EPPLER 361 AIRFOIL (e361-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 361 AIRFOIL (e361-il) Reynolds number: 100,000 Max Cl/Cd: 46.32 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e361-il-100000-n5.txt Download as CSV file: xf-e361-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 361 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5376 0.08279 0.07770 -0.0298 1.0000 0.0200
-10.000 -0.5436 0.07737 0.07228 -0.0335 1.0000 0.0198
-9.750 -0.5563 0.07189 0.06678 -0.0370 1.0000 0.0196
-9.500 -0.5729 0.06707 0.06188 -0.0389 1.0000 0.0195
-9.250 -0.5904 0.06303 0.05775 -0.0389 1.0000 0.0193
-9.000 -0.6090 0.05943 0.05403 -0.0369 1.0000 0.0193
-8.750 -0.6206 0.05612 0.05056 -0.0347 1.0000 0.0191
-8.500 -0.6304 0.05239 0.04661 -0.0323 1.0000 0.0190
-8.250 -0.6351 0.04896 0.04292 -0.0298 1.0000 0.0189
-8.000 -0.6359 0.04578 0.03946 -0.0272 1.0000 0.0187
-7.750 -0.6363 0.04238 0.03568 -0.0242 1.0000 0.0189
-7.500 -0.6330 0.03937 0.03227 -0.0211 1.0000 0.0193
-7.250 -0.6276 0.03658 0.02903 -0.0180 1.0000 0.0197
-7.000 -0.6190 0.03453 0.02670 -0.0153 1.0000 0.0204
-6.750 -0.6077 0.03329 0.02542 -0.0131 1.0000 0.0212
-6.500 -0.5885 0.03143 0.02330 -0.0123 0.9943 0.0220
-6.250 -0.5547 0.02894 0.02041 -0.0139 0.9805 0.0228
-6.000 -0.5198 0.02661 0.01769 -0.0152 0.9666 0.0238
-5.750 -0.4844 0.02476 0.01562 -0.0167 0.9523 0.0248
-5.500 -0.4494 0.02342 0.01422 -0.0185 0.9376 0.0264
-5.250 -0.4142 0.02221 0.01284 -0.0199 0.9230 0.0296
-5.000 -0.3820 0.02114 0.01176 -0.0210 0.9076 0.0336
-4.750 -0.3529 0.02006 0.01062 -0.0213 0.8917 0.0380
-4.500 -0.3259 0.01924 0.00975 -0.0211 0.8759 0.0461
-4.250 -0.3013 0.01847 0.00893 -0.0205 0.8608 0.0588
-4.000 -0.2783 0.01769 0.00820 -0.0195 0.8468 0.0805
-3.750 -0.2572 0.01686 0.00759 -0.0182 0.8331 0.1253
-3.500 -0.2404 0.01572 0.00708 -0.0165 0.8201 0.2486
-3.250 -0.2307 0.01430 0.00675 -0.0134 0.8082 0.4786
-3.000 -0.2088 0.01387 0.00708 -0.0107 0.7987 0.6812
-2.750 -0.1826 0.01404 0.00728 -0.0091 0.7879 0.7517
-2.500 -0.1562 0.01429 0.00743 -0.0076 0.7785 0.7953
-2.250 -0.1263 0.01469 0.00772 -0.0065 0.7696 0.8320
-2.000 -0.0935 0.01516 0.00805 -0.0060 0.7608 0.8612
-1.750 -0.0577 0.01547 0.00818 -0.0065 0.7527 0.8787
-1.500 -0.0161 0.01567 0.00821 -0.0086 0.7442 0.8874
-1.250 0.0147 0.01573 0.00811 -0.0089 0.7364 0.8970
-1.000 0.0517 0.01580 0.00804 -0.0106 0.7280 0.9031
-0.750 0.0794 0.01582 0.00793 -0.0105 0.7205 0.9118
-0.500 0.1179 0.01585 0.00785 -0.0126 0.7127 0.9160
-0.250 0.1505 0.01587 0.00776 -0.0136 0.7053 0.9219
0.000 0.1792 0.01588 0.00769 -0.0139 0.6981 0.9284
0.250 0.2150 0.01590 0.00763 -0.0156 0.6905 0.9324
0.500 0.2463 0.01592 0.00757 -0.0164 0.6840 0.9379
0.750 0.2750 0.01595 0.00757 -0.0168 0.6761 0.9440
1.000 0.3101 0.01595 0.00750 -0.0183 0.6698 0.9479
1.250 0.3411 0.01600 0.00755 -0.0192 0.6613 0.9534
1.500 0.3706 0.01602 0.00752 -0.0197 0.6544 0.9588
1.750 0.4045 0.01603 0.00754 -0.0212 0.6449 0.9630
2.000 0.4352 0.01602 0.00748 -0.0218 0.6355 0.9682
