E168 (12.45%) (e168-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E168 (12.45%) (e168-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.96 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e168-il-1000000.txt Download as CSV file: xf-e168-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: E168 (12.45%)
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
------ -------- --------- --------- -------- -------- --------
-16.750 -1.1411 0.08335 0.07989 -0.0078 1.0000 0.0068
-16.500 -1.1570 0.07715 0.07359 -0.0109 1.0000 0.0069
-16.250 -1.1721 0.07126 0.06759 -0.0138 1.0000 0.0069
-16.000 -1.1876 0.06555 0.06177 -0.0165 1.0000 0.0069
-15.750 -1.2114 0.05887 0.05496 -0.0196 1.0000 0.0070
-15.500 -1.2243 0.05376 0.04973 -0.0220 1.0000 0.0070
-15.250 -1.2413 0.04821 0.04406 -0.0246 1.0000 0.0071
-15.000 -1.2572 0.04293 0.03866 -0.0269 1.0000 0.0073
-14.750 -1.2631 0.03908 0.03471 -0.0286 1.0000 0.0074
-14.500 -1.2658 0.03579 0.03130 -0.0297 1.0000 0.0073
-14.250 -1.2703 0.03253 0.02795 -0.0307 1.0000 0.0076
-14.000 -1.2711 0.02997 0.02529 -0.0309 1.0000 0.0077
-13.750 -1.2699 0.02792 0.02315 -0.0306 1.0000 0.0078
-13.500 -1.2670 0.02627 0.02142 -0.0296 1.0000 0.0081
-13.250 -1.2646 0.02484 0.01991 -0.0280 1.0000 0.0083
-13.000 -1.2598 0.02375 0.01875 -0.0259 1.0000 0.0085
-12.750 -1.2537 0.02286 0.01778 -0.0234 1.0000 0.0088
-12.500 -1.2473 0.02202 0.01687 -0.0207 1.0000 0.0090
-12.250 -1.2334 0.02133 0.01611 -0.0190 1.0000 0.0092
-12.000 -1.2249 0.02016 0.01485 -0.0168 1.0000 0.0096
-11.750 -1.2113 0.01925 0.01388 -0.0151 1.0000 0.0102
-11.500 -1.1938 0.01857 0.01316 -0.0138 1.0000 0.0107
-11.250 -1.1746 0.01799 0.01253 -0.0128 1.0000 0.0114
-11.000 -1.1540 0.01750 0.01199 -0.0118 1.0000 0.0119
-10.750 -1.1360 0.01674 0.01116 -0.0105 1.0000 0.0128
-10.500 -1.1167 0.01606 0.01046 -0.0094 1.0000 0.0138
-10.250 -1.0951 0.01559 0.00995 -0.0085 1.0000 0.0148
-10.000 -1.0728 0.01516 0.00949 -0.0077 1.0000 0.0156
-9.750 -1.0527 0.01449 0.00877 -0.0066 1.0000 0.0172
-9.500 -1.0309 0.01400 0.00826 -0.0056 1.0000 0.0187
-9.250 -1.0079 0.01362 0.00784 -0.0049 1.0000 0.0201
-9.000 -0.9865 0.01306 0.00728 -0.0038 1.0000 0.0230
-8.750 -0.9637 0.01267 0.00688 -0.0030 1.0000 0.0256
-8.500 -0.9420 0.01215 0.00639 -0.0019 1.0000 0.0313
-8.250 -0.9200 0.01168 0.00596 -0.0010 1.0000 0.0388
-8.000 -0.8978 0.01123 0.00556 0.0000 1.0000 0.0482
-7.750 -0.8753 0.01080 0.00519 0.0010 1.0000 0.0587
-7.500 -0.8528 0.01039 0.00483 0.0019 1.0000 0.0712
