E591 (e591-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E591 (e591-il) Reynolds number: 1,000,000 Max Cl/Cd: 129.91 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e591-il-1000000.txt Download as CSV file: xf-e591-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: E591
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3274 0.05955 0.05726 -0.1114 0.9774 0.0132
-11.250 -0.3589 0.04595 0.04337 -0.1284 0.9734 0.0130
-11.000 -0.3718 0.03954 0.03681 -0.1351 0.9638 0.0130
-10.750 -0.3816 0.03369 0.03078 -0.1416 0.9527 0.0130
-10.500 -0.3703 0.02780 0.02466 -0.1519 0.9430 0.0131
-10.250 -0.3347 0.02403 0.02065 -0.1624 0.9384 0.0131
-10.000 -0.3034 0.02202 0.01846 -0.1670 0.9323 0.0132
-9.750 -0.2701 0.01883 0.01498 -0.1731 0.9260 0.0135
-9.500 -0.2264 0.01719 0.01321 -0.1785 0.9227 0.0138
-9.250 -0.1888 0.01632 0.01228 -0.1816 0.9150 0.0141
-9.000 -0.1413 0.01556 0.01143 -0.1865 0.9093 0.0145
-8.750 -0.0985 0.01483 0.01060 -0.1903 0.9006 0.0150
-8.250 -0.0252 0.01353 0.00903 -0.1950 0.8760 0.0157
-8.000 0.0055 0.01303 0.00841 -0.1960 0.8619 0.0159
-7.750 0.0349 0.01272 0.00797 -0.1964 0.8476 0.0161
-7.500 0.0629 0.01187 0.00699 -0.1972 0.8331 0.0167
-7.250 0.0906 0.01151 0.00654 -0.1974 0.8188 0.0171
-7.000 0.1180 0.01123 0.00619 -0.1974 0.8051 0.0175
-6.750 0.1453 0.01097 0.00583 -0.1973 0.7914 0.0180
-6.500 0.1725 0.01074 0.00550 -0.1972 0.7776 0.0186
-6.250 0.2000 0.01055 0.00521 -0.1971 0.7643 0.0191
-6.000 0.2283 0.01015 0.00473 -0.1974 0.7513 0.0200
-5.750 0.2556 0.00998 0.00448 -0.1972 0.7381 0.0208
-5.500 0.2834 0.00984 0.00427 -0.1971 0.7251 0.0218
-5.250 0.3115 0.00967 0.00401 -0.1971 0.7127 0.0229
-5.000 0.3391 0.00952 0.00380 -0.1970 0.6999 0.0245
-4.750 0.3673 0.00943 0.00364 -0.1969 0.6876 0.0261
-4.500 0.3960 0.00923 0.00338 -0.1970 0.6757 0.0284
-4.000 0.4526 0.00902 0.00304 -0.1970 0.6518 0.0341
-3.750 0.4808 0.00892 0.00289 -0.1970 0.6401 0.0383
-3.500 0.5095 0.00883 0.00276 -0.1970 0.6281 0.0442
-3.250 0.5385 0.00869 0.00264 -0.1972 0.6173 0.0588
-3.000 0.5678 0.00850 0.00252 -0.1976 0.6055 0.0955
-2.750 0.5980 0.00827 0.00242 -0.1982 0.5948 0.1477
-2.500 0.6267 0.00817 0.00239 -0.1984 0.5836 0.1928
-2.250 0.6558 0.00811 0.00239 -0.1986 0.5733 0.2270
-2.000 0.6837 0.00813 0.00241 -0.1985 0.5628 0.2528
-1.750 0.7121 0.00815 0.00243 -0.1984 0.5527 0.2706
-1.500 0.7398 0.00821 0.00246 -0.1983 0.5430 0.2862
-1.250 0.7677 0.00827 0.00249 -0.1981 0.5331 0.3007
-1.000 0.7952 0.00835 0.00254 -0.1979 0.5237 0.3153
-0.750 0.8233 0.00840 0.00259 -0.1978 0.5146 0.3297
-0.500 0.8506 0.00850 0.00265 -0.1975 0.5055 0.3429
-0.250 0.8783 0.00858 0.00271 -0.1974 0.4967 0.3571
0.000 0.9054 0.00868 0.00278 -0.1971 0.4879 0.3683
0.250 0.9333 0.00875 0.00283 -0.1969 0.4802 0.3780
0.500 0.9601 0.00887 0.00291 -0.1966 0.4712 0.3883
0.750 0.9877 0.00895 0.00298 -0.1964 0.4641 0.3988
1.000 1.0149 0.00905 0.00307 -0.1962 0.4561 0.4103
1.250 1.0417 0.00918 0.00316 -0.1959 0.4487 0.4209
1.500 1.0691 0.00926 0.00325 -0.1957 0.4414 0.4341
1.750 1.0952 0.00941 0.00336 -0.1952 0.4336 0.4464
2.000 1.1226 0.00949 0.00346 -0.1951 0.4274 0.4605
2.250 1.1492 0.00961 0.00358 -0.1947 0.4202 0.4754
2.500 1.1751 0.00976 0.00371 -0.1943 0.4131 0.4903
3.000 1.2281 0.01000 0.00397 -0.1936 0.4003 0.5248
3.250 1.2540 0.01014 0.00412 -0.1932 0.3938 0.5430
3.500 1.2804 0.01025 0.00426 -0.1929 0.3879 0.5626
