E591 (e591-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E591 (e591-il) Reynolds number: 100,000 Max Cl/Cd: 57.24 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e591-il-100000-n5.txt Download as CSV file: xf-e591-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.0720 0.09532 0.09039 -0.0790 0.9388 0.0369
-8.250 -0.0661 0.09104 0.08613 -0.0820 0.9299 0.0373
-8.000 -0.0564 0.08613 0.08122 -0.0863 0.9235 0.0369
-7.750 -0.0548 0.08156 0.07668 -0.0891 0.9128 0.0365
-7.500 -0.0532 0.07463 0.06975 -0.0951 0.9064 0.0357
-7.250 -0.1163 0.05844 0.05346 -0.1063 0.8849 0.0338
-7.000 -0.1139 0.04288 0.03710 -0.1334 0.8724 0.0334
-6.750 -0.0951 0.03784 0.03147 -0.1400 0.8602 0.0336
-6.500 -0.0534 0.03326 0.02617 -0.1477 0.8559 0.0344
-6.250 -0.0256 0.03153 0.02429 -0.1492 0.8469 0.0352
-6.000 0.0118 0.02971 0.02225 -0.1523 0.8406 0.0367
-5.750 0.0576 0.02757 0.01968 -0.1568 0.8366 0.0392
-5.500 0.0848 0.02658 0.01866 -0.1573 0.8261 0.0410
-5.250 0.1269 0.02509 0.01693 -0.1603 0.8202 0.0431
-5.000 0.1630 0.02397 0.01572 -0.1621 0.8121 0.0452
-4.750 0.1993 0.02307 0.01470 -0.1639 0.8032 0.0488
-4.500 0.2408 0.02214 0.01373 -0.1667 0.7961 0.0533
-4.250 0.2730 0.02144 0.01297 -0.1678 0.7851 0.0577
-4.000 0.3155 0.02063 0.01207 -0.1708 0.7772 0.0656
-3.750 0.3483 0.02002 0.01141 -0.1720 0.7658 0.0749
-3.500 0.3897 0.01922 0.01059 -0.1750 0.7566 0.0931
-3.250 0.4256 0.01848 0.00999 -0.1771 0.7453 0.1330
-3.000 0.4626 0.01798 0.00967 -0.1791 0.7350 0.2043
-2.750 0.4961 0.01785 0.00953 -0.1802 0.7238 0.2554
-2.500 0.5271 0.01788 0.00951 -0.1807 0.7125 0.2958
-2.250 0.5603 0.01794 0.00952 -0.1814 0.7021 0.3282
-2.000 0.5881 0.01803 0.00954 -0.1812 0.6901 0.3503
-1.750 0.6199 0.01807 0.00944 -0.1816 0.6801 0.3705
-1.500 0.6469 0.01814 0.00944 -0.1813 0.6684 0.3869
-1.250 0.6769 0.01818 0.00933 -0.1814 0.6580 0.4023
-1.000 0.7045 0.01823 0.00932 -0.1812 0.6470 0.4153
-0.750 0.7327 0.01829 0.00929 -0.1810 0.6367 0.4281
-0.500 0.7613 0.01837 0.00923 -0.1810 0.6263 0.4423
-0.250 0.7880 0.01845 0.00930 -0.1806 0.6160 0.4544
0.000 0.8163 0.01855 0.00929 -0.1805 0.6063 0.4682
0.250 0.8430 0.01868 0.00936 -0.1801 0.5962 0.4824
0.500 0.8704 0.01879 0.00941 -0.1798 0.5868 0.4963
0.750 0.8966 0.01894 0.00953 -0.1794 0.5772 0.5111
1.000 0.9239 0.01909 0.00960 -0.1791 0.5680 0.5274
1.250 0.9498 0.01925 0.00975 -0.1786 0.5588 0.5436
1.500 0.9757 0.01942 0.00989 -0.1781 0.5499 0.5605
1.750 1.0017 0.01961 0.01005 -0.1776 0.5415 0.5788
2.000 1.0265 0.01980 0.01025 -0.1769 0.5325 0.5983
2.250 1.0528 0.02000 0.01039 -0.1765 0.5248 0.6196
2.500 1.0762 0.02022 0.01066 -0.1756 0.5159 0.6426
2.750 1.1018 0.02042 0.01081 -0.1750 0.5085 0.6680
3.000 1.1238 0.02064 0.01112 -0.1738 0.5001 0.6950
3.250 1.1464 0.02084 0.01134 -0.1726 0.4925 0.7270
3.500 1.1678 0.02103 0.01155 -0.1712 0.4855 0.7642
3.750 1.1845 0.02116 0.01181 -0.1689 0.4777 0.8116
