E203 (13.64%) (e203-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E203 (13.64%) (e203-il) Reynolds number: 500,000 Max Cl/Cd: 101.31 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e203-il-500000-n5.txt Download as CSV file: xf-e203-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E203 (13.64%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.7072 0.08458 0.08171 -0.0535 1.0000 0.0093
-14.500 -0.7400 0.07441 0.07134 -0.0596 1.0000 0.0092
-14.250 -0.7635 0.06681 0.06359 -0.0642 1.0000 0.0092
-14.000 -0.7783 0.06114 0.05780 -0.0675 1.0000 0.0092
-13.750 -0.7925 0.05588 0.05241 -0.0705 1.0000 0.0093
-13.500 -0.8045 0.05122 0.04763 -0.0730 1.0000 0.0093
-13.250 -0.8152 0.04696 0.04324 -0.0751 1.0000 0.0093
-13.000 -0.8205 0.04365 0.03983 -0.0766 1.0000 0.0095
-12.750 -0.8293 0.04015 0.03619 -0.0777 1.0000 0.0095
-12.500 -0.8347 0.03737 0.03331 -0.0782 1.0000 0.0096
-12.250 -0.8392 0.03506 0.03090 -0.0781 1.0000 0.0097
-12.000 -0.8497 0.03272 0.02842 -0.0768 1.0000 0.0097
-11.750 -0.8579 0.03144 0.02706 -0.0742 1.0000 0.0099
-11.500 -0.8706 0.03027 0.02580 -0.0698 0.9998 0.0100
-11.250 -0.8478 0.02843 0.02378 -0.0721 0.9962 0.0103
-11.000 -0.8237 0.02692 0.02212 -0.0739 0.9926 0.0106
-10.750 -0.8004 0.02553 0.02057 -0.0751 0.9885 0.0109
-10.500 -0.7738 0.02423 0.01911 -0.0767 0.9850 0.0112
-10.250 -0.7474 0.02299 0.01772 -0.0780 0.9815 0.0114
-10.000 -0.7236 0.02197 0.01658 -0.0784 0.9757 0.0116
-9.750 -0.6944 0.02103 0.01551 -0.0798 0.9718 0.0117
-9.500 -0.6748 0.01949 0.01386 -0.0797 0.9640 0.0121
-9.000 -0.6239 0.01756 0.01178 -0.0807 0.9483 0.0129
-8.750 -0.5946 0.01681 0.01097 -0.0818 0.9395 0.0133
-8.500 -0.5637 0.01612 0.01020 -0.0831 0.9288 0.0139
-8.250 -0.5326 0.01541 0.00939 -0.0843 0.9154 0.0144
-8.000 -0.5019 0.01476 0.00861 -0.0854 0.8992 0.0148
-7.750 -0.4745 0.01422 0.00794 -0.0856 0.8794 0.0152
-7.500 -0.4490 0.01379 0.00737 -0.0854 0.8596 0.0155
-7.250 -0.4243 0.01343 0.00685 -0.0850 0.8409 0.0158
-7.000 -0.4009 0.01296 0.00625 -0.0844 0.8230 0.0164
-6.750 -0.3769 0.01257 0.00574 -0.0839 0.8068 0.0173
-6.500 -0.3522 0.01226 0.00533 -0.0834 0.7923 0.0183
-6.250 -0.3272 0.01200 0.00496 -0.0830 0.7786 0.0195
-6.000 -0.3018 0.01177 0.00461 -0.0826 0.7659 0.0209
-5.750 -0.2764 0.01149 0.00427 -0.0823 0.7540 0.0238
-5.500 -0.2509 0.01119 0.00395 -0.0820 0.7431 0.0312
-5.250 -0.2256 0.01087 0.00365 -0.0817 0.7329 0.0484
-5.000 -0.1999 0.01059 0.00338 -0.0815 0.7230 0.0664
