EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Reynolds number: 1,000,000 Max Cl/Cd: 138.07 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e817-il-1000000.txt Download as CSV file: xf-e817-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.3506 0.14679 0.14522 -0.0440 0.9978 0.0061
-14.500 -0.3458 0.14366 0.14208 -0.0460 0.9972 0.0063
-8.250 -0.4210 0.01819 0.01390 -0.1291 0.9343 0.0041
-8.000 -0.4036 0.01555 0.01096 -0.1283 0.9300 0.0036
-7.750 -0.3865 0.01383 0.00903 -0.1271 0.9254 0.0032
-7.500 -0.3656 0.01256 0.00755 -0.1266 0.9217 0.0031
-7.250 -0.3411 0.01168 0.00651 -0.1266 0.9188 0.0030
-7.000 -0.3152 0.01095 0.00561 -0.1268 0.9163 0.0030
-6.750 -0.2896 0.01041 0.00497 -0.1268 0.9137 0.0031
-6.500 -0.2630 0.00994 0.00439 -0.1269 0.9111 0.0033
-6.250 -0.2357 0.00958 0.00394 -0.1271 0.9088 0.0037
-6.000 -0.2080 0.00916 0.00343 -0.1273 0.9068 0.0084
-5.750 -0.1810 0.00849 0.00297 -0.1278 0.9049 0.0542
-5.500 -0.1538 0.00786 0.00260 -0.1284 0.9030 0.1183
-5.250 -0.1272 0.00723 0.00229 -0.1290 0.9012 0.1990
-5.000 -0.0995 0.00689 0.00214 -0.1294 0.8994 0.2512
-4.750 -0.0714 0.00666 0.00204 -0.1298 0.8975 0.2906
-4.500 -0.0428 0.00654 0.00195 -0.1302 0.8957 0.3116
-4.250 -0.0140 0.00646 0.00185 -0.1306 0.8941 0.3232
-4.000 0.0149 0.00637 0.00179 -0.1310 0.8927 0.3398
-3.750 0.0439 0.00631 0.00174 -0.1315 0.8913 0.3569
-3.500 0.0728 0.00626 0.00171 -0.1319 0.8899 0.3716
-3.250 0.1011 0.00621 0.00168 -0.1321 0.8884 0.3825
-3.000 0.1296 0.00615 0.00163 -0.1324 0.8867 0.3931
-2.750 0.1582 0.00611 0.00161 -0.1328 0.8851 0.4035
-2.500 0.1870 0.00607 0.00159 -0.1331 0.8836 0.4140
-2.250 0.2159 0.00603 0.00157 -0.1335 0.8820 0.4250
-2.000 0.2449 0.00599 0.00156 -0.1338 0.8805 0.4359
-1.750 0.2740 0.00597 0.00155 -0.1342 0.8790 0.4465
-1.500 0.3031 0.00598 0.00157 -0.1346 0.8772 0.4578
-1.250 0.3312 0.00594 0.00159 -0.1348 0.8752 0.4692
-1.000 0.3594 0.00591 0.00160 -0.1350 0.8728 0.4802
-0.750 0.3879 0.00587 0.00160 -0.1352 0.8703 0.4910
-0.500 0.4168 0.00583 0.00159 -0.1355 0.8674 0.5025
-0.250 0.4459 0.00581 0.00159 -0.1358 0.8643 0.5141
0.000 0.4734 0.00577 0.00161 -0.1357 0.8604 0.5253
0.250 0.5015 0.00572 0.00161 -0.1358 0.8560 0.5370
0.500 0.5303 0.00567 0.00160 -0.1360 0.8519 0.5490
0.750 0.5577 0.00563 0.00161 -0.1359 0.8464 0.5605
1.000 0.5856 0.00557 0.00159 -0.1358 0.8404 0.5718
1.250 0.6131 0.00553 0.00161 -0.1357 0.8336 0.5837
1.500 0.6403 0.00547 0.00158 -0.1355 0.8236 0.5957
1.750 0.6666 0.00542 0.00157 -0.1350 0.8123 0.6077
2.000 0.6928 0.00539 0.00158 -0.1346 0.7979 0.6199
2.500 0.7456 0.00540 0.00169 -0.1339 0.7672 0.6448
2.750 0.7637 0.00569 0.00174 -0.1317 0.6923 0.6570
3.000 0.7662 0.00687 0.00223 -0.1265 0.5320 0.6681
3.250 0.7698 0.00828 0.00281 -0.1220 0.3460 0.6797
3.500 0.7806 0.00945 0.00333 -0.1190 0.1991 0.6922
3.750 0.7985 0.01018 0.00373 -0.1174 0.1178 0.7053
4.000 0.8185 0.01078 0.00410 -0.1160 0.0639 0.7192
4.250 0.8399 0.01128 0.00447 -0.1150 0.0305 0.7335
4.500 0.8601 0.01196 0.00511 -0.1133 0.0063 0.7482
4.750 0.8833 0.01234 0.00559 -0.1124 0.0056 0.7638
5.000 0.9063 0.01274 0.00607 -0.1115 0.0049 0.7802
5.250 0.9281 0.01322 0.00666 -0.1103 0.0043 0.7971
5.500 0.9488 0.01382 0.00744 -0.1089 0.0040 0.8155
5.750 0.9677 0.01461 0.00839 -0.1071 0.0038 0.8356
6.000 0.9843 0.01570 0.00967 -0.1048 0.0036 0.8580
6.250 0.9993 0.01762 0.01184 -0.1023 0.0034 0.8830
6.500 1.0168 0.01752 0.01187 -0.1001 0.0032 0.9273
6.750 1.0364 0.01798 0.01244 -0.0985 0.0031 1.0000
7.000 1.0597 0.01884 0.01338 -0.0978 0.0028 1.0000
7.250 1.0828 0.01995 0.01459 -0.0970 0.0025 1.0000
7.500 1.1061 0.02168 0.01649 -0.0962 0.0024 1.0000
7.750 1.1290 0.02420 0.01928 -0.0952 0.0023 1.0000
8.000 1.1466 0.02857 0.02413 -0.0930 0.0025 1.0000
8.500 1.1576 0.03942 0.03591 -0.0847 0.0042 1.0000
8.750 1.1599 0.04267 0.03942 -0.0811 0.0042 1.0000
9.000 1.1591 0.04571 0.04269 -0.0774 0.0041 1.0000
9.250 1.1538 0.04876 0.04595 -0.0732 0.0040 1.0000
9.500 1.1415 0.05151 0.04891 -0.0681 0.0040 1.0000
9.750 1.1265 0.05438 0.05196 -0.0633 0.0039 1.0000
10.000 1.1094 0.05771 0.05546 -0.0591 0.0039 1.0000
10.250 1.0909 0.06148 0.05939 -0.0557 0.0039 1.0000
10.500 1.0710 0.06571 0.06379 -0.0532 0.0039 1.0000
10.750 1.0500 0.07058 0.06881 -0.0518 0.0039 1.0000
11.000 1.0277 0.07632 0.07467 -0.0516 0.0039 1.0000
11.250 1.0037 0.08323 0.08173 -0.0531 0.0039 1.0000
11.500 0.9769 0.09233 0.09098 -0.0573 0.0040 1.0000
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Polar data table (+)
Polar graphs
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