4.000 1.1960 0.02109 0.01181 -0.1653 0.4716 0.9271
4.250 1.2217 0.02144 0.01210 -0.1651 0.4639 1.0000
4.500 1.2468 0.02184 0.01243 -0.1648 0.4563 1.0000
4.750 1.2731 0.02224 0.01270 -0.1647 0.4498 1.0000
5.000 1.2955 0.02268 0.01316 -0.1639 0.4420 1.0000
5.250 1.3198 0.02310 0.01348 -0.1634 0.4353 1.0000
5.500 1.3429 0.02355 0.01389 -0.1627 0.4285 1.0000
5.750 1.3644 0.02402 0.01437 -0.1618 0.4212 1.0000
6.000 1.3881 0.02446 0.01471 -0.1612 0.4152 1.0000
6.250 1.4081 0.02498 0.01526 -0.1600 0.4083 1.0000
6.500 1.4278 0.02547 0.01577 -0.1588 0.4015 1.0000
6.750 1.4509 0.02594 0.01613 -0.1581 0.3960 1.0000
7.000 1.4666 0.02653 0.01680 -0.1563 0.3891 1.0000
7.250 1.4844 0.02707 0.01735 -0.1548 0.3827 1.0000
7.500 1.5057 0.02759 0.01779 -0.1539 0.3773 1.0000
7.750 1.5196 0.02827 0.01859 -0.1519 0.3707 1.0000
8.000 1.5359 0.02890 0.01923 -0.1502 0.3647 1.0000
8.250 1.5555 0.02947 0.01973 -0.1491 0.3595 1.0000
8.500 1.5673 0.03028 0.02068 -0.1470 0.3531 1.0000
8.750 1.5816 0.03101 0.02144 -0.1452 0.3473 1.0000
9.000 1.6003 0.03163 0.02199 -0.1440 0.3424 1.0000
9.250 1.6094 0.03261 0.02314 -0.1417 0.3362 1.0000
9.500 1.6215 0.03349 0.02408 -0.1398 0.3306 1.0000
9.750 1.6380 0.03423 0.02476 -0.1385 0.3258 1.0000
10.000 1.6461 0.03537 0.02605 -0.1363 0.3202 1.0000
10.250 1.6553 0.03648 0.02725 -0.1343 0.3146 1.0000
10.500 1.6689 0.03740 0.02816 -0.1328 0.3099 1.0000
10.750 1.6775 0.03865 0.02950 -0.1310 0.3048 1.0000
11.000 1.6834 0.04008 0.03106 -0.1289 0.2993 1.0000
11.250 1.6931 0.04130 0.03232 -0.1273 0.2945 1.0000
11.500 1.7043 0.04250 0.03354 -0.1260 0.2900 1.0000
11.750 1.7055 0.04442 0.03564 -0.1239 0.2848 1.0000
12.000 1.7110 0.04606 0.03737 -0.1223 0.2799 1.0000
12.250 1.7235 0.04723 0.03852 -0.1212 0.2756 1.0000
12.500 1.7222 0.04957 0.04104 -0.1195 0.2708 1.0000
12.750 1.7225 0.05185 0.04347 -0.1181 0.2659 1.0000
13.000 1.7289 0.05362 0.04528 -0.1169 0.2615 1.0000
13.250 1.7355 0.05546 0.04717 -0.1159 0.2573 1.0000
13.500 1.7277 0.05877 0.05070 -0.1147 0.2525 1.0000
13.750 1.7276 0.06140 0.05344 -0.1138 0.2480 1.0000
14.000 1.7377 0.06297 0.05500 -0.1132 0.2441 1.0000
14.250 1.7297 0.06668 0.05890 -0.1125 0.2396 1.0000
14.500 1.7198 0.07075 0.06317 -0.1122 0.2349 1.0000
14.750 1.7216 0.07346 0.06596 -0.1118 0.2308 1.0000
15.000 1.7333 0.07495 0.06743 -0.1114 0.2272 1.0000
15.250 1.7072 0.08156 0.07434 -0.1120 0.2224 1.0000
15.500 1.6971 0.08618 0.07911 -0.1125 0.2179 1.0000
15.750 1.7058 0.08812 0.08107 -0.1124 0.2143 1.0000
16.000 1.6957 0.09294 0.08603 -0.1132 0.2103 1.0000
16.250 1.6609 0.10180 0.09517 -0.1157 0.2052 1.0000
16.500 1.6610 0.10520 0.09864 -0.1164 0.2013 1.0000
16.750 1.6859 0.10453 0.09792 -0.1155 0.1983 1.0000
17.000 1.5893 0.12480 0.11865 -0.1241 0.1906 1.0000
17.250 1.5953 0.12733 0.12123 -0.1248 0.1871 1.0000
17.500 1.6268 0.12519 0.11907 -0.1232 0.1850 1.0000
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