E168 (12.45%) (e168-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E168 (12.45%) (e168-il) Reynolds number: 100,000 Max Cl/Cd: 38.36 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e168-il-100000.txt Download as CSV file: xf-e168-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.7162 0.13545 0.13032 0.0138 1.0000 0.0731
-13.500 -0.8147 0.10241 0.09733 -0.0062 1.0000 0.0604
-13.250 -0.8431 0.09234 0.08722 -0.0121 1.0000 0.0594
-13.000 -0.8739 0.08294 0.07773 -0.0182 1.0000 0.0579
-12.750 -0.9093 0.07414 0.06875 -0.0244 1.0000 0.0568
-12.500 -0.9423 0.06677 0.06118 -0.0290 1.0000 0.0555
-12.250 -0.9701 0.06115 0.05530 -0.0316 1.0000 0.0550
-12.000 -0.9929 0.05670 0.05059 -0.0323 1.0000 0.0546
-11.750 -1.0084 0.05332 0.04697 -0.0314 1.0000 0.0550
-11.500 -1.0197 0.05049 0.04392 -0.0293 1.0000 0.0560
-11.250 -1.0263 0.04769 0.04081 -0.0273 1.0000 0.0573
-11.000 -1.0282 0.04478 0.03751 -0.0253 1.0000 0.0586
-10.750 -1.0257 0.04207 0.03435 -0.0233 1.0000 0.0601
-10.500 -1.0124 0.03885 0.03107 -0.0224 1.0000 0.0632
-10.250 -0.9988 0.03704 0.02919 -0.0213 1.0000 0.0674
-10.000 -0.9861 0.03501 0.02680 -0.0196 1.0000 0.0716
-9.750 -0.9677 0.03259 0.02448 -0.0188 1.0000 0.0770
-9.500 -0.9531 0.03102 0.02264 -0.0172 1.0000 0.0843
-9.250 -0.9360 0.02907 0.02086 -0.0161 1.0000 0.0935
-9.000 -0.9206 0.02739 0.01919 -0.0147 1.0000 0.1054
-8.750 -0.9056 0.02586 0.01768 -0.0131 1.0000 0.1212
-8.500 -0.8907 0.02446 0.01637 -0.0115 1.0000 0.1410
-8.250 -0.8751 0.02339 0.01529 -0.0099 1.0000 0.1658
-8.000 -0.8586 0.02254 0.01460 -0.0085 1.0000 0.1914
-7.750 -0.8408 0.02192 0.01403 -0.0070 1.0000 0.2173
-7.500 -0.8219 0.02143 0.01354 -0.0056 1.0000 0.2421
-7.250 -0.8019 0.02105 0.01312 -0.0043 1.0000 0.2653
-7.000 -0.7808 0.02065 0.01274 -0.0031 1.0000 0.2857
-6.750 -0.7589 0.02033 0.01243 -0.0020 1.0000 0.3047
-6.500 -0.7369 0.01999 0.01204 -0.0009 1.0000 0.3233
-6.250 -0.7149 0.01964 0.01162 0.0003 1.0000 0.3413
-6.000 -0.6924 0.01929 0.01125 0.0014 1.0000 0.3582
-5.750 -0.6694 0.01895 0.01094 0.0024 1.0000 0.3742
-5.500 -0.6465 0.01862 0.01060 0.0035 1.0000 0.3898
-5.250 -0.6237 0.01827 0.01026 0.0045 1.0000 0.4052
-5.000 -0.6009 0.01793 0.00993 0.0056 1.0000 0.4204
-4.750 -0.5783 0.01759 0.00960 0.0067 1.0000 0.4355
-4.500 -0.5557 0.01726 0.00927 0.0077 1.0000 0.4506
-4.250 -0.5335 0.01694 0.00897 0.0088 1.0000 0.4655
-4.000 -0.5116 0.01663 0.00869 0.0100 1.0000 0.4805
-3.750 -0.4903 0.01634 0.00843 0.0111 1.0000 0.4956
-3.500 -0.4699 0.01607 0.00821 0.0124 1.0000 0.5106
-3.250 -0.4510 0.01585 0.00804 0.0139 1.0000 0.5257
-3.000 -0.4340 0.01567 0.00792 0.0155 1.0000 0.5407
-2.750 -0.4189 0.01557 0.00786 0.0172 1.0000 0.5557
-2.500 -0.4053 0.01555 0.00791 0.0189 1.0000 0.5705
-2.250 -0.3480 0.01554 0.00803 0.0128 0.9827 0.5923
-2.000 -0.2954 0.01543 0.00796 0.0078 0.9631 0.6154
-1.750 -0.2419 0.01526 0.00790 0.0031 0.9455 0.6373
-1.500 -0.1910 0.01505 0.00776 -0.0009 0.9276 0.6599
-1.250 -0.1468 0.01485 0.00762 -0.0034 0.9064 0.6816
-1.000 -0.1086 0.01469 0.00752 -0.0045 0.8830 0.7020
