EPPLER 361 AIRFOIL (e361-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 361 AIRFOIL (e361-il) Reynolds number: 1,000,000 Max Cl/Cd: 84.8 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e361-il-1000000-n5.txt Download as CSV file: xf-e361-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 361 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.7829 0.05597 0.05384 -0.0414 1.0000 0.0039
-12.250 -0.8159 0.04811 0.04578 -0.0461 1.0000 0.0039
-12.000 -0.8441 0.04271 0.04016 -0.0467 1.0000 0.0039
-11.750 -0.8634 0.03907 0.03633 -0.0452 1.0000 0.0039
-11.500 -0.8859 0.03556 0.03257 -0.0419 1.0000 0.0039
-11.250 -0.8960 0.03333 0.03017 -0.0383 1.0000 0.0039
-11.000 -0.9082 0.03106 0.02767 -0.0335 1.0000 0.0039
-10.750 -0.9092 0.02907 0.02547 -0.0301 1.0000 0.0039
-10.500 -0.9054 0.02720 0.02340 -0.0272 1.0000 0.0039
-10.250 -0.8987 0.02547 0.02146 -0.0245 1.0000 0.0039
-10.000 -0.8881 0.02409 0.01992 -0.0222 1.0000 0.0039
-9.750 -0.8742 0.02262 0.01826 -0.0204 0.9978 0.0039
-9.500 -0.8463 0.02109 0.01653 -0.0215 0.9767 0.0039
-9.250 -0.8071 0.01950 0.01470 -0.0249 0.9334 0.0039
-9.000 -0.7867 0.01864 0.01355 -0.0238 0.8819 0.0039
-8.750 -0.7688 0.01791 0.01259 -0.0221 0.8491 0.0039
-8.500 -0.7496 0.01716 0.01164 -0.0206 0.8244 0.0039
-8.250 -0.7293 0.01648 0.01080 -0.0194 0.8040 0.0039
-8.000 -0.7079 0.01589 0.01007 -0.0183 0.7870 0.0039
-7.750 -0.6878 0.01503 0.00905 -0.0170 0.7716 0.0040
-7.500 -0.6664 0.01436 0.00824 -0.0159 0.7570 0.0040
-7.250 -0.6439 0.01383 0.00761 -0.0149 0.7437 0.0041
-7.000 -0.6210 0.01334 0.00701 -0.0140 0.7311 0.0041
-6.750 -0.5980 0.01282 0.00640 -0.0131 0.7198 0.0042
-6.500 -0.5739 0.01243 0.00594 -0.0124 0.7096 0.0043
-6.250 -0.5496 0.01208 0.00552 -0.0118 0.6997 0.0044
-6.000 -0.5250 0.01174 0.00512 -0.0111 0.6893 0.0046
-5.750 -0.5000 0.01146 0.00478 -0.0106 0.6803 0.0047
-5.500 -0.4748 0.01119 0.00445 -0.0100 0.6716 0.0048
-5.250 -0.4493 0.01093 0.00415 -0.0096 0.6640 0.0050
-5.000 -0.4238 0.01069 0.00385 -0.0091 0.6555 0.0053
-4.750 -0.3980 0.01047 0.00359 -0.0086 0.6481 0.0057
-4.500 -0.3722 0.01025 0.00332 -0.0082 0.6407 0.0061
-4.250 -0.3463 0.01003 0.00308 -0.0077 0.6344 0.0071
-4.000 -0.3199 0.00986 0.00287 -0.0074 0.6276 0.0080
-3.750 -0.2938 0.00969 0.00268 -0.0070 0.6210 0.0095
-3.500 -0.2674 0.00950 0.00250 -0.0067 0.6151 0.0127
-3.250 -0.2411 0.00933 0.00233 -0.0063 0.6089 0.0181
-3.000 -0.2148 0.00917 0.00218 -0.0060 0.6034 0.0259
-2.750 -0.1884 0.00898 0.00205 -0.0057 0.5978 0.0382
-2.500 -0.1625 0.00877 0.00191 -0.0053 0.5923 0.0604
-2.250 -0.1373 0.00849 0.00177 -0.0048 0.5873 0.1011
-2.000 -0.1129 0.00811 0.00163 -0.0042 0.5823 0.1663
-1.750 -0.0888 0.00773 0.00150 -0.0036 0.5772 0.2419
-1.500 -0.0659 0.00728 0.00137 -0.0028 0.5725 0.3412
-1.250 -0.0421 0.00687 0.00125 -0.0021 0.5680 0.4307
-1.000 -0.0196 0.00642 0.00114 -0.0012 0.5631 0.5345
-0.500 0.0282 0.00589 0.00107 0.0005 0.5540 0.6818
-0.250 0.0535 0.00575 0.00108 0.0012 0.5487 0.7306
0.000 0.0798 0.00572 0.00109 0.0016 0.5420 0.7570
0.250 0.1069 0.00570 0.00110 0.0019 0.5335 0.7770
0.500 0.1340 0.00572 0.00111 0.0022 0.5233 0.7927
0.750 0.1612 0.00575 0.00112 0.0024 0.5111 0.8051
1.000 0.1885 0.00580 0.00113 0.0026 0.4960 0.8156
1.250 0.2159 0.00585 0.00115 0.0028 0.4822 0.8242
1.500 0.2437 0.00591 0.00117 0.0028 0.4715 0.8302
1.750 0.2713 0.00596 0.00121 0.0029 0.4613 0.8356
2.000 0.2989 0.00604 0.00124 0.0030 0.4474 0.8412
2.500 0.3533 0.00624 0.00134 0.0032 0.4112 0.8516
