E174 (Dicke 8.92%) (e174-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E174 (Dicke 8.92%) (e174-il) Reynolds number: 1,000,000 Max Cl/Cd: 141.87 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e174-il-1000000.txt Download as CSV file: xf-e174-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: E174 (Dicke 8.92%)
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3439 0.08714 0.08559 -0.0317 1.0000 0.0088
-8.250 -0.3504 0.08233 0.08082 -0.0332 1.0000 0.0091
-8.000 -0.3492 0.07939 0.07791 -0.0340 1.0000 0.0091
-7.750 -0.3452 0.07628 0.07482 -0.0358 0.9871 0.0092
-7.500 -0.3112 0.07044 0.06894 -0.0475 0.9591 0.0094
-7.250 -0.2851 0.06556 0.06392 -0.0566 0.9090 0.0097
-7.000 -0.2807 0.06152 0.05968 -0.0603 0.8632 0.0097
-6.750 -0.2726 0.05735 0.05538 -0.0643 0.8343 0.0098
-6.500 -0.2612 0.05270 0.05059 -0.0687 0.8128 0.0100
-6.250 -0.2467 0.04757 0.04530 -0.0732 0.7954 0.0102
-6.000 -0.2297 0.04208 0.03962 -0.0770 0.7807 0.0105
-5.750 -0.2109 0.03624 0.03352 -0.0800 0.7680 0.0110
-5.500 -0.1866 0.02981 0.02667 -0.0814 0.7570 0.0123
-5.250 -0.1649 0.02592 0.02231 -0.0822 0.7466 0.0124
-4.500 -0.0962 0.01392 0.00885 -0.0826 0.7198 0.0110
-4.250 -0.0694 0.01253 0.00717 -0.0823 0.7113 0.0109
-4.000 -0.0422 0.01144 0.00589 -0.0821 0.7034 0.0108
-3.750 -0.0150 0.01070 0.00499 -0.0819 0.6957 0.0109
-3.500 0.0127 0.01020 0.00439 -0.0818 0.6883 0.0114
-3.250 0.0401 0.00962 0.00369 -0.0817 0.6814 0.0115
-3.000 0.0679 0.00907 0.00306 -0.0816 0.6747 0.0115
-2.750 0.0956 0.00869 0.00258 -0.0815 0.6682 0.0118
-2.500 0.1238 0.00841 0.00222 -0.0814 0.6620 0.0123
-2.250 0.1518 0.00803 0.00175 -0.0814 0.6559 0.0140
-2.000 0.1800 0.00786 0.00153 -0.0813 0.6502 0.0161
-1.750 0.2082 0.00762 0.00132 -0.0813 0.6442 0.0309
-1.500 0.2358 0.00730 0.00120 -0.0814 0.6386 0.0988
-1.250 0.2638 0.00706 0.00113 -0.0816 0.6332 0.1571
-1.000 0.2916 0.00680 0.00108 -0.0817 0.6276 0.2394
-0.750 0.3191 0.00652 0.00106 -0.0818 0.6224 0.3424
-0.500 0.3465 0.00612 0.00106 -0.0819 0.6171 0.4889
-0.250 0.3735 0.00582 0.00108 -0.0819 0.6117 0.6124
0.000 0.3990 0.00545 0.00112 -0.0814 0.6068 0.7647
0.250 0.4207 0.00500 0.00115 -0.0796 0.6016 0.9549
0.500 0.4579 0.00503 0.00112 -0.0816 0.5961 1.0000
0.750 0.4860 0.00507 0.00112 -0.0816 0.5910 1.0000
1.000 0.5141 0.00513 0.00113 -0.0816 0.5854 1.0000
1.250 0.5419 0.00521 0.00115 -0.0816 0.5799 1.0000
1.500 0.5701 0.00525 0.00117 -0.0817 0.5740 1.0000
1.750 0.5979 0.00533 0.00120 -0.0816 0.5675 1.0000
2.000 0.6260 0.00538 0.00124 -0.0817 0.5607 1.0000
2.250 0.6538 0.00547 0.00128 -0.0817 0.5534 1.0000
2.500 0.6818 0.00553 0.00132 -0.0817 0.5462 1.0000
2.750 0.7095 0.00562 0.00139 -0.0817 0.5387 1.0000
3.000 0.7375 0.00568 0.00145 -0.0817 0.5313 1.0000
3.250 0.7650 0.00579 0.00151 -0.0817 0.5234 1.0000
3.500 0.7930 0.00586 0.00159 -0.0817 0.5147 1.0000
3.750 0.8205 0.00596 0.00168 -0.0817 0.5057 1.0000
4.000 0.8480 0.00608 0.00177 -0.0816 0.4957 1.0000
