E591 (e591-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E591 (e591-il) Reynolds number: 500,000 Max Cl/Cd: 107.29 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e591-il-500000.txt Download as CSV file: xf-e591-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.1307 0.05399 0.05145 -0.1207 0.9447 0.0229
-8.750 -0.1366 0.04578 0.04312 -0.1306 0.9370 0.0219
-8.500 -0.1341 0.03223 0.02902 -0.1576 0.9220 0.0213
-8.250 -0.1107 0.02616 0.02235 -0.1677 0.9102 0.0212
-8.000 -0.0640 0.02196 0.01760 -0.1766 0.9066 0.0212
-7.750 -0.0312 0.01994 0.01526 -0.1796 0.8964 0.0216
-7.500 0.0168 0.01815 0.01313 -0.1850 0.8909 0.0221
-7.250 0.0514 0.01709 0.01183 -0.1871 0.8798 0.0225
-7.000 0.0903 0.01575 0.01038 -0.1900 0.8706 0.0232
-6.750 0.1226 0.01508 0.00964 -0.1912 0.8582 0.0237
-6.500 0.1541 0.01450 0.00895 -0.1922 0.8456 0.0245
-6.250 0.1865 0.01396 0.00826 -0.1933 0.8335 0.0254
-6.000 0.2160 0.01346 0.00762 -0.1937 0.8201 0.0264
-5.750 0.2442 0.01295 0.00709 -0.1940 0.8068 0.0276
-5.500 0.2735 0.01263 0.00667 -0.1943 0.7940 0.0291
-5.250 0.3024 0.01222 0.00614 -0.1946 0.7808 0.0304
-5.000 0.3307 0.01182 0.00571 -0.1948 0.7677 0.0322
-4.750 0.3593 0.01159 0.00535 -0.1949 0.7549 0.0342
-4.500 0.3885 0.01121 0.00492 -0.1953 0.7420 0.0370
-4.250 0.4171 0.01093 0.00458 -0.1955 0.7292 0.0407
-4.000 0.4458 0.01072 0.00429 -0.1956 0.7169 0.0457
-3.750 0.4744 0.01052 0.00404 -0.1957 0.7042 0.0523
-3.500 0.5034 0.01029 0.00379 -0.1959 0.6920 0.0644
-3.250 0.5335 0.00992 0.00353 -0.1966 0.6800 0.1123
-3.000 0.5633 0.00957 0.00341 -0.1973 0.6677 0.1900
-2.750 0.5915 0.00951 0.00339 -0.1973 0.6561 0.2329
-2.500 0.6189 0.00953 0.00339 -0.1971 0.6441 0.2600
-2.250 0.6465 0.00955 0.00339 -0.1968 0.6328 0.2809
-2.000 0.6735 0.00965 0.00341 -0.1965 0.6215 0.2981
-1.750 0.7008 0.00969 0.00343 -0.1962 0.6101 0.3136
-1.500 0.7280 0.00978 0.00348 -0.1959 0.5996 0.3300
-1.250 0.7550 0.00986 0.00352 -0.1956 0.5886 0.3461
-1.000 0.7820 0.00996 0.00357 -0.1952 0.5784 0.3602
-0.750 0.8087 0.01007 0.00363 -0.1948 0.5680 0.3749
-0.500 0.8359 0.01014 0.00369 -0.1945 0.5583 0.3872
-0.250 0.8624 0.01027 0.00374 -0.1941 0.5482 0.3984
0.000 0.8896 0.01034 0.00380 -0.1938 0.5390 0.4092
0.250 0.9160 0.01048 0.00387 -0.1934 0.5296 0.4206
0.500 0.9430 0.01056 0.00396 -0.1931 0.5208 0.4323
0.750 0.9693 0.01070 0.00403 -0.1927 0.5116 0.4442
1.000 0.9960 0.01080 0.00414 -0.1924 0.5035 0.4576
1.250 1.0226 0.01092 0.00424 -0.1920 0.4949 0.4707
1.750 1.0752 0.01117 0.00449 -0.1912 0.4788 0.5009
2.000 1.1006 0.01135 0.00463 -0.1907 0.4709 0.5167
2.250 1.1273 0.01145 0.00477 -0.1903 0.4636 0.5344
2.500 1.1529 0.01160 0.00492 -0.1898 0.4558 0.5533
2.750 1.1784 0.01177 0.00509 -0.1893 0.4489 0.5731
3.000 1.2044 0.01189 0.00525 -0.1889 0.4416 0.5952
3.250 1.2288 0.01209 0.00545 -0.1882 0.4343 0.6188
3.500 1.2545 0.01222 0.00564 -0.1877 0.4278 0.6440
3.750 1.2794 0.01237 0.00583 -0.1871 0.4208 0.6718
4.000 1.3025 0.01260 0.00607 -0.1862 0.4139 0.7029
4.250 1.3271 0.01268 0.00627 -0.1855 0.4076 0.7377
4.500 1.3491 0.01283 0.00648 -0.1843 0.4010 0.7791
4.750 1.3680 0.01298 0.00672 -0.1824 0.3948 0.8361