2.750 0.3797 0.00642 0.00143 0.0035 0.3847 0.8574
3.000 0.4055 0.00666 0.00153 0.0038 0.3501 0.8629
3.250 0.4309 0.00691 0.00166 0.0042 0.3157 0.8685
3.500 0.4562 0.00717 0.00181 0.0046 0.2836 0.8748
3.750 0.4812 0.00747 0.00198 0.0050 0.2509 0.8807
4.000 0.5062 0.00774 0.00215 0.0054 0.2223 0.8871
4.250 0.5316 0.00798 0.00230 0.0058 0.2007 0.8938
4.500 0.5571 0.00819 0.00246 0.0062 0.1825 0.9004
4.750 0.5823 0.00842 0.00264 0.0066 0.1647 0.9078
5.000 0.6078 0.00863 0.00281 0.0069 0.1507 0.9150
5.250 0.6336 0.00883 0.00299 0.0072 0.1404 0.9231
5.750 0.6860 0.00924 0.00337 0.0076 0.1222 0.9396
6.000 0.7136 0.00946 0.00357 0.0075 0.1153 0.9471
6.250 0.7418 0.00966 0.00377 0.0072 0.1098 0.9548
6.500 0.7710 0.00992 0.00400 0.0067 0.1029 0.9610
6.750 0.8012 0.01013 0.00422 0.0060 0.0990 0.9666
7.000 0.8297 0.01038 0.00446 0.0055 0.0940 0.9724
7.250 0.8610 0.01064 0.00471 0.0045 0.0893 0.9759
7.500 0.8908 0.01087 0.00495 0.0038 0.0861 0.9803
7.750 0.9194 0.01115 0.00522 0.0033 0.0818 0.9844
8.000 0.9510 0.01144 0.00550 0.0021 0.0776 0.9864
8.250 0.9818 0.01169 0.00578 0.0011 0.0749 0.9889
8.500 1.0112 0.01201 0.00608 0.0003 0.0709 0.9919
8.750 1.0401 0.01234 0.00640 -0.0004 0.0670 0.9947
9.000 1.0708 0.01263 0.00671 -0.0014 0.0640 0.9969
9.250 1.1007 0.01298 0.00706 -0.0024 0.0608 0.9990
9.500 1.1255 0.01334 0.00742 -0.0023 0.0574 1.0000
9.750 1.1433 0.01362 0.00772 -0.0006 0.0554 1.0000
10.000 1.1607 0.01393 0.00805 0.0011 0.0530 1.0000
10.250 1.1772 0.01430 0.00842 0.0029 0.0504 1.0000
10.500 1.1942 0.01465 0.00879 0.0046 0.0480 1.0000
10.750 1.2111 0.01500 0.00916 0.0062 0.0458 1.0000
11.000 1.2265 0.01542 0.00959 0.0081 0.0432 1.0000
11.250 1.2413 0.01586 0.01004 0.0100 0.0408 1.0000
11.500 1.2562 0.01626 0.01047 0.0120 0.0392 1.0000
11.750 1.2673 0.01669 0.01092 0.0146 0.0375 1.0000
12.000 1.2769 0.01722 0.01147 0.0172 0.0354 1.0000
12.250 1.2881 0.01775 0.01204 0.0195 0.0340 1.0000
12.500 1.3004 0.01830 0.01263 0.0214 0.0329 1.0000
12.750 1.3116 0.01895 0.01332 0.0232 0.0312 1.0000
13.000 1.3214 0.01975 0.01414 0.0250 0.0296 1.0000
13.250 1.3317 0.02057 0.01501 0.0266 0.0283 1.0000
13.500 1.3428 0.02142 0.01592 0.0279 0.0272 1.0000
13.750 1.3531 0.02238 0.01692 0.0291 0.0261 1.0000
14.000 1.3613 0.02354 0.01812 0.0303 0.0245 1.0000
14.250 1.3700 0.02474 0.01937 0.0313 0.0234 1.0000
14.500 1.3794 0.02595 0.02064 0.0321 0.0225 1.0000
14.750 1.3875 0.02731 0.02206 0.0328 0.0215 1.0000
15.000 1.3943 0.02884 0.02363 0.0334 0.0205 1.0000
15.250 1.3997 0.03054 0.02540 0.0340 0.0195 1.0000
15.500 1.4065 0.03217 0.02710 0.0343 0.0187 1.0000
15.750 1.4120 0.03395 0.02895 0.0346 0.0180 1.0000
16.000 1.4158 0.03593 0.03099 0.0348 0.0172 1.0000
16.250 1.4180 0.03813 0.03325 0.0349 0.0165 1.0000
16.500 1.4194 0.04043 0.03561 0.0349 0.0155 1.0000
16.750 1.4212 0.04276 0.03804 0.0348 0.0154 1.0000
17.000 1.4218 0.04527 0.04062 0.0346 0.0148 1.0000
17.250 1.4207 0.04804 0.04347 0.0342 0.0141 1.0000
17.500 1.4179 0.05108 0.04660 0.0336 0.0136 1.0000
17.750 1.4132 0.05448 0.05006 0.0328 0.0130 1.0000
18.000 1.4086 0.05795 0.05363 0.0318 0.0126 1.0000
18.250 1.4041 0.06153 0.05731 0.0307 0.0122 1.0000
18.500 1.3972 0.06554 0.06141 0.0294 0.0116 1.0000
18.750 1.3874 0.07003 0.06599 0.0277 0.0110 1.0000
19.000 1.3747 0.07511 0.07116 0.0257 0.0105 1.0000
19.250 1.3637 0.08011 0.07628 0.0235 0.0106 1.0000
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Polar data table (+)
Polar graphs
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