2.250 0.4656 0.01599 0.00744 -0.0224 0.6232 0.9733
2.500 0.4980 0.01592 0.00735 -0.0234 0.6087 0.9779
2.750 0.5275 0.01588 0.00729 -0.0239 0.5938 0.9833
3.000 0.5605 0.01580 0.00722 -0.0251 0.5785 0.9877
3.250 0.5922 0.01576 0.00719 -0.0261 0.5635 0.9926
3.500 0.6246 0.01572 0.00717 -0.0272 0.5481 0.9972
3.750 0.6522 0.01572 0.00718 -0.0274 0.5323 1.0000
4.000 0.6717 0.01576 0.00727 -0.0260 0.5165 1.0000
4.250 0.6907 0.01582 0.00734 -0.0245 0.4989 1.0000
4.500 0.7093 0.01589 0.00742 -0.0228 0.4794 1.0000
4.750 0.7273 0.01601 0.00756 -0.0211 0.4549 1.0000
5.000 0.7446 0.01617 0.00767 -0.0193 0.4255 1.0000
5.250 0.7605 0.01642 0.00780 -0.0172 0.3895 1.0000
5.500 0.7747 0.01682 0.00800 -0.0150 0.3472 1.0000
5.750 0.7872 0.01739 0.00835 -0.0125 0.3058 1.0000
6.000 0.7992 0.01803 0.00880 -0.0101 0.2715 1.0000
6.250 0.8112 0.01870 0.00932 -0.0076 0.2444 1.0000
6.500 0.8235 0.01936 0.00987 -0.0053 0.2228 1.0000
6.750 0.8360 0.02003 0.01046 -0.0030 0.2057 1.0000
7.000 0.8491 0.02067 0.01105 -0.0007 0.1920 1.0000
7.250 0.8625 0.02131 0.01167 0.0014 0.1806 1.0000
7.500 0.8753 0.02198 0.01230 0.0036 0.1712 1.0000
7.750 0.8889 0.02263 0.01296 0.0057 0.1624 1.0000
8.000 0.9024 0.02333 0.01364 0.0078 0.1552 1.0000
8.250 0.9164 0.02401 0.01435 0.0097 0.1483 1.0000
8.500 0.9299 0.02477 0.01509 0.0117 0.1423 1.0000
8.750 0.9446 0.02547 0.01587 0.0134 0.1360 1.0000
9.000 0.9578 0.02629 0.01666 0.0153 0.1311 1.0000
9.250 0.9730 0.02707 0.01753 0.0169 0.1260 1.0000
9.500 0.9871 0.02787 0.01839 0.0185 0.1210 1.0000
9.750 0.9999 0.02878 0.01928 0.0202 0.1168 1.0000
10.000 1.0139 0.02965 0.02029 0.0219 0.1125 1.0000
10.250 1.0259 0.03053 0.02127 0.0237 0.1082 1.0000
10.500 1.0373 0.03147 0.02222 0.0254 0.1046 1.0000
10.750 1.0503 0.03255 0.02339 0.0269 0.1012 1.0000
11.000 1.0617 0.03363 0.02465 0.0284 0.0974 1.0000
11.250 1.0722 0.03472 0.02583 0.0299 0.0940 1.0000
11.500 1.0828 0.03588 0.02698 0.0312 0.0910 1.0000
11.750 1.0929 0.03725 0.02853 0.0324 0.0880 1.0000
12.000 1.1007 0.03868 0.03019 0.0337 0.0848 1.0000
12.250 1.1083 0.04010 0.03172 0.0348 0.0820 1.0000
12.500 1.1159 0.04148 0.03313 0.0358 0.0796 1.0000
12.750 1.1226 0.04322 0.03499 0.0367 0.0772 1.0000
13.000 1.1246 0.04530 0.03735 0.0375 0.0747 1.0000
13.250 1.1265 0.04737 0.03960 0.0382 0.0724 1.0000
13.500 1.1289 0.04936 0.04171 0.0386 0.0702 1.0000
13.750 1.1332 0.05126 0.04367 0.0389 0.0685 1.0000
14.000 1.1345 0.05369 0.04621 0.0391 0.0668 1.0000
14.250 1.1261 0.05717 0.05000 0.0389 0.0652 1.0000
14.500 1.1170 0.06082 0.05390 0.0383 0.0636 1.0000
14.750 1.1076 0.06466 0.05795 0.0373 0.0621 1.0000
15.000 1.0988 0.06853 0.06198 0.0361 0.0608 1.0000
15.250 1.0921 0.07223 0.06579 0.0348 0.0596 1.0000
15.500 1.0918 0.07514 0.06874 0.0339 0.0583 1.0000
15.750 1.0822 0.07963 0.07333 0.0322 0.0573 1.0000
16.000 1.0534 0.08742 0.08140 0.0281 0.0570 1.0000
16.250 1.0166 0.09744 0.09167 0.0224 0.0569 1.0000
16.500 0.9630 0.11212 0.10656 0.0135 0.0573 1.0000
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