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