EPPLER 694 AIRFOIL (e694-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 694 AIRFOIL (e694-il) Reynolds number: 500,000 Max Cl/Cd: 111.79 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e694-il-500000-n5.txt Download as CSV file: xf-e694-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 694 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-12.500 0.0504 0.08705 0.08389 -0.1852 0.9241 0.0098
-12.250 0.0525 0.08270 0.07953 -0.1878 0.9225 0.0097
-12.000 0.0502 0.07770 0.07453 -0.1906 0.9208 0.0096
-11.750 0.0416 0.07305 0.06990 -0.1918 0.9183 0.0094
-11.500 -0.0765 0.04497 0.04162 -0.2059 0.9113 0.0085
-11.250 -0.1056 0.03820 0.03456 -0.2108 0.9075 0.0085
-11.000 -0.1328 0.03449 0.03066 -0.2096 0.9033 0.0085
-10.750 -0.1513 0.03185 0.02781 -0.2074 0.8992 0.0085
-10.500 -0.1638 0.02952 0.02526 -0.2051 0.8953 0.0085
-10.250 -0.1701 0.02747 0.02297 -0.2029 0.8925 0.0085
-10.000 -0.1850 0.02638 0.02175 -0.1975 0.8885 0.0086
-9.750 -0.1883 0.02507 0.02025 -0.1941 0.8849 0.0087
-9.500 -0.1838 0.02361 0.01855 -0.1918 0.8821 0.0088
-9.250 -0.1718 0.02233 0.01706 -0.1905 0.8798 0.0089
-9.000 -0.1550 0.02106 0.01555 -0.1899 0.8779 0.0091
-8.750 -0.1432 0.02018 0.01451 -0.1879 0.8754 0.0092
-8.500 -0.1334 0.01939 0.01360 -0.1852 0.8721 0.0093
-8.250 -0.1171 0.01869 0.01276 -0.1837 0.8692 0.0096
-8.000 -0.0968 0.01797 0.01190 -0.1830 0.8668 0.0097
-7.750 -0.0738 0.01729 0.01109 -0.1828 0.8648 0.0098
-7.500 -0.0486 0.01653 0.01023 -0.1831 0.8631 0.0100
-7.250 -0.0349 0.01579 0.00944 -0.1810 0.8598 0.0102
-7.000 -0.0227 0.01529 0.00891 -0.1784 0.8554 0.0103
-6.750 -0.0023 0.01476 0.00835 -0.1775 0.8523 0.0107
-6.500 0.0227 0.01430 0.00784 -0.1776 0.8500 0.0112
-6.250 0.0510 0.01380 0.00728 -0.1783 0.8482 0.0117
-6.000 0.0631 0.01350 0.00696 -0.1755 0.8435 0.0121
-5.750 0.0793 0.01313 0.00656 -0.1735 0.8389 0.0123
-5.500 0.1040 0.01273 0.00610 -0.1734 0.8360 0.0126
-5.000 0.1407 0.01208 0.00537 -0.1703 0.8275 0.0135
-4.750 0.1617 0.01176 0.00502 -0.1693 0.8233 0.0141
-4.500 0.1907 0.01146 0.00467 -0.1700 0.8206 0.0151
-4.250 0.2097 0.01128 0.00445 -0.1684 0.8158 0.0161
-4.000 0.2333 0.01106 0.00422 -0.1679 0.8118 0.0180
-3.750 0.2621 0.01078 0.00396 -0.1686 0.8090 0.0253
-3.500 0.2938 0.01042 0.00371 -0.1700 0.8069 0.0554
-3.250 0.3210 0.01016 0.00358 -0.1704 0.8040 0.0896
-3.000 0.3495 0.00991 0.00344 -0.1711 0.8012 0.1304
-2.750 0.3815 0.00950 0.00329 -0.1728 0.7987 0.2085
-2.500 0.4173 0.00898 0.00315 -0.1754 0.7967 0.3296
-2.250 0.4545 0.00855 0.00303 -0.1783 0.7950 0.4371
-2.000 0.4935 0.00812 0.00298 -0.1815 0.7937 0.5650
-1.750 0.5242 0.00798 0.00302 -0.1825 0.7917 0.6243
-1.500 0.5521 0.00798 0.00312 -0.1827 0.7892 0.6650
-1.250 0.5800 0.00803 0.00321 -0.1828 0.7867 0.6980
-1.000 0.6089 0.00810 0.00328 -0.1832 0.7841 0.7198
-0.750 0.6398 0.00818 0.00333 -0.1840 0.7818 0.7360
-0.250 0.6990 0.00834 0.00342 -0.1852 0.7777 0.7507
0.000 0.7246 0.00844 0.00350 -0.1849 0.7752 0.7563
0.250 0.7536 0.00852 0.00354 -0.1855 0.7724 0.7620
0.500 0.7829 0.00860 0.00360 -0.1860 0.7694 0.7655
0.750 0.8163 0.00869 0.00366 -0.1874 0.7666 0.7699
1.000 0.8492 0.00880 0.00374 -0.1887 0.7642 0.7758
1.250 0.8682 0.00892 0.00387 -0.1871 0.7602 0.7802
1.500 0.8912 0.00903 0.00399 -0.1862 0.7557 0.7831
1.750 0.9242 0.00913 0.00404 -0.1876 0.7512 0.7856
2.000 0.9512 0.00923 0.00414 -0.1877 0.7471 0.7885
2.250 0.9690 0.00935 0.00428 -0.1858 0.7421 0.7917
2.500 0.9952 0.00945 0.00437 -0.1858 0.7379 0.7945