-0.750 -0.0772 0.01459 0.00743 -0.0042 0.8581 0.7234
-0.500 -0.0491 0.01453 0.00738 -0.0032 0.8343 0.7438
-0.250 -0.0244 0.01451 0.00738 -0.0017 0.8094 0.7645
0.000 0.0000 0.01449 0.00733 0.0000 0.7876 0.7876
0.250 0.0243 0.01451 0.00738 0.0017 0.7645 0.8094
0.500 0.0490 0.01453 0.00738 0.0032 0.7438 0.8343
0.750 0.0772 0.01459 0.00743 0.0043 0.7234 0.8581
1.000 0.1086 0.01469 0.00752 0.0045 0.7020 0.8830
1.250 0.1468 0.01485 0.00763 0.0034 0.6816 0.9064
1.500 0.1910 0.01505 0.00776 0.0009 0.6599 0.9276
1.750 0.2419 0.01526 0.00790 -0.0031 0.6373 0.9455
2.000 0.2954 0.01543 0.00796 -0.0078 0.6154 0.9631
2.250 0.3478 0.01554 0.00803 -0.0128 0.5923 0.9827
2.500 0.4052 0.01554 0.00791 -0.0189 0.5705 1.0000
2.750 0.4189 0.01557 0.00786 -0.0172 0.5556 1.0000
3.000 0.4340 0.01567 0.00792 -0.0155 0.5408 1.0000
3.250 0.4510 0.01584 0.00804 -0.0139 0.5256 1.0000
3.500 0.4699 0.01607 0.00821 -0.0124 0.5106 1.0000
3.750 0.4903 0.01634 0.00843 -0.0111 0.4955 1.0000
4.000 0.5116 0.01663 0.00869 -0.0100 0.4805 1.0000
4.250 0.5335 0.01693 0.00897 -0.0088 0.4655 1.0000
4.500 0.5557 0.01726 0.00927 -0.0077 0.4505 1.0000
4.750 0.5783 0.01759 0.00960 -0.0067 0.4355 1.0000
5.000 0.6009 0.01793 0.00993 -0.0056 0.4204 1.0000
5.250 0.6237 0.01827 0.01026 -0.0045 0.4052 1.0000
5.500 0.6465 0.01862 0.01060 -0.0035 0.3898 1.0000
5.750 0.6694 0.01895 0.01094 -0.0024 0.3741 1.0000
6.000 0.6924 0.01929 0.01125 -0.0013 0.3582 1.0000
6.250 0.7149 0.01964 0.01162 -0.0003 0.3413 1.0000
6.500 0.7369 0.01999 0.01204 0.0009 0.3233 1.0000
6.750 0.7589 0.02033 0.01244 0.0020 0.3047 1.0000
7.000 0.7808 0.02065 0.01274 0.0031 0.2857 1.0000
7.250 0.8019 0.02105 0.01312 0.0043 0.2653 1.0000
7.500 0.8219 0.02143 0.01354 0.0057 0.2421 1.0000
7.750 0.8408 0.02192 0.01403 0.0070 0.2173 1.0000
8.000 0.8586 0.02254 0.01459 0.0085 0.1913 1.0000
8.250 0.8751 0.02339 0.01530 0.0100 0.1657 1.0000
8.500 0.8907 0.02446 0.01637 0.0115 0.1410 1.0000
8.750 0.9056 0.02586 0.01768 0.0131 0.1211 1.0000
9.000 0.9205 0.02739 0.01919 0.0147 0.1052 1.0000
9.250 0.9359 0.02906 0.02086 0.0161 0.0934 1.0000
9.500 0.9532 0.03103 0.02264 0.0172 0.0844 1.0000
9.750 0.9680 0.03261 0.02451 0.0188 0.0772 1.0000
10.000 0.9863 0.03501 0.02680 0.0196 0.0717 1.0000
10.250 0.9987 0.03700 0.02916 0.0212 0.0674 1.0000
10.500 1.0124 0.03884 0.03106 0.0224 0.0631 1.0000
10.750 1.0259 0.04209 0.03437 0.0233 0.0601 1.0000
11.000 1.0285 0.04478 0.03750 0.0253 0.0587 1.0000
11.250 1.0263 0.04771 0.04083 0.0273 0.0573 1.0000
11.500 1.0197 0.05053 0.04396 0.0293 0.0560 1.0000
11.750 1.0083 0.05338 0.04704 0.0313 0.0551 1.0000
12.000 0.9933 0.05671 0.05060 0.0322 0.0546 1.0000
12.250 0.9730 0.06087 0.05500 0.0317 0.0546 1.0000
12.500 0.9460 0.06633 0.06071 0.0292 0.0548 1.0000
12.750 0.9096 0.07415 0.06877 0.0243 0.0567 1.0000
13.000 0.8747 0.08297 0.07776 0.0181 0.0580 1.0000
13.250 0.8442 0.09233 0.08721 0.0120 0.0595 1.0000
13.500 0.8157 0.10240 0.09731 0.0060 0.0604 1.0000
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Polar data table (+)
Polar graphs
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