-7.250 -0.8302 0.00998 0.00449 0.0029 1.0000 0.0861
-7.000 -0.8080 0.00954 0.00416 0.0038 1.0000 0.1041
-6.750 -0.7852 0.00917 0.00387 0.0048 1.0000 0.1223
-6.500 -0.7623 0.00881 0.00361 0.0057 1.0000 0.1418
-6.250 -0.7392 0.00850 0.00338 0.0066 1.0000 0.1603
-6.000 -0.7157 0.00824 0.00318 0.0075 1.0000 0.1763
-5.500 -0.6418 0.00773 0.00282 0.0034 0.9931 0.2131
-5.250 -0.6053 0.00748 0.00265 0.0015 0.9858 0.2334
-5.000 -0.5691 0.00727 0.00249 -0.0002 0.9741 0.2487
-4.750 -0.5283 0.00708 0.00233 -0.0029 0.9523 0.2632
-4.500 -0.4894 0.00696 0.00215 -0.0051 0.9057 0.2773
-4.250 -0.4639 0.00695 0.00203 -0.0043 0.8581 0.2900
-4.000 -0.4385 0.00694 0.00191 -0.0036 0.8215 0.3029
-3.750 -0.4124 0.00692 0.00181 -0.0031 0.7900 0.3156
-3.500 -0.3857 0.00689 0.00172 -0.0027 0.7623 0.3280
-3.250 -0.3590 0.00685 0.00163 -0.0023 0.7373 0.3409
-3.000 -0.3320 0.00681 0.00154 -0.0020 0.7140 0.3538
-2.750 -0.3048 0.00678 0.00147 -0.0018 0.6925 0.3665
-2.500 -0.2774 0.00674 0.00140 -0.0016 0.6720 0.3788
-2.250 -0.2498 0.00672 0.00134 -0.0014 0.6524 0.3908
-1.750 -0.1946 0.00668 0.00124 -0.0010 0.6163 0.4160
-1.500 -0.1670 0.00665 0.00120 -0.0008 0.5996 0.4288
-1.250 -0.1392 0.00663 0.00117 -0.0007 0.5831 0.4414
-1.000 -0.1114 0.00662 0.00114 -0.0005 0.5672 0.4538
-0.750 -0.0836 0.00661 0.00112 -0.0004 0.5517 0.4671
-0.500 -0.0557 0.00661 0.00110 -0.0003 0.5367 0.4802
-0.250 -0.0278 0.00661 0.00109 -0.0001 0.5220 0.4939
0.000 0.0000 0.00661 0.00109 0.0000 0.5080 0.5080
0.250 0.0278 0.00661 0.00109 0.0001 0.4939 0.5220
0.500 0.0556 0.00661 0.00110 0.0003 0.4802 0.5368
0.750 0.0835 0.00661 0.00112 0.0004 0.4671 0.5517
1.000 0.1114 0.00662 0.00114 0.0005 0.4539 0.5671
1.250 0.1392 0.00663 0.00117 0.0007 0.4414 0.5830
1.500 0.1669 0.00665 0.00120 0.0008 0.4287 0.5995
1.750 0.1946 0.00668 0.00124 0.0010 0.4160 0.6164
2.250 0.2498 0.00672 0.00134 0.0014 0.3908 0.6523
2.500 0.2773 0.00674 0.00140 0.0016 0.3787 0.6720
2.750 0.3047 0.00678 0.00147 0.0018 0.3662 0.6927
3.000 0.3319 0.00681 0.00154 0.0021 0.3539 0.7141
3.250 0.3589 0.00685 0.00163 0.0024 0.3409 0.7375
3.500 0.3857 0.00689 0.00172 0.0027 0.3279 0.7624
3.750 0.4123 0.00692 0.00181 0.0031 0.3154 0.7899
4.000 0.4384 0.00694 0.00191 0.0036 0.3030 0.8213
4.250 0.4639 0.00695 0.00203 0.0043 0.2901 0.8584
4.500 0.4894 0.00696 0.00215 0.0051 0.2770 0.9057
4.750 0.5282 0.00708 0.00233 0.0030 0.2632 0.9522
5.000 0.5689 0.00727 0.00249 0.0003 0.2487 0.9740
5.250 0.6053 0.00747 0.00265 -0.0015 0.2340 0.9858
5.500 0.6417 0.00773 0.00282 -0.0034 0.2131 0.9930
