E168 (12.45%) (e168-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E168 (12.45%) (e168-il) Reynolds number: 100,000 Max Cl/Cd: 40.52 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e168-il-100000-n5.txt Download as CSV file: xf-e168-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.8181 0.12615 0.12090 0.0130 1.0000 0.0285
-15.000 -0.8552 0.11241 0.10701 0.0050 1.0000 0.0275
-14.750 -0.8836 0.10173 0.09615 -0.0015 1.0000 0.0272
-14.500 -0.9060 0.09303 0.08727 -0.0067 1.0000 0.0271
-14.250 -0.9235 0.08586 0.07991 -0.0109 1.0000 0.0271
-14.000 -0.9388 0.07945 0.07332 -0.0146 1.0000 0.0275
-13.750 -0.9512 0.07377 0.06748 -0.0177 1.0000 0.0278
-13.500 -0.9619 0.06858 0.06206 -0.0204 1.0000 0.0283
-13.250 -0.9718 0.06369 0.05694 -0.0229 1.0000 0.0291
-13.000 -0.9783 0.05947 0.05250 -0.0247 1.0000 0.0297
-12.750 -0.9799 0.05614 0.04913 -0.0254 1.0000 0.0305
-12.500 -0.9815 0.05294 0.04586 -0.0263 1.0000 0.0314
-12.250 -0.9833 0.04982 0.04265 -0.0272 1.0000 0.0324
-12.000 -0.9839 0.04695 0.03967 -0.0277 1.0000 0.0335
-11.750 -0.9842 0.04425 0.03683 -0.0279 1.0000 0.0351
-11.500 -0.9830 0.04181 0.03420 -0.0278 1.0000 0.0369
-11.250 -0.9813 0.03956 0.03181 -0.0271 1.0000 0.0385
-11.000 -0.9822 0.03741 0.02963 -0.0261 1.0000 0.0401
-10.750 -0.9811 0.03560 0.02775 -0.0245 1.0000 0.0420
-10.500 -0.9783 0.03400 0.02605 -0.0225 1.0000 0.0443
-10.250 -0.9711 0.03258 0.02444 -0.0206 1.0000 0.0475
-10.000 -0.9662 0.03093 0.02279 -0.0188 1.0000 0.0510
-9.750 -0.9562 0.02955 0.02131 -0.0172 1.0000 0.0558
-9.500 -0.9459 0.02811 0.01981 -0.0155 1.0000 0.0609
-9.250 -0.9330 0.02684 0.01846 -0.0140 1.0000 0.0684
-9.000 -0.9198 0.02555 0.01718 -0.0126 1.0000 0.0777
-8.750 -0.9047 0.02438 0.01600 -0.0113 1.0000 0.0895
-8.500 -0.8882 0.02330 0.01493 -0.0101 1.0000 0.1047
-8.250 -0.8706 0.02233 0.01396 -0.0090 1.0000 0.1231
-8.000 -0.8524 0.02144 0.01313 -0.0079 1.0000 0.1441
-7.750 -0.8327 0.02070 0.01242 -0.0070 1.0000 0.1663
-7.500 -0.8123 0.02007 0.01180 -0.0060 1.0000 0.1882
-7.250 -0.7910 0.01952 0.01122 -0.0051 1.0000 0.2080
-7.000 -0.7694 0.01903 0.01070 -0.0042 1.0000 0.2262
-6.750 -0.7473 0.01858 0.01022 -0.0033 1.0000 0.2436
-6.500 -0.7248 0.01818 0.00977 -0.0025 1.0000 0.2605
-6.250 -0.7022 0.01780 0.00935 -0.0016 1.0000 0.2767
-6.000 -0.6794 0.01744 0.00896 -0.0007 1.0000 0.2924
-5.750 -0.6565 0.01710 0.00857 0.0002 1.0000 0.3073
-5.500 -0.6337 0.01677 0.00823 0.0011 1.0000 0.3216
-5.250 -0.6108 0.01646 0.00792 0.0020 1.0000 0.3356
-5.000 -0.5880 0.01616 0.00763 0.0029 1.0000 0.3493
-4.750 -0.5652 0.01588 0.00733 0.0038 1.0000 0.3626
-4.500 -0.5426 0.01561 0.00708 0.0048 1.0000 0.3758
-4.250 -0.5200 0.01536 0.00684 0.0057 1.0000 0.3888
-4.000 -0.4977 0.01512 0.00662 0.0067 1.0000 0.4020
-3.750 -0.4760 0.01491 0.00642 0.0077 1.0000 0.4151
-3.500 -0.4444 0.01472 0.00626 0.0067 0.9910 0.4300
-3.250 -0.4042 0.01454 0.00609 0.0041 0.9706 0.4461
-3.000 -0.3649 0.01436 0.00592 0.0018 0.9476 0.4623
-2.750 -0.3242 0.01419 0.00577 -0.0006 0.9242 0.4788
-2.500 -0.2849 0.01404 0.00562 -0.0027 0.8986 0.4954
-2.250 -0.2482 0.01392 0.00546 -0.0042 0.8714 0.5118
-2.000 -0.2153 0.01383 0.00534 -0.0047 0.8435 0.5279
-1.750 -0.1858 0.01377 0.00522 -0.0046 0.8164 0.5436
-1.500 -0.1582 0.01373 0.00513 -0.0041 0.7907 0.5595
-1.250 -0.1316 0.01370 0.00506 -0.0034 0.7659 0.5755
-1.000 -0.1052 0.01368 0.00499 -0.0027 0.7434 0.5920
-0.750 -0.0791 0.01366 0.00495 -0.0020 0.7211 0.6086