2.750 1.0258 0.00953 0.00445 -0.1866 0.7345 0.7960
3.000 1.0481 0.00965 0.00460 -0.1857 0.7309 0.7979
3.250 1.0658 0.00979 0.00480 -0.1839 0.7269 0.8002
3.500 1.0878 0.00991 0.00496 -0.1829 0.7230 0.8024
3.750 1.1148 0.01001 0.00507 -0.1830 0.7188 0.8045
4.000 1.1332 0.01016 0.00527 -0.1814 0.7136 0.8069
4.250 1.1499 0.01034 0.00548 -0.1794 0.7069 0.8096
4.500 1.1704 0.01047 0.00565 -0.1782 0.7007 0.8117
4.750 1.1800 0.01071 0.00597 -0.1747 0.6902 0.8145
5.000 1.1907 0.01096 0.00625 -0.1714 0.6752 0.8174
5.250 1.2008 0.01128 0.00653 -0.1681 0.6544 0.8198
5.500 1.2083 0.01174 0.00688 -0.1644 0.6282 0.8221
5.750 1.2152 0.01237 0.00737 -0.1607 0.5997 0.8241
6.000 1.2213 0.01312 0.00797 -0.1570 0.5696 0.8259
6.250 1.2238 0.01401 0.00871 -0.1527 0.5365 0.8274
6.500 1.2244 0.01505 0.00959 -0.1482 0.4999 0.8291
6.750 1.2255 0.01617 0.01054 -0.1439 0.4637 0.8309
7.000 1.2276 0.01733 0.01154 -0.1400 0.4286 0.8325
7.250 1.2317 0.01849 0.01254 -0.1365 0.3926 0.8341
7.500 1.2364 0.01969 0.01357 -0.1333 0.3574 0.8357
7.750 1.2412 0.02096 0.01465 -0.1302 0.3197 0.8372
8.000 1.2443 0.02239 0.01585 -0.1270 0.2747 0.8387
8.250 1.2496 0.02379 0.01703 -0.1242 0.2367 0.8403
8.500 1.2604 0.02485 0.01800 -0.1223 0.2139 0.8417
8.750 1.2685 0.02611 0.01910 -0.1200 0.1802 0.8429
9.000 1.2776 0.02735 0.02019 -0.1179 0.1515 0.8441
9.250 1.2878 0.02855 0.02129 -0.1161 0.1286 0.8453
9.500 1.2984 0.02976 0.02242 -0.1143 0.1076 0.8466
9.750 1.3078 0.03109 0.02364 -0.1125 0.0866 0.8478
10.000 1.3176 0.03243 0.02489 -0.1108 0.0669 0.8492
10.250 1.3262 0.03391 0.02627 -0.1090 0.0474 0.8505
10.500 1.3332 0.03556 0.02781 -0.1072 0.0293 0.8518
10.750 1.3416 0.03714 0.02932 -0.1055 0.0162 0.8531
11.000 1.3519 0.03860 0.03079 -0.1041 0.0116 0.8545
11.500 1.3765 0.04119 0.03349 -0.1018 0.0095 0.8573
11.750 1.3881 0.04255 0.03492 -0.1006 0.0090 0.8586
12.000 1.3986 0.04404 0.03649 -0.0994 0.0085 0.8598
12.250 1.4104 0.04543 0.03798 -0.0984 0.0082 0.8612
12.500 1.4213 0.04694 0.03957 -0.0973 0.0080 0.8625
12.750 1.4317 0.04853 0.04125 -0.0963 0.0078 0.8639
13.000 1.4414 0.05021 0.04301 -0.0953 0.0076 0.8654
13.250 1.4502 0.05201 0.04490 -0.0942 0.0074 0.8668
13.500 1.4587 0.05387 0.04685 -0.0933 0.0071 0.8683
13.750 1.4657 0.05592 0.04899 -0.0923 0.0069 0.8696
14.000 1.4717 0.05812 0.05127 -0.0913 0.0067 0.8710
14.250 1.4759 0.06052 0.05377 -0.0903 0.0065 0.8722
14.500 1.4772 0.06332 0.05667 -0.0892 0.0063 0.8735
14.750 1.4799 0.06600 0.05946 -0.0883 0.0062 0.8749
15.000 1.4838 0.06860 0.06217 -0.0876 0.0061 0.8765
15.250 1.4870 0.07134 0.06503 -0.0871 0.0061 0.8782
15.500 1.4895 0.07424 0.06804 -0.0866 0.0060 0.8799
15.750 1.4913 0.07731 0.07124 -0.0862 0.0059 0.8816
16.000 1.4925 0.08055 0.07459 -0.0860 0.0058 0.8831
16.250 1.4929 0.08394 0.07810 -0.0860 0.0057 0.8845
16.500 1.4926 0.08746 0.08174 -0.0860 0.0057 0.8859
16.750 1.4919 0.09109 0.08549 -0.0862 0.0056 0.8872
17.000 1.4906 0.09487 0.08939 -0.0866 0.0055 0.8887
17.250 1.4890 0.09875 0.09340 -0.0871 0.0054 0.8903
17.500 1.4870 0.10274 0.09751 -0.0878 0.0054 0.8919
17.750 1.4847 0.10683 0.10173 -0.0887 0.0053 0.8936
18.000 1.4822 0.11099 0.10601 -0.0897 0.0053 0.8954
18.250 1.4795 0.11522 0.11036 -0.0909 0.0052 0.8972
18.750 1.4738 0.12383 0.11922 -0.0938 0.0051 0.9009
19.000 1.4706 0.12819 0.12370 -0.0954 0.0051 0.9032
19.250 1.4675 0.13257 0.12821 -0.0972 0.0050 0.9057
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