6.000 0.7157 0.00824 0.00318 -0.0075 0.1763 1.0000
6.250 0.7392 0.00850 0.00338 -0.0066 0.1603 1.0000
6.500 0.7623 0.00882 0.00361 -0.0057 0.1413 1.0000
6.750 0.7852 0.00917 0.00387 -0.0048 0.1225 1.0000
7.000 0.8080 0.00954 0.00416 -0.0039 0.1040 1.0000
7.250 0.8303 0.00998 0.00449 -0.0029 0.0861 1.0000
7.500 0.8528 0.01039 0.00483 -0.0019 0.0712 1.0000
7.750 0.8754 0.01080 0.00518 -0.0010 0.0591 1.0000
8.000 0.8978 0.01123 0.00556 0.0000 0.0481 1.0000
8.250 0.9200 0.01168 0.00596 0.0010 0.0388 1.0000
8.500 0.9419 0.01215 0.00639 0.0020 0.0311 1.0000
8.750 0.9636 0.01267 0.00688 0.0030 0.0256 1.0000
9.000 0.9865 0.01306 0.00728 0.0038 0.0230 1.0000
9.250 1.0078 0.01362 0.00785 0.0049 0.0201 1.0000
9.500 1.0308 0.01400 0.00826 0.0057 0.0188 1.0000
9.750 1.0528 0.01448 0.00875 0.0065 0.0174 1.0000
10.000 1.0727 0.01517 0.00949 0.0077 0.0157 1.0000
10.250 1.0952 0.01557 0.00994 0.0085 0.0148 1.0000
10.500 1.1166 0.01607 0.01047 0.0094 0.0139 1.0000
10.750 1.1361 0.01673 0.01115 0.0105 0.0127 1.0000
11.000 1.1544 0.01746 0.01195 0.0118 0.0119 1.0000
11.250 1.1746 0.01799 0.01253 0.0128 0.0114 1.0000
11.500 1.1939 0.01857 0.01316 0.0138 0.0107 1.0000
11.750 1.2118 0.01922 0.01384 0.0150 0.0101 1.0000
12.000 1.2254 0.02014 0.01483 0.0167 0.0097 1.0000
12.250 1.2329 0.02138 0.01617 0.0191 0.0092 1.0000
12.500 1.2467 0.02206 0.01692 0.0207 0.0089 1.0000
12.750 1.2547 0.02282 0.01775 0.0233 0.0087 1.0000
13.000 1.2604 0.02374 0.01874 0.0258 0.0085 1.0000
13.250 1.2661 0.02479 0.01985 0.0278 0.0082 1.0000
13.500 1.2669 0.02631 0.02146 0.0296 0.0081 1.0000
13.750 1.2702 0.02792 0.02317 0.0305 0.0079 1.0000
14.000 1.2714 0.02999 0.02532 0.0308 0.0077 1.0000
14.250 1.2719 0.03242 0.02783 0.0306 0.0075 1.0000
14.500 1.2681 0.03560 0.03111 0.0297 0.0073 1.0000
14.750 1.2601 0.03953 0.03516 0.0282 0.0072 1.0000
15.000 1.2529 0.04358 0.03932 0.0265 0.0072 1.0000
15.250 1.2420 0.04824 0.04409 0.0244 0.0071 1.0000
15.500 1.2264 0.05361 0.04959 0.0219 0.0070 1.0000
15.750 1.2117 0.05898 0.05507 0.0194 0.0070 1.0000
16.000 1.1832 0.06634 0.06258 0.0159 0.0068 1.0000
16.250 1.1780 0.07059 0.06691 0.0139 0.0069 1.0000
16.500 1.1593 0.07701 0.07345 0.0107 0.0068 1.0000
16.750 1.1511 0.08211 0.07864 0.0082 0.0068 1.0000
17.000 1.1362 0.08826 0.08489 0.0051 0.0068 1.0000
17.250 1.1245 0.09416 0.09088 0.0021 0.0067 1.0000
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Polar data table (+)
Polar graphs
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