E591 (e591-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E591 (e591-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.72 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e591-il-1000000-n5.txt Download as CSV file: xf-e591-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.4445 0.06857 0.06594 -0.1090 0.9843 0.0096
-13.250 -0.4669 0.06125 0.05849 -0.1141 0.9805 0.0095
-13.000 -0.4889 0.05338 0.05049 -0.1213 0.9760 0.0095
-12.750 -0.5014 0.04615 0.04311 -0.1295 0.9725 0.0095
-12.250 -0.5359 0.03627 0.03304 -0.1356 0.9507 0.0095
-12.000 -0.5387 0.03124 0.02787 -0.1411 0.9389 0.0096
-11.750 -0.5181 0.02642 0.02288 -0.1504 0.9308 0.0097
-11.500 -0.4781 0.02243 0.01871 -0.1617 0.9249 0.0098
-11.250 -0.4340 0.02007 0.01618 -0.1700 0.9197 0.0100
-11.000 -0.3909 0.01873 0.01471 -0.1755 0.9128 0.0101
-10.750 -0.3399 0.01751 0.01336 -0.1822 0.9068 0.0103
-10.500 -0.2955 0.01659 0.01230 -0.1870 0.8960 0.0105
-10.250 -0.2567 0.01586 0.01144 -0.1903 0.8825 0.0105
-10.000 -0.2248 0.01498 0.01040 -0.1925 0.8657 0.0108
-9.750 -0.1966 0.01432 0.00961 -0.1935 0.8492 0.0110
-9.500 -0.1699 0.01384 0.00900 -0.1939 0.8327 0.0112
-9.250 -0.1440 0.01342 0.00845 -0.1940 0.8166 0.0114
-9.000 -0.1178 0.01304 0.00798 -0.1940 0.8014 0.0115
-8.750 -0.0915 0.01272 0.00757 -0.1940 0.7868 0.0118
-8.500 -0.0652 0.01241 0.00715 -0.1939 0.7728 0.0120
-8.250 -0.0389 0.01214 0.00677 -0.1938 0.7589 0.0122
-8.000 -0.0116 0.01184 0.00639 -0.1938 0.7456 0.0125
-7.750 0.0156 0.01159 0.00605 -0.1938 0.7331 0.0127
-7.500 0.0425 0.01138 0.00573 -0.1936 0.7197 0.0130
-7.250 0.0705 0.01115 0.00542 -0.1937 0.7077 0.0132
-7.000 0.0984 0.01089 0.00508 -0.1938 0.6962 0.0136
-6.750 0.1262 0.01069 0.00480 -0.1938 0.6833 0.0140
-6.500 0.1545 0.01051 0.00456 -0.1939 0.6718 0.0146
-6.250 0.1823 0.01038 0.00435 -0.1938 0.6603 0.0151
-6.000 0.2108 0.01023 0.00414 -0.1939 0.6484 0.0157
-5.750 0.2391 0.01011 0.00394 -0.1939 0.6373 0.0163
-5.500 0.2673 0.00999 0.00377 -0.1939 0.6254 0.0173
-5.250 0.2959 0.00989 0.00361 -0.1940 0.6147 0.0184
-5.000 0.3240 0.00982 0.00347 -0.1939 0.6031 0.0195
-4.750 0.3529 0.00972 0.00333 -0.1940 0.5926 0.0210
-4.500 0.3811 0.00967 0.00322 -0.1940 0.5818 0.0224
-4.250 0.4098 0.00960 0.00310 -0.1940 0.5708 0.0242
-4.000 0.4382 0.00956 0.00300 -0.1940 0.5612 0.0261
-3.750 0.4669 0.00950 0.00291 -0.1941 0.5508 0.0284
-3.500 0.4954 0.00947 0.00283 -0.1941 0.5411 0.0313
-3.250 0.5240 0.00943 0.00275 -0.1941 0.5311 0.0351
-3.000 0.5527 0.00939 0.00269 -0.1942 0.5223 0.0412
-2.750 0.5816 0.00934 0.00263 -0.1943 0.5123 0.0524
-2.500 0.6106 0.00927 0.00257 -0.1945 0.5038 0.0717
-2.250 0.6401 0.00915 0.00252 -0.1949 0.4948 0.1016
-2.000 0.6698 0.00902 0.00248 -0.1953 0.4861 0.1487
-1.750 0.6991 0.00896 0.00248 -0.1956 0.4778 0.1820
-1.500 0.7274 0.00897 0.00250 -0.1956 0.4695 0.2074
-1.250 0.7563 0.00896 0.00252 -0.1957 0.4621 0.2310
-1.000 0.7843 0.00901 0.00257 -0.1957 0.4536 0.2534
-0.750 0.8126 0.00904 0.00262 -0.1956 0.4469 0.2725
-0.500 0.8407 0.00909 0.00267 -0.1956 0.4394 0.2901
-0.250 0.8682 0.00918 0.00275 -0.1954 0.4316 0.3091
0.000 0.8961 0.00924 0.00280 -0.1953 0.4255 0.3189
0.250 0.9236 0.00933 0.00287 -0.1951 0.4183 0.3289
0.500 0.9507 0.00944 0.00294 -0.1948 0.4117 0.3362
0.750 0.9783 0.00952 0.00301 -0.1946 0.4052 0.3456
1.000 1.0052 0.00964 0.00311 -0.1943 0.3984 0.3546
1.250 1.0323 0.00975 0.00319 -0.1941 0.3926 0.3622
1.500 1.0594 0.00985 0.00329 -0.1938 0.3859 0.3727
1.750 1.0857 0.00999 0.00340 -0.1934 0.3793 0.3813
2.000 1.1127 0.01009 0.00350 -0.1932 0.3739 0.3916