-4.750 -0.1740 0.01030 0.00314 -0.0813 0.7139 0.0885
-4.500 -0.1482 0.01001 0.00292 -0.0811 0.7055 0.1169
-4.250 -0.1221 0.00972 0.00271 -0.0810 0.6969 0.1501
-4.000 -0.0960 0.00943 0.00251 -0.0809 0.6894 0.1866
-3.750 -0.0699 0.00911 0.00232 -0.0808 0.6818 0.2329
-3.500 -0.0436 0.00885 0.00216 -0.0807 0.6748 0.2751
-3.250 -0.0172 0.00859 0.00205 -0.0806 0.6677 0.3242
-3.000 0.0095 0.00842 0.00198 -0.0805 0.6614 0.3734
-2.750 0.0370 0.00833 0.00195 -0.0805 0.6548 0.4065
-2.500 0.0646 0.00831 0.00191 -0.0804 0.6486 0.4231
-2.250 0.0926 0.00829 0.00187 -0.0804 0.6429 0.4350
-2.000 0.1206 0.00829 0.00183 -0.0805 0.6369 0.4463
-1.750 0.1483 0.00828 0.00180 -0.0804 0.6314 0.4567
-1.500 0.1764 0.00827 0.00178 -0.0805 0.6257 0.4660
-1.250 0.2043 0.00828 0.00176 -0.0805 0.6203 0.4753
-1.000 0.2321 0.00827 0.00175 -0.0805 0.6152 0.4841
-0.750 0.2602 0.00828 0.00174 -0.0805 0.6097 0.4925
-0.500 0.2880 0.00829 0.00174 -0.0805 0.6046 0.5005
-0.250 0.3160 0.00830 0.00175 -0.0805 0.5997 0.5084
0.000 0.3440 0.00830 0.00176 -0.0805 0.5943 0.5173
0.250 0.3717 0.00832 0.00178 -0.0805 0.5894 0.5263
0.500 0.3996 0.00834 0.00181 -0.0806 0.5846 0.5353
0.750 0.4275 0.00834 0.00184 -0.0806 0.5793 0.5434
1.250 0.4830 0.00839 0.00193 -0.0805 0.5696 0.5605
1.500 0.5108 0.00841 0.00198 -0.0805 0.5642 0.5697
1.750 0.5383 0.00846 0.00203 -0.0805 0.5593 0.5797
2.000 0.5660 0.00847 0.00210 -0.0805 0.5541 0.5902
2.250 0.5935 0.00850 0.00217 -0.0804 0.5485 0.6024
2.500 0.6206 0.00855 0.00225 -0.0803 0.5427 0.6151
2.750 0.6480 0.00857 0.00234 -0.0802 0.5353 0.6287
3.000 0.6746 0.00862 0.00242 -0.0800 0.5276 0.6442
3.250 0.7016 0.00864 0.00252 -0.0799 0.5196 0.6619
3.500 0.7280 0.00869 0.00263 -0.0796 0.5120 0.6814
4.000 0.7804 0.00877 0.00287 -0.0790 0.4932 0.7262
4.250 0.8057 0.00882 0.00301 -0.0785 0.4830 0.7541
4.500 0.8304 0.00886 0.00315 -0.0778 0.4720 0.7866
4.750 0.8544 0.00890 0.00331 -0.0770 0.4599 0.8238
5.000 0.8766 0.00895 0.00347 -0.0757 0.4466 0.8677
5.250 0.8991 0.00902 0.00363 -0.0745 0.4306 0.9269
5.500 0.9351 0.00923 0.00382 -0.0764 0.4084 1.0000
5.750 0.9580 0.00954 0.00405 -0.0756 0.3844 1.0000
6.000 0.9794 0.00993 0.00431 -0.0746 0.3533 1.0000
6.250 0.9977 0.01053 0.00469 -0.0731 0.3065 1.0000
6.500 1.0144 0.01124 0.00515 -0.0714 0.2586 1.0000
6.750 1.0307 0.01197 0.00566 -0.0697 0.2150 1.0000
7.000 1.0469 0.01269 0.00618 -0.0679 0.1767 1.0000
7.250 1.0629 0.01338 0.00669 -0.0661 0.1438 1.0000
7.500 1.0797 0.01399 0.00718 -0.0645 0.1194 1.0000
