EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Reynolds number: 500,000 Max Cl/Cd: 98.21 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e817-il-500000-n5.txt Download as CSV file: xf-e817-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 817 HYDROFOIL AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5052 0.08553 0.08318 -0.0627 0.9940 0.0021
-11.500 -0.5273 0.07404 0.07158 -0.0705 0.9915 0.0021
-11.250 -0.5375 0.06592 0.06334 -0.0774 0.9884 0.0021
-11.000 -0.5504 0.05720 0.05445 -0.0859 0.9846 0.0021
-10.750 -0.5548 0.05012 0.04718 -0.0942 0.9815 0.0020
-10.500 -0.5633 0.04410 0.04096 -0.1002 0.9733 0.0020
-10.250 -0.5669 0.03790 0.03447 -0.1078 0.9671 0.0020
-10.000 -0.5621 0.03393 0.03025 -0.1128 0.9591 0.0020
-9.750 -0.5552 0.02978 0.02575 -0.1176 0.9515 0.0020
-9.500 -0.5412 0.02674 0.02238 -0.1200 0.9459 0.0020
-9.250 -0.5233 0.02422 0.01956 -0.1215 0.9418 0.0020
-9.000 -0.5077 0.02223 0.01730 -0.1216 0.9361 0.0020
-8.750 -0.4875 0.02043 0.01521 -0.1221 0.9322 0.0020
-8.500 -0.4657 0.01895 0.01353 -0.1225 0.9290 0.0020
-8.250 -0.4473 0.01768 0.01209 -0.1220 0.9244 0.0020
-8.000 -0.4254 0.01653 0.01077 -0.1220 0.9207 0.0021
-7.750 -0.4013 0.01549 0.00957 -0.1223 0.9178 0.0021
-7.500 -0.3778 0.01461 0.00855 -0.1224 0.9148 0.0021
-7.250 -0.3549 0.01373 0.00752 -0.1223 0.9116 0.0022
-7.000 -0.3304 0.01280 0.00639 -0.1224 0.9088 0.0026
-6.750 -0.3035 0.01227 0.00573 -0.1227 0.9066 0.0030
-6.500 -0.2758 0.01181 0.00518 -0.1232 0.9048 0.0041
-6.250 -0.2479 0.01140 0.00471 -0.1236 0.9031 0.0075
-6.000 -0.2221 0.01096 0.00427 -0.1237 0.9006 0.0214
-5.750 -0.1963 0.01027 0.00381 -0.1241 0.8981 0.0648
-5.500 -0.1710 0.00915 0.00323 -0.1250 0.8958 0.1833
-5.250 -0.1431 0.00878 0.00300 -0.1255 0.8940 0.2334
-5.000 -0.1144 0.00857 0.00283 -0.1260 0.8924 0.2606
-4.750 -0.0854 0.00844 0.00268 -0.1265 0.8911 0.2773
-4.500 -0.0566 0.00831 0.00256 -0.1269 0.8897 0.2954
-4.250 -0.0290 0.00818 0.00244 -0.1271 0.8878 0.3170
-4.000 -0.0011 0.00807 0.00237 -0.1274 0.8859 0.3364
-3.500 0.0557 0.00792 0.00221 -0.1280 0.8823 0.3588
-3.250 0.0844 0.00786 0.00214 -0.1283 0.8808 0.3679
-3.000 0.1134 0.00781 0.00206 -0.1287 0.8794 0.3772
-2.750 0.1425 0.00776 0.00201 -0.1291 0.8782 0.3872
-2.500 0.1717 0.00771 0.00197 -0.1296 0.8769 0.3968
-2.250 0.1993 0.00768 0.00197 -0.1297 0.8749 0.4063
-2.000 0.2273 0.00766 0.00197 -0.1298 0.8732 0.4168
-1.750 0.2554 0.00763 0.00197 -0.1301 0.8714 0.4270
-1.500 0.2839 0.00760 0.00197 -0.1303 0.8695 0.4369
-1.250 0.3126 0.00757 0.00198 -0.1306 0.8678 0.4477
-1.000 0.3416 0.00755 0.00199 -0.1310 0.8662 0.4586
-0.750 0.3708 0.00753 0.00200 -0.1314 0.8645 0.4692
-0.500 0.3987 0.00751 0.00204 -0.1315 0.8622 0.4802
-0.250 0.4260 0.00750 0.00210 -0.1315 0.8593 0.4911
