EH 2.0/12 (eh2012-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 2.0/12 (eh2012-il) Reynolds number: 50,000 Max Cl/Cd: 18.04 at α=12.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh2012-il-50000.txt Download as CSV file: xf-eh2012-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EH 2.0/12
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4648 0.10744 0.10090 0.0070 1.0000 0.2958
-9.000 -0.4676 0.10462 0.09816 0.0069 1.0000 0.3121
-8.750 -0.4756 0.10214 0.09577 0.0068 1.0000 0.3281
-8.500 -0.4408 0.09674 0.09029 0.0087 1.0000 0.3493
-8.250 -0.4359 0.09355 0.08716 0.0093 1.0000 0.3684
-7.750 -0.4172 0.08715 0.08083 0.0122 1.0000 0.4227
-7.500 -0.4215 0.08497 0.07875 0.0138 1.0000 0.4488
-7.250 -0.5860 0.06130 0.05455 -0.0214 1.0000 0.1498
-7.000 -0.5776 0.05698 0.05009 -0.0206 1.0000 0.1465
-6.750 -0.5727 0.05288 0.04576 -0.0193 1.0000 0.1449
-6.500 -0.5671 0.04891 0.04149 -0.0176 1.0000 0.1432
-6.250 -0.5606 0.04516 0.03736 -0.0156 1.0000 0.1414
-6.000 -0.5524 0.04208 0.03391 -0.0132 1.0000 0.1436
-5.750 -0.5452 0.03945 0.03073 -0.0104 1.0000 0.1477
-5.500 -0.5327 0.03684 0.02802 -0.0083 1.0000 0.1527
-5.250 -0.5213 0.03484 0.02577 -0.0058 1.0000 0.1594
-5.000 -0.5106 0.03299 0.02370 -0.0034 1.0000 0.1682
-4.750 -0.4990 0.03137 0.02176 -0.0009 1.0000 0.1767
-4.500 -0.4872 0.02998 0.02034 0.0012 1.0000 0.1889
-4.250 -0.4737 0.02863 0.01889 0.0031 1.0000 0.2011
-4.000 -0.4598 0.02752 0.01771 0.0048 1.0000 0.2172
-3.750 -0.4438 0.02650 0.01661 0.0063 1.0000 0.2360
-3.500 -0.4257 0.02553 0.01575 0.0073 1.0000 0.2596
-3.250 -0.4063 0.02464 0.01500 0.0081 1.0000 0.2915
-3.000 -0.0258 0.02219 0.01417 -0.0343 1.0000 1.0000
-2.750 -0.0544 0.02301 0.01503 -0.0288 1.0000 1.0000
-2.500 -0.0812 0.02374 0.01576 -0.0236 1.0000 1.0000
-2.250 -0.0366 0.02395 0.01570 -0.0299 0.9843 1.0000
-2.000 0.0374 0.02385 0.01524 -0.0403 0.9612 1.0000
-1.750 0.1171 0.02355 0.01465 -0.0511 0.9418 1.0000
-1.500 0.1792 0.02328 0.01415 -0.0583 0.9199 1.0000
-1.250 0.2320 0.02304 0.01374 -0.0634 0.8986 1.0000
-1.000 0.2658 0.02308 0.01363 -0.0650 0.8764 1.0000
-0.750 0.2929 0.02323 0.01365 -0.0651 0.8556 1.0000
-0.500 0.3167 0.02341 0.01372 -0.0644 0.8370 1.0000
-0.250 0.3346 0.02381 0.01403 -0.0630 0.8178 1.0000
0.000 0.3533 0.02420 0.01433 -0.0617 0.8002 1.0000
0.250 0.3714 0.02460 0.01466 -0.0602 0.7837 1.0000
0.500 0.3890 0.02505 0.01505 -0.0587 0.7682 1.0000
0.750 0.4061 0.02554 0.01548 -0.0570 0.7532 1.0000
1.000 0.4228 0.02609 0.01599 -0.0554 0.7389 1.0000
1.250 0.4393 0.02668 0.01653 -0.0537 0.7252 1.0000
1.500 0.4559 0.02727 0.01709 -0.0520 0.7121 1.0000
1.750 0.4735 0.02781 0.01759 -0.0502 0.7000 1.0000
2.000 0.4904 0.02841 0.01817 -0.0484 0.6877 1.0000
2.250 0.5043 0.02931 0.01908 -0.0469 0.6747 1.0000
2.500 0.5179 0.03026 0.02003 -0.0452 0.6623 1.0000
2.750 0.5320 0.03115 0.02095 -0.0434 0.6506 1.0000
3.000 0.5502 0.03175 0.02152 -0.0415 0.6404 1.0000
3.250 0.5636 0.03276 0.02256 -0.0398 0.6289 1.0000
3.500 0.5727 0.03411 0.02395 -0.0380 0.6170 1.0000
3.750 0.5842 0.03533 0.02519 -0.0361 0.6064 1.0000
4.000 0.6069 0.03570 0.02557 -0.0344 0.5973 1.0000
4.250 0.6091 0.03764 0.02758 -0.0324 0.5855 1.0000
4.500 0.6138 0.03945 0.02943 -0.0305 0.5749 1.0000
4.750 0.6381 0.03986 0.02984 -0.0289 0.5661 1.0000
5.000 0.6369 0.04215 0.03219 -0.0270 0.5551 1.0000
5.250 0.6322 0.04476 0.03483 -0.0250 0.5448 1.0000
5.500 0.6592 0.04513 0.03526 -0.0235 0.5361 1.0000
5.750 0.6459 0.04851 0.03867 -0.0217 0.5258 1.0000
6.000 0.6351 0.05178 0.04194 -0.0201 0.5166 1.0000
6.250 0.6824 0.05083 0.04111 -0.0190 0.5076 1.0000
6.500 0.6179 0.05800 0.04814 -0.0173 0.5002 1.0000
6.750 0.6438 0.05904 0.04927 -0.0165 0.4908 1.0000
7.000 0.6082 0.06391 0.05405 -0.0152 0.4854 1.0000
7.250 0.6335 0.06524 0.05548 -0.0145 0.4764 1.0000
7.500 0.6062 0.06992 0.06010 -0.0143 0.4723 1.0000
7.750 0.6342 0.07117 0.06149 -0.0136 0.4620 1.0000
8.000 0.6130 0.07583 0.06612 -0.0140 0.4601 1.0000
8.250 0.6024 0.07985 0.07015 -0.0145 0.4585 1.0000
8.500 0.5974 0.08383 0.07416 -0.0153 0.4590 1.0000
8.750 0.6047 0.08783 0.07824 -0.0164 0.4621 1.0000
12.250 1.0702 0.05931 0.05232 0.0276 0.1894 1.0000
12.500 1.0367 0.06606 0.05918 0.0262 0.1885 1.0000
13.000 1.0618 0.06487 0.05736 0.0311 0.1337 1.0000
13.250 1.0336 0.07149 0.06423 0.0288 0.1332 1.0000
13.500 1.0043 0.07916 0.07208 0.0255 0.1338 1.0000
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Polar data table (+)
Polar graphs
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