2.500 1.1651 0.01037 0.00375 -0.1924 0.3606 0.4131
2.750 1.1916 0.01048 0.00386 -0.1921 0.3558 0.4234
3.000 1.2178 0.01061 0.00400 -0.1917 0.3494 0.4368
3.250 1.2429 0.01079 0.00416 -0.1911 0.3424 0.4483
3.500 1.2688 0.01091 0.00429 -0.1907 0.3375 0.4615
3.750 1.2938 0.01106 0.00445 -0.1901 0.3312 0.4762
4.000 1.3177 0.01125 0.00462 -0.1893 0.3247 0.4898
4.250 1.3424 0.01138 0.00478 -0.1886 0.3198 0.5042
4.500 1.3664 0.01155 0.00496 -0.1879 0.3139 0.5216
4.750 1.3897 0.01176 0.00517 -0.1870 0.3077 0.5384
5.000 1.4139 0.01191 0.00536 -0.1863 0.3027 0.5548
5.250 1.4372 0.01211 0.00557 -0.1854 0.2970 0.5735
5.500 1.4598 0.01235 0.00581 -0.1845 0.2911 0.5950
5.750 1.4835 0.01252 0.00603 -0.1837 0.2862 0.6164
6.000 1.5064 0.01274 0.00628 -0.1828 0.2808 0.6378
6.250 1.5283 0.01300 0.00656 -0.1818 0.2750 0.6643
6.500 1.5517 0.01319 0.00681 -0.1810 0.2704 0.6942
7.000 1.5947 0.01369 0.00742 -0.1788 0.2600 0.7627
7.250 1.6163 0.01388 0.00772 -0.1777 0.2558 0.8184
7.500 1.6294 0.01390 0.00796 -0.1748 0.2511 1.0000
7.750 1.6495 0.01426 0.00829 -0.1735 0.2460 1.0000
8.000 1.6695 0.01460 0.00863 -0.1722 0.2417 1.0000
8.250 1.6898 0.01493 0.00895 -0.1710 0.2372 1.0000
8.500 1.7089 0.01533 0.00934 -0.1696 0.2321 1.0000
8.750 1.7272 0.01576 0.00975 -0.1681 0.2274 1.0000
9.000 1.7466 0.01613 0.01013 -0.1668 0.2237 1.0000
9.250 1.7649 0.01656 0.01057 -0.1654 0.2190 1.0000
9.500 1.7814 0.01710 0.01108 -0.1637 0.2139 1.0000
9.750 1.7991 0.01755 0.01155 -0.1623 0.2103 1.0000
10.000 1.8166 0.01804 0.01205 -0.1608 0.2061 1.0000
10.250 1.8317 0.01865 0.01266 -0.1590 0.2013 1.0000
10.500 1.8470 0.01927 0.01328 -0.1573 0.1971 1.0000
10.750 1.8629 0.01985 0.01388 -0.1557 0.1934 1.0000
11.000 1.8775 0.02053 0.01457 -0.1540 0.1890 1.0000
11.250 1.8899 0.02135 0.01538 -0.1521 0.1846 1.0000
11.500 1.9047 0.02205 0.01611 -0.1506 0.1814 1.0000
11.750 1.9180 0.02284 0.01693 -0.1489 0.1776 1.0000
12.000 1.9296 0.02378 0.01787 -0.1471 0.1734 1.0000
12.250 1.9403 0.02479 0.01890 -0.1452 0.1697 1.0000
12.500 1.9531 0.02570 0.01985 -0.1437 0.1666 1.0000
12.750 1.9639 0.02677 0.02094 -0.1420 0.1628 1.0000
13.000 1.9720 0.02806 0.02225 -0.1402 0.1589 1.0000
13.250 1.9817 0.02929 0.02351 -0.1386 0.1556 1.0000
13.500 1.9916 0.03054 0.02480 -0.1371 0.1524 1.0000
13.750 1.9993 0.03200 0.02630 -0.1356 0.1490 1.0000
14.000 2.0049 0.03370 0.02802 -0.1339 0.1453 1.0000
14.250 2.0130 0.03523 0.02960 -0.1326 0.1425 1.0000
14.500 2.0199 0.03692 0.03133 -0.1313 0.1395 1.0000
14.750 2.0245 0.03888 0.03333 -0.1300 0.1361 1.0000
15.000 2.0268 0.04113 0.03561 -0.1287 0.1326 1.0000
15.250 2.0328 0.04307 0.03761 -0.1277 0.1301 1.0000
15.500 2.0364 0.04532 0.03991 -0.1268 0.1270 1.0000
15.750 2.0371 0.04796 0.04259 -0.1258 0.1238 1.0000
16.000 2.0366 0.05081 0.04550 -0.1250 0.1206 1.0000
16.250 2.0398 0.05332 0.04807 -0.1244 0.1182 1.0000
16.500 2.0401 0.05620 0.05102 -0.1239 0.1153 1.0000
16.750 2.0367 0.05964 0.05450 -0.1235 0.1122 1.0000
17.000 2.0335 0.06316 0.05809 -0.1232 0.1094 1.0000
17.250 2.0322 0.06651 0.06151 -0.1231 0.1068 1.0000
17.500 2.0279 0.07030 0.06537 -0.1231 0.1039 1.0000
17.750 2.0202 0.07466 0.06978 -0.1233 0.1010 1.0000
18.000 2.0159 0.07861 0.07381 -0.1236 0.0987 1.0000
18.250 2.0119 0.08260 0.07788 -0.1240 0.0964 1.0000
18.500 2.0042 0.08716 0.08251 -0.1247 0.0938 1.0000
18.750 1.9936 0.09225 0.08767 -0.1256 0.0913 1.0000
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Polar data table (+)
Polar graphs
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