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
|
Polar data table (+)
Polar graphs
<< Back to EPPLER 863 STRUT AIRFOIL (e863-il)