4.250 0.8755 0.00619 0.00187 -0.0816 0.4836 1.0000
4.500 0.9023 0.00636 0.00197 -0.0815 0.4639 1.0000
4.750 0.9285 0.00661 0.00212 -0.0813 0.4335 1.0000
5.000 0.9545 0.00688 0.00229 -0.0811 0.4039 1.0000
5.250 0.9796 0.00726 0.00252 -0.0808 0.3659 1.0000
5.500 1.0027 0.00790 0.00287 -0.0802 0.3042 1.0000
5.750 1.0236 0.00880 0.00338 -0.0794 0.2287 1.0000
6.000 1.0452 0.00958 0.00387 -0.0787 0.1701 1.0000
6.250 1.0666 0.01037 0.00438 -0.0780 0.1179 1.0000
6.500 1.0870 0.01125 0.00496 -0.0771 0.0672 1.0000
6.750 1.1050 0.01237 0.00576 -0.0758 0.0172 1.0000
7.000 1.1282 0.01288 0.00626 -0.0752 0.0124 1.0000
7.250 1.1514 0.01338 0.00680 -0.0745 0.0108 1.0000
7.500 1.1741 0.01389 0.00737 -0.0738 0.0100 1.0000
7.750 1.1968 0.01438 0.00793 -0.0731 0.0095 1.0000
8.000 1.2187 0.01493 0.00854 -0.0723 0.0092 1.0000
8.250 1.2398 0.01553 0.00920 -0.0714 0.0089 1.0000
8.500 1.2601 0.01618 0.00991 -0.0704 0.0086 1.0000
8.750 1.2792 0.01688 0.01068 -0.0692 0.0084 1.0000
9.000 1.2971 0.01766 0.01153 -0.0679 0.0081 1.0000
9.250 1.3131 0.01852 0.01246 -0.0663 0.0078 1.0000
9.500 1.3265 0.01952 0.01355 -0.0644 0.0076 1.0000
9.750 1.3338 0.02083 0.01495 -0.0617 0.0074 1.0000
10.000 1.3343 0.02225 0.01647 -0.0578 0.0072 1.0000
10.250 1.3325 0.02399 0.01832 -0.0541 0.0071 1.0000
10.500 1.3331 0.02591 0.02034 -0.0511 0.0070 1.0000
10.750 1.3483 0.02643 0.02094 -0.0499 0.0068 1.0000
11.000 1.3559 0.02781 0.02241 -0.0481 0.0067 1.0000
11.250 1.3650 0.02908 0.02378 -0.0466 0.0066 1.0000
11.500 1.3707 0.03084 0.02564 -0.0450 0.0065 1.0000
11.750 1.3769 0.03263 0.02753 -0.0435 0.0065 1.0000
12.000 1.3824 0.03458 0.02960 -0.0422 0.0064 1.0000
12.250 1.3879 0.03658 0.03171 -0.0411 0.0063 1.0000
12.500 1.3920 0.03879 0.03406 -0.0400 0.0062 1.0000
12.750 1.3944 0.04138 0.03679 -0.0389 0.0062 1.0000
13.000 1.3958 0.04404 0.03960 -0.0381 0.0062 1.0000
13.250 1.3973 0.04660 0.04229 -0.0376 0.0060 1.0000
13.500 1.3956 0.04974 0.04559 -0.0372 0.0060 1.0000
13.750 1.3912 0.05338 0.04940 -0.0369 0.0060 1.0000
14.000 1.3872 0.05686 0.05303 -0.0371 0.0059 1.0000
14.250 1.3777 0.06138 0.05775 -0.0375 0.0060 1.0000
14.500 1.3693 0.06576 0.06230 -0.0383 0.0059 1.0000
14.750 1.3589 0.07066 0.06737 -0.0396 0.0059 1.0000
15.000 1.3461 0.07621 0.07310 -0.0414 0.0059 1.0000
15.250 1.3344 0.08183 0.07888 -0.0436 0.0058 1.0000
15.500 1.3193 0.08837 0.08559 -0.0464 0.0058 1.0000
15.750 1.3016 0.09581 0.09321 -0.0499 0.0058 1.0000
16.000 1.2849 0.10345 0.10101 -0.0540 0.0058 1.0000
16.250 1.2680 0.11153 0.10926 -0.0585 0.0058 1.0000
16.500 1.2460 0.12134 0.11924 -0.0642 0.0059 1.0000
16.750 1.2249 0.13152 0.12957 -0.0705 0.0060 1.0000
17.000 1.2007 0.14320 0.14142 -0.0779 0.0061 1.0000
17.250 1.1777 0.15544 0.15380 -0.0857 0.0062 1.0000
17.500 1.1496 0.17035 0.16885 -0.0951 0.0065 1.0000
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Polar data table (+)
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