   0.4342
   4.000   0.4754   0.01286   0.00619  -0.0094   0.3875   0.4354
   4.250   0.5035   0.01298   0.00629  -0.0097   0.3853   0.4364
   4.500   0.5316   0.01317   0.00645  -0.0100   0.3827   0.4373
   4.750   0.5597   0.01311   0.00645  -0.0104   0.3820   0.4405
   5.000   0.5879   0.01310   0.00648  -0.0107   0.3809   0.4430
   5.250   0.6160   0.01312   0.00654  -0.0110   0.3796   0.4451
   5.500   0.6438   0.01315   0.00660  -0.0113   0.3781   0.4470
   5.750   0.6713   0.01320   0.00668  -0.0115   0.3765   0.4489
   6.000   0.6985   0.01326   0.00675  -0.0117   0.3749   0.4507
   6.250   0.7249   0.01334   0.00684  -0.0117   0.3732   0.4525
   6.500   0.7501   0.01344   0.00694  -0.0115   0.3713   0.4542
   6.750   0.7741   0.01359   0.00707  -0.0112   0.3692   0.4557
   7.000   0.7970   0.01382   0.00727  -0.0106   0.3665   0.4568
   7.250   0.8168   0.01387   0.00736  -0.0095   0.3655   0.4582
   7.500   0.8362   0.01390   0.00746  -0.0083   0.3643   0.4615
   7.750   0.8577   0.01400   0.00761  -0.0076   0.3627   0.4645
   8.000   0.8807   0.01415   0.00780  -0.0071   0.3610   0.4670
   8.250   0.9040   0.01433   0.00802  -0.0068   0.3592   0.4695
   8.500   0.9263   0.01456   0.00826  -0.0064   0.3573   0.4718
   8.750   0.9478   0.01484   0.00854  -0.0059   0.3552   0.4740
   9.000   0.9674   0.01520   0.00890  -0.0052   0.3528   0.4761
   9.250   0.9885   0.01557   0.00926  -0.0048   0.3504   0.4778
   9.500   1.0111   0.01585   0.00959  -0.0046   0.3491   0.4803
   9.750   1.0334   0.01612   0.00993  -0.0045   0.3473   0.4848
  10.000   1.0552   0.01645   0.01032  -0.0044   0.3454   0.4885
  10.250   1.0759   0.01685   0.01076  -0.0041   0.3432   0.4918
  10.500   1.0951   0.01735   0.01127  -0.0038   0.3410   0.4950
  10.750   1.1120   0.01798   0.01191  -0.0033   0.3384   0.4978
  11.000   1.1280   0.01870   0.01262  -0.0027   0.3355   0.5001
  11.250   1.1487   0.01922   0.01320  -0.0028   0.3339   0.5039
  11.500   1.1680   0.01983   0.01389  -0.0028   0.3319   0.5094
  11.750   1.1868   0.02049   0.01461  -0.0028   0.3295   0.5142
  12.000   1.2024   0.02137   0.01552  -0.0026   0.3269   0.5187
  12.250   1.2147   0.02247   0.01664  -0.0023   0.3241   0.5225
  12.500   1.2253   0.02365   0.01781  -0.0018   0.3208   0.5266
  12.750   1.2412   0.02463   0.01889  -0.0019   0.3189   0.5338
  13.000   1.2569   0.02561   0.01995  -0.0019   0.3165   0.5399
  13.250   1.2677   0.02695   0.02133  -0.0018   0.3137   0.5452
  13.500   1.2748   0.02854   0.02294  -0.0015   0.3107   0.5494
  13.750   1.2771   0.03041   0.02483  -0.0009   0.3068   0.5575
  14.000   1.2865   0.03197   0.02650  -0.0009   0.3046   0.5649
  14.250   1.2965   0.03347   0.02806  -0.0009   0.3018   0.5715
  14.500   1.2990   0.03558   0.03023  -0.0007   0.2985   0.5787
  14.750   1.2951   0.03815   0.03283  -0.0002   0.2946   0.5871
  15.000   1.2976   0.04027   0.03500  -0.0001   0.2913   0.5954
  15.250   1.3005   0.04250   0.03732  -0.0001   0.2883   0.6041
  15.500   1.3020   0.04479   0.03969   0.0000   0.2847   0.6152
  15.750   1.2913   0.04810   0.04303   0.0004   0.2803   0.6238
  16.000   1.2938   0.05034   0.04534   0.0003   0.2770   0.6356
  16.250   1.2907   0.05320   0.04830   0.0003   0.2734   0.6475
  16.500   1.2890   0.05586   0.05101   0.0002   0.2694   0.6596
  16.750   1.2789   0.05925   0.05443   0.0004   0.2647   0.6732
  17.000   1.2809   0.06169   0.05700   0.0001   0.2617   0.6887
  17.250   1.2742   0.06498   0.06037   0.0000   0.2574   0.7055
  17.500   1.2694   0.06797   0.06342  -0.0002   0.2529   0.7250
  17.750   1.2664   0.07092   0.06651  -0.0004   0.2494   0.7487
  18.000   1.2660   0.07362   0.06937  -0.0007   0.2456   0.7829
  18.250   1.2634   0.07636   0.07232  -0.0008   0.2414   0.8431
  18.500   1.2499   0.07900   0.07530   0.0010   0.2374   1.0000
  18.750   1.2523   0.08154   0.07789   0.0005   0.2341   1.0000
  19.000   1.2524   0.08429   0.08063   0.0000   0.2303   1.0000
<< Back to EPPLER 863 STRUT AIRFOIL (e863-il)

Polar data table (+)

Polar graphs


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