5.000 1.3798 0.01286 0.00679 -0.1789 0.3893 1.0000
5.250 1.4027 0.01313 0.00701 -0.1780 0.3828 1.0000
5.500 1.4247 0.01345 0.00726 -0.1770 0.3766 1.0000
5.750 1.4485 0.01367 0.00748 -0.1762 0.3705 1.0000
6.000 1.4701 0.01397 0.00774 -0.1752 0.3640 1.0000
6.250 1.4915 0.01430 0.00804 -0.1740 0.3582 1.0000
6.500 1.5140 0.01456 0.00830 -0.1731 0.3521 1.0000
6.750 1.5341 0.01492 0.00861 -0.1718 0.3459 1.0000
7.000 1.5547 0.01527 0.00895 -0.1706 0.3402 1.0000
7.250 1.5763 0.01556 0.00926 -0.1696 0.3344 1.0000
7.500 1.5952 0.01598 0.00963 -0.1681 0.3284 1.0000
7.750 1.6145 0.01638 0.01003 -0.1667 0.3229 1.0000
8.000 1.6350 0.01673 0.01040 -0.1656 0.3174 1.0000
8.250 1.6527 0.01720 0.01084 -0.1640 0.3117 1.0000
8.500 1.6704 0.01768 0.01132 -0.1625 0.3064 1.0000
8.750 1.6898 0.01808 0.01175 -0.1612 0.3010 1.0000
9.000 1.7064 0.01862 0.01228 -0.1596 0.2956 1.0000
9.250 1.7219 0.01923 0.01288 -0.1578 0.2904 1.0000
9.500 1.7405 0.01968 0.01338 -0.1565 0.2853 1.0000
9.750 1.7560 0.02029 0.01399 -0.1548 0.2801 1.0000
10.000 1.7685 0.02110 0.01476 -0.1528 0.2749 1.0000
10.250 1.7864 0.02160 0.01535 -0.1515 0.2704 1.0000
10.500 1.8013 0.02229 0.01606 -0.1499 0.2653 1.0000
10.750 1.8124 0.02321 0.01696 -0.1479 0.2603 1.0000
11.000 1.8273 0.02394 0.01774 -0.1464 0.2559 1.0000
11.250 1.8414 0.02473 0.01858 -0.1448 0.2511 1.0000
11.500 1.8519 0.02576 0.01960 -0.1430 0.2463 1.0000
11.750 1.8624 0.02684 0.02070 -0.1412 0.2418 1.0000
12.000 1.8761 0.02772 0.02166 -0.1398 0.2374 1.0000
12.250 1.8863 0.02887 0.02283 -0.1381 0.2327 1.0000
12.500 1.8923 0.03036 0.02432 -0.1361 0.2282 1.0000
12.750 1.9048 0.03142 0.02547 -0.1349 0.2243 1.0000
13.000 1.9148 0.03270 0.02680 -0.1335 0.2199 1.0000
13.250 1.9207 0.03434 0.02845 -0.1318 0.2156 1.0000
13.500 1.9265 0.03606 0.03021 -0.1303 0.2116 1.0000
13.750 1.9369 0.03743 0.03168 -0.1292 0.2076 1.0000
14.000 1.9431 0.03922 0.03350 -0.1279 0.2034 1.0000
14.250 1.9448 0.04148 0.03577 -0.1265 0.1993 1.0000
14.500 1.9516 0.04332 0.03770 -0.1255 0.1957 1.0000
14.750 1.9584 0.04522 0.03968 -0.1246 0.1918 1.0000
15.000 1.9608 0.04761 0.04211 -0.1236 0.1879 1.0000
15.250 1.9586 0.05055 0.04506 -0.1226 0.1840 1.0000
15.500 1.9657 0.05259 0.04722 -0.1221 0.1808 1.0000
15.750 1.9691 0.05508 0.04979 -0.1215 0.1770 1.0000
16.000 1.9680 0.05813 0.05288 -0.1210 0.1734 1.0000
16.250 1.9646 0.06154 0.05632 -0.1205 0.1698 1.0000
16.500 1.9688 0.06412 0.05903 -0.1203 0.1666 1.0000
16.750 1.9690 0.06724 0.06222 -0.1201 0.1630 1.0000
17.000 1.9648 0.07097 0.06599 -0.1201 0.1596 1.0000
17.250 1.9604 0.07480 0.06987 -0.1202 0.1562 1.0000
17.500 1.9616 0.07798 0.07318 -0.1204 0.1531 1.0000
17.750 1.9591 0.08168 0.07696 -0.1208 0.1498 1.0000
18.000 1.9523 0.08603 0.08134 -0.1213 0.1465 1.0000
18.250 1.9473 0.09018 0.08556 -0.1219 0.1433 1.0000
18.500 1.9463 0.09384 0.08935 -0.1226 0.1403 1.0000
18.750 1.9417 0.09802 0.09359 -0.1234 0.1370 1.0000
19.000 1.9331 0.10281 0.09841 -0.1245 0.1339 1.0000
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Polar data table (+)
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