0.000 0.4541 0.00749 0.00214 -0.1316 0.8564 0.5019
0.250 0.4829 0.00745 0.00217 -0.1319 0.8532 0.5130
0.500 0.5118 0.00742 0.00219 -0.1321 0.8496 0.5247
0.750 0.5381 0.00739 0.00224 -0.1318 0.8440 0.5362
1.000 0.5667 0.00733 0.00224 -0.1319 0.8387 0.5480
1.250 0.5932 0.00730 0.00228 -0.1316 0.8316 0.5596
1.500 0.6211 0.00723 0.00229 -0.1315 0.8232 0.5716
1.750 0.6473 0.00718 0.00230 -0.1310 0.8116 0.5835
2.000 0.6719 0.00712 0.00230 -0.1302 0.7921 0.5956
2.250 0.6963 0.00709 0.00227 -0.1292 0.7612 0.6076
2.500 0.7132 0.00741 0.00222 -0.1266 0.6682 0.6194
2.750 0.7205 0.00833 0.00259 -0.1224 0.5494 0.6303
3.000 0.7329 0.00910 0.00299 -0.1194 0.4568 0.6420
3.250 0.7474 0.00986 0.00344 -0.1170 0.3683 0.6539
3.500 0.7609 0.01077 0.00391 -0.1145 0.2609 0.6661
3.750 0.7776 0.01156 0.00436 -0.1127 0.1756 0.6790
4.000 0.7940 0.01242 0.00485 -0.1108 0.0921 0.6921
4.250 0.8130 0.01310 0.00530 -0.1094 0.0430 0.7059
4.500 0.8348 0.01355 0.00570 -0.1084 0.0241 0.7203
4.750 0.8563 0.01403 0.00616 -0.1073 0.0100 0.7352
5.000 0.8782 0.01449 0.00670 -0.1061 0.0058 0.7504
5.250 0.8999 0.01495 0.00727 -0.1050 0.0048 0.7661
5.500 0.9211 0.01547 0.00791 -0.1037 0.0044 0.7819
5.750 0.9411 0.01607 0.00872 -0.1022 0.0041 0.7988
6.000 0.9596 0.01678 0.00959 -0.1004 0.0039 0.8179
6.250 0.9754 0.01775 0.01074 -0.0981 0.0036 0.8394
6.500 0.9912 0.01858 0.01174 -0.0958 0.0033 0.8659
6.750 1.0054 0.01891 0.01222 -0.0931 0.0031 0.9074
7.000 1.0224 0.01940 0.01284 -0.0910 0.0028 1.0000
7.250 1.0433 0.02026 0.01378 -0.0900 0.0026 1.0000
7.500 1.0641 0.02139 0.01504 -0.0889 0.0025 1.0000
7.750 1.0854 0.02256 0.01633 -0.0879 0.0024 1.0000
8.000 1.1066 0.02375 0.01767 -0.0870 0.0022 1.0000
8.250 1.1272 0.02496 0.01901 -0.0860 0.0020 1.0000
8.500 1.1467 0.02622 0.02042 -0.0849 0.0019 1.0000
8.750 1.1646 0.02750 0.02190 -0.0835 0.0018 1.0000
9.000 1.1807 0.02884 0.02339 -0.0819 0.0017 1.0000
9.250 1.1946 0.03044 0.02519 -0.0800 0.0016 1.0000
9.500 1.2049 0.03258 0.02758 -0.0776 0.0015 1.0000
9.750 1.2068 0.03588 0.03128 -0.0741 0.0014 1.0000
10.000 1.1960 0.04043 0.03633 -0.0692 0.0014 1.0000
10.250 1.1829 0.04450 0.04078 -0.0644 0.0013 1.0000
10.500 1.1628 0.04915 0.04582 -0.0597 0.0013 1.0000
10.750 1.1463 0.05327 0.05023 -0.0562 0.0013 1.0000
11.000 1.1276 0.05778 0.05499 -0.0533 0.0013 1.0000
11.250 1.1088 0.06251 0.05995 -0.0515 0.0013 1.0000
11.500 1.0874 0.06796 0.06561 -0.0507 0.0013 1.0000
11.750 1.0658 0.07401 0.07184 -0.0513 0.0013 1.0000
12.000 1.0503 0.07973 0.07771 -0.0531 0.0014 1.0000
12.250 1.0321 0.08703 0.08516 -0.0568 0.0014 1.0000
12.500 1.0133 0.09672 0.09499 -0.0631 0.0014 1.0000
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Polar data table (+)
Polar graphs
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