-0.500 -0.0526 0.01364 0.00493 -0.0013 0.7006 0.6256
-0.250 -0.0263 0.01363 0.00491 -0.0007 0.6808 0.6431
0.000 0.0000 0.01363 0.00491 0.0000 0.6615 0.6614
0.250 0.0263 0.01363 0.00491 0.0007 0.6431 0.6808
0.500 0.0526 0.01364 0.00493 0.0014 0.6256 0.7007
0.750 0.0791 0.01366 0.00495 0.0020 0.6086 0.7211
1.000 0.1052 0.01368 0.00499 0.0027 0.5920 0.7433
1.250 0.1316 0.01370 0.00506 0.0034 0.5755 0.7659
1.500 0.1582 0.01373 0.00513 0.0041 0.5595 0.7907
1.750 0.1858 0.01377 0.00522 0.0046 0.5436 0.8164
2.000 0.2153 0.01383 0.00534 0.0047 0.5279 0.8435
2.250 0.2481 0.01392 0.00546 0.0042 0.5118 0.8714
2.500 0.2849 0.01404 0.00562 0.0027 0.4955 0.8986
2.750 0.3242 0.01419 0.00577 0.0006 0.4788 0.9241
3.000 0.3649 0.01436 0.00592 -0.0018 0.4623 0.9475
3.250 0.4042 0.01454 0.00609 -0.0041 0.4461 0.9706
3.500 0.4444 0.01472 0.00626 -0.0067 0.4300 0.9910
3.750 0.4760 0.01491 0.00642 -0.0077 0.4151 1.0000
4.000 0.4978 0.01512 0.00663 -0.0067 0.4020 1.0000
4.250 0.5201 0.01536 0.00684 -0.0057 0.3888 1.0000
4.500 0.5426 0.01561 0.00708 -0.0048 0.3758 1.0000
4.750 0.5653 0.01588 0.00733 -0.0038 0.3626 1.0000
5.000 0.5880 0.01616 0.00763 -0.0029 0.3493 1.0000
5.250 0.6109 0.01646 0.00792 -0.0020 0.3356 1.0000
5.500 0.6337 0.01677 0.00823 -0.0011 0.3217 1.0000
5.750 0.6566 0.01710 0.00857 -0.0002 0.3073 1.0000
6.000 0.6794 0.01744 0.00894 0.0007 0.2923 1.0000
6.250 0.7022 0.01780 0.00935 0.0016 0.2767 1.0000
6.500 0.7248 0.01818 0.00977 0.0025 0.2605 1.0000
6.750 0.7473 0.01858 0.01022 0.0033 0.2436 1.0000
7.000 0.7694 0.01903 0.01070 0.0042 0.2263 1.0000
7.250 0.7909 0.01952 0.01122 0.0051 0.2080 1.0000
7.500 0.8123 0.02007 0.01180 0.0060 0.1883 1.0000
7.750 0.8327 0.02070 0.01242 0.0070 0.1664 1.0000
8.000 0.8523 0.02144 0.01313 0.0079 0.1441 1.0000
8.250 0.8705 0.02233 0.01395 0.0090 0.1230 1.0000
8.500 0.8882 0.02329 0.01492 0.0101 0.1047 1.0000
8.750 0.9046 0.02437 0.01599 0.0113 0.0895 1.0000
9.000 0.9197 0.02555 0.01718 0.0126 0.0778 1.0000
9.250 0.9329 0.02684 0.01845 0.0141 0.0685 1.0000
9.500 0.9458 0.02810 0.01980 0.0155 0.0609 1.0000
9.750 0.9560 0.02955 0.02130 0.0172 0.0558 1.0000
10.000 0.9661 0.03092 0.02278 0.0188 0.0509 1.0000
10.250 0.9710 0.03257 0.02443 0.0206 0.0476 1.0000
10.500 0.9782 0.03400 0.02605 0.0225 0.0442 1.0000
10.750 0.9809 0.03560 0.02775 0.0245 0.0418 1.0000
11.000 0.9823 0.03739 0.02961 0.0261 0.0401 1.0000
11.250 0.9817 0.03953 0.03178 0.0271 0.0385 1.0000
11.500 0.9831 0.04181 0.03420 0.0278 0.0368 1.0000
11.750 0.9842 0.04425 0.03683 0.0279 0.0350 1.0000
12.000 0.9841 0.04693 0.03965 0.0276 0.0334 1.0000
12.250 0.9834 0.04982 0.04265 0.0271 0.0323 1.0000
12.500 0.9822 0.05288 0.04580 0.0264 0.0314 1.0000
12.750 0.9802 0.05612 0.04910 0.0254 0.0305 1.0000
13.000 0.9785 0.05946 0.05247 0.0246 0.0297 1.0000
13.250 0.9722 0.06367 0.05691 0.0228 0.0291 1.0000
13.500 0.9629 0.06849 0.06196 0.0205 0.0284 1.0000
13.750 0.9523 0.07368 0.06736 0.0178 0.0279 1.0000
14.000 0.9389 0.07952 0.07343 0.0144 0.0273 1.0000
14.250 0.9244 0.08580 0.07985 0.0109 0.0272 1.0000
14.500 0.9066 0.09302 0.08725 0.0066 0.0270 1.0000
14.750 0.8846 0.10162 0.09604 0.0014 0.0271 1.0000
15.000 0.8547 0.11268 0.10728 -0.0053 0.0274 1.0000
15.250 0.8166 0.12677 0.12152 -0.0135 0.0284 1.0000
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Polar data table (+)
Polar graphs
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