7.750 1.0955 0.01463 0.00770 -0.0627 0.0974 1.0000
8.000 1.1085 0.01534 0.00827 -0.0604 0.0746 1.0000
8.250 1.1212 0.01594 0.00882 -0.0580 0.0593 1.0000
8.500 1.1344 0.01653 0.00936 -0.0558 0.0487 1.0000
8.750 1.1474 0.01714 0.00994 -0.0535 0.0403 1.0000
9.250 1.1714 0.01850 0.01126 -0.0491 0.0252 1.0000
9.500 1.1819 0.01930 0.01204 -0.0468 0.0184 1.0000
9.750 1.1915 0.02017 0.01291 -0.0445 0.0132 1.0000
10.000 1.2014 0.02106 0.01382 -0.0423 0.0108 1.0000
10.250 1.2120 0.02195 0.01476 -0.0404 0.0094 1.0000
10.500 1.2214 0.02297 0.01581 -0.0385 0.0083 1.0000
10.750 1.2296 0.02411 0.01701 -0.0366 0.0075 1.0000
11.000 1.2400 0.02515 0.01812 -0.0351 0.0072 1.0000
11.250 1.2492 0.02633 0.01938 -0.0336 0.0068 1.0000
11.500 1.2576 0.02762 0.02075 -0.0322 0.0066 1.0000
11.750 1.2656 0.02901 0.02222 -0.0309 0.0062 1.0000
12.000 1.2733 0.03047 0.02376 -0.0297 0.0061 1.0000
12.250 1.2799 0.03208 0.02545 -0.0286 0.0060 1.0000
12.500 1.2846 0.03392 0.02737 -0.0276 0.0057 1.0000
12.750 1.2891 0.03584 0.02937 -0.0266 0.0055 1.0000
13.000 1.2918 0.03800 0.03162 -0.0258 0.0054 1.0000
13.250 1.2914 0.04052 0.03425 -0.0250 0.0052 1.0000
13.500 1.2929 0.04296 0.03677 -0.0245 0.0051 1.0000
13.750 1.2950 0.04538 0.03929 -0.0241 0.0050 1.0000
14.000 1.2966 0.04795 0.04196 -0.0238 0.0050 1.0000
14.250 1.2983 0.05056 0.04467 -0.0237 0.0049 1.0000
14.500 1.2999 0.05327 0.04750 -0.0237 0.0049 1.0000
14.750 1.2994 0.05633 0.05067 -0.0238 0.0048 1.0000
15.000 1.2985 0.05952 0.05396 -0.0241 0.0048 1.0000
15.250 1.2982 0.06273 0.05727 -0.0245 0.0047 1.0000
15.500 1.2958 0.06632 0.06098 -0.0252 0.0046 1.0000
15.750 1.2937 0.06998 0.06475 -0.0260 0.0046 1.0000
16.000 1.2914 0.07376 0.06864 -0.0269 0.0045 1.0000
16.250 1.2875 0.07788 0.07288 -0.0280 0.0045 1.0000
16.500 1.2847 0.08196 0.07707 -0.0293 0.0044 1.0000
16.750 1.2806 0.08634 0.08157 -0.0308 0.0043 1.0000
17.000 1.2747 0.09111 0.08646 -0.0325 0.0043 1.0000
17.250 1.2710 0.09564 0.09111 -0.0343 0.0043 1.0000
17.500 1.2646 0.10073 0.09631 -0.0365 0.0042 1.0000
17.750 1.2587 0.10585 0.10155 -0.0387 0.0041 1.0000
18.000 1.2522 0.11116 0.10698 -0.0412 0.0041 1.0000
18.250 1.2463 0.11648 0.11242 -0.0438 0.0041 1.0000
18.500 1.2377 0.12238 0.11845 -0.0467 0.0040 1.0000
18.750 1.2313 0.12800 0.12420 -0.0497 0.0040 1.0000
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Polar data table (+)
Polar graphs
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