3.750 1.3054 0.01042 0.00443 -0.1923 0.3809 0.5838
4.000 1.3308 0.01055 0.00459 -0.1918 0.3749 0.6056
4.250 1.3560 0.01067 0.00475 -0.1912 0.3689 0.6286
4.500 1.3796 0.01086 0.00495 -0.1904 0.3621 0.6551
4.750 1.4044 0.01098 0.00512 -0.1898 0.3564 0.6837
5.000 1.4287 0.01113 0.00532 -0.1891 0.3503 0.7141
5.250 1.4514 0.01134 0.00556 -0.1881 0.3434 0.7507
5.500 1.4754 0.01144 0.00577 -0.1873 0.3382 0.7978
5.750 1.4961 0.01154 0.00599 -0.1859 0.3322 0.8658
6.000 1.5096 0.01162 0.00616 -0.1829 0.3262 1.0000
6.250 1.5335 0.01182 0.00635 -0.1821 0.3212 1.0000
6.500 1.5562 0.01206 0.00657 -0.1812 0.3152 1.0000
6.750 1.5771 0.01239 0.00685 -0.1800 0.3087 1.0000
7.000 1.6002 0.01261 0.00707 -0.1792 0.3044 1.0000
7.250 1.6218 0.01288 0.00733 -0.1781 0.2987 1.0000
7.500 1.6414 0.01326 0.00766 -0.1767 0.2922 1.0000
7.750 1.6637 0.01350 0.00792 -0.1757 0.2880 1.0000
8.000 1.6848 0.01381 0.00821 -0.1746 0.2827 1.0000
8.250 1.7033 0.01422 0.00858 -0.1731 0.2766 1.0000
8.500 1.7239 0.01453 0.00891 -0.1719 0.2722 1.0000
8.750 1.7441 0.01486 0.00925 -0.1707 0.2674 1.0000
9.000 1.7621 0.01531 0.00967 -0.1692 0.2618 1.0000
9.250 1.7805 0.01572 0.01008 -0.1677 0.2571 1.0000
9.500 1.7998 0.01610 0.01047 -0.1664 0.2525 1.0000
9.750 1.8169 0.01659 0.01095 -0.1648 0.2474 1.0000
10.000 1.8328 0.01714 0.01149 -0.1630 0.2423 1.0000
10.250 1.8514 0.01756 0.01194 -0.1617 0.2382 1.0000
10.500 1.8673 0.01812 0.01250 -0.1601 0.2334 1.0000
10.750 1.8804 0.01884 0.01320 -0.1580 0.2277 1.0000
11.000 1.8980 0.01933 0.01373 -0.1567 0.2243 1.0000
11.250 1.9131 0.01996 0.01438 -0.1550 0.2199 1.0000
11.500 1.9253 0.02078 0.01519 -0.1531 0.2149 1.0000
11.750 1.9394 0.02151 0.01594 -0.1514 0.2109 1.0000
12.000 1.9538 0.02222 0.01669 -0.1498 0.2070 1.0000
12.250 1.9655 0.02313 0.01760 -0.1480 0.2026 1.0000
12.500 1.9745 0.02424 0.01871 -0.1459 0.1977 1.0000
12.750 1.9889 0.02503 0.01955 -0.1445 0.1945 1.0000
13.000 1.9997 0.02607 0.02062 -0.1428 0.1905 1.0000
13.250 2.0071 0.02739 0.02195 -0.1409 0.1860 1.0000
13.500 2.0173 0.02856 0.02316 -0.1393 0.1824 1.0000
13.750 2.0278 0.02974 0.02438 -0.1378 0.1789 1.0000
14.000 2.0352 0.03119 0.02586 -0.1362 0.1750 1.0000
14.250 2.0389 0.03301 0.02769 -0.1344 0.1705 1.0000
14.500 2.0489 0.03435 0.02910 -0.1332 0.1677 1.0000
14.750 2.0562 0.03597 0.03076 -0.1319 0.1642 1.0000
15.000 2.0598 0.03799 0.03280 -0.1304 0.1603 1.0000
15.250 2.0622 0.04018 0.03503 -0.1291 0.1565 1.0000
15.500 2.0693 0.04198 0.03690 -0.1281 0.1537 1.0000
15.750 2.0728 0.04420 0.03917 -0.1271 0.1503 1.0000
16.000 2.0720 0.04694 0.04194 -0.1260 0.1466 1.0000
16.250 2.0735 0.04952 0.04458 -0.1252 0.1434 1.0000
16.500 2.0773 0.05190 0.04703 -0.1245 0.1405 1.0000
16.750 2.0764 0.05488 0.05006 -0.1239 0.1372 1.0000
17.000 2.0710 0.05849 0.05371 -0.1234 0.1337 1.0000
17.250 2.0707 0.06158 0.05687 -0.1230 0.1309 1.0000
17.500 2.0713 0.06460 0.05997 -0.1228 0.1282 1.0000
17.750 2.0669 0.06833 0.06376 -0.1227 0.1251 1.0000
18.000 2.0577 0.07281 0.06828 -0.1229 0.1219 1.0000
18.250 2.0542 0.07658 0.07215 -0.1231 0.1196 1.0000
18.500 2.0512 0.08036 0.07600 -0.1234 0.1170 1.0000
18.750 2.0439 0.08479 0.08050 -0.1239 0.1142 1.0000
19.000 2.0318 0.08998 0.08576 -0.1248 0.1113 1.0000
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Polar data table (+)
Polar graphs
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