EPPLER 818 HYDROFOIL AIRFOIL (e818-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER 818 HYDROFOIL AIRFOIL (e818-il) Reynolds number: 1,000,000 Max Cl/Cd: 126.56 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e818-il-1000000.txt Download as CSV file: xf-e818-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 818 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4173 0.07933 0.07775 -0.0642 0.9916 0.0060
-9.000 -0.4145 0.07215 0.07057 -0.0705 0.9887 0.0060
-8.750 -0.4202 0.05703 0.05537 -0.0866 0.9849 0.0053
-8.500 -0.4222 0.04716 0.04529 -0.1032 0.9787 0.0051
-8.250 -0.4127 0.04156 0.03945 -0.1126 0.9721 0.0053
-8.000 -0.3933 0.03705 0.03469 -0.1190 0.9699 0.0056
-7.750 -0.3750 0.03349 0.03088 -0.1223 0.9660 0.0062
-7.500 -0.3554 0.03038 0.02751 -0.1242 0.9611 0.0069
-7.250 -0.3301 0.02772 0.02460 -0.1261 0.9582 0.0080
-7.000 -0.2959 0.02830 0.02510 -0.1268 0.9568 0.0100
-6.750 -0.2724 0.02704 0.02358 -0.1272 0.9523 0.0103
-6.500 -0.2578 0.02056 0.01649 -0.1281 0.9465 0.0112
-6.250 -0.2327 0.01756 0.01327 -0.1292 0.9437 0.0132
-6.000 -0.2078 0.01617 0.01173 -0.1292 0.9402 0.0151
-5.750 -0.1816 0.01493 0.01035 -0.1292 0.9367 0.0177
-5.500 -0.1513 0.01575 0.01106 -0.1293 0.9340 0.0215
-5.000 -0.0988 0.01015 0.00517 -0.1280 0.9284 0.0079
-4.750 -0.0712 0.00895 0.00372 -0.1280 0.9253 0.0052
-4.500 -0.0425 0.00854 0.00321 -0.1283 0.9228 0.0043
-4.250 -0.0136 0.00819 0.00276 -0.1286 0.9206 0.0039
-4.000 0.0160 0.00785 0.00226 -0.1290 0.9186 0.0037
-3.750 0.0451 0.00769 0.00197 -0.1293 0.9165 0.0037
-3.500 0.0731 0.00758 0.00180 -0.1294 0.9142 0.0038
-3.250 0.1014 0.00672 0.00143 -0.1304 0.9119 0.1580
-3.000 0.1300 0.00620 0.00129 -0.1312 0.9099 0.2656
-2.750 0.1588 0.00596 0.00125 -0.1317 0.9079 0.3195
-2.500 0.1877 0.00564 0.00126 -0.1324 0.9061 0.4138
-2.250 0.2169 0.00559 0.00125 -0.1329 0.9043 0.4400
-2.000 0.2449 0.00555 0.00125 -0.1331 0.9023 0.4530
-1.250 0.3303 0.00545 0.00125 -0.1339 0.8954 0.4930
-0.500 0.4152 0.00537 0.00130 -0.1345 0.8866 0.5327
-0.250 0.4434 0.00534 0.00130 -0.1346 0.8828 0.5458
0.000 0.4722 0.00531 0.00130 -0.1348 0.8788 0.5593
0.250 0.4994 0.00528 0.00133 -0.1348 0.8741 0.5728
0.500 0.5271 0.00522 0.00131 -0.1347 0.8674 0.5864
0.750 0.5550 0.00521 0.00142 -0.1347 0.8627 0.6004
1.000 0.5816 0.00514 0.00139 -0.1343 0.8509 0.6142
1.250 0.6075 0.00509 0.00138 -0.1338 0.8363 0.6279
1.500 0.6331 0.00506 0.00139 -0.1332 0.8178 0.6417
1.750 0.6543 0.00517 0.00134 -0.1315 0.7550 0.6552
2.000 0.6529 0.00679 0.00181 -0.1255 0.4948 0.6671
2.250 0.6480 0.00955 0.00275 -0.1198 0.0699 0.6789
2.500 0.6700 0.01024 0.00333 -0.1185 0.0066 0.6931
2.750 0.6942 0.01070 0.00400 -0.1176 0.0061 0.7076
3.000 0.7202 0.01088 0.00421 -0.1173 0.0051 0.7231
3.250 0.7446 0.01128 0.00473 -0.1166 0.0045 0.7388
3.500 0.7687 0.01172 0.00526 -0.1158 0.0039 0.7553
3.750 0.7924 0.01219 0.00581 -0.1150 0.0031 0.7720
4.000 0.8118 0.01331 0.00709 -0.1131 0.0024 0.7890
4.250 0.8309 0.01508 0.00905 -0.1110 0.0022 0.8064
4.500 0.8552 0.01654 0.01067 -0.1100 0.0022 0.8247
4.750 0.8807 0.01760 0.01189 -0.1092 0.0024 0.8448
5.250 0.9248 0.01510 0.01040 -0.1031 0.0038 0.8509
5.500 0.9443 0.01731 0.01291 -0.1011 0.0035 0.8706
5.750 0.9605 0.02006 0.01604 -0.0984 0.0033 0.8923
6.000 0.9721 0.02252 0.01881 -0.0951 0.0031 0.9252
6.250 0.9798 0.02542 0.02199 -0.0911 0.0030 1.0000
6.500 0.9921 0.02904 0.02587 -0.0886 0.0029 1.0000
6.750 1.0017 0.03306 0.03013 -0.0858 0.0028 1.0000
7.000 1.0091 0.03705 0.03433 -0.0831 0.0027 1.0000
7.250 1.0136 0.04132 0.03882 -0.0803 0.0026 1.0000
7.500 1.0145 0.04593 0.04364 -0.0772 0.0026 1.0000
7.750 1.0115 0.05078 0.04868 -0.0739 0.0025 1.0000
8.000 1.0046 0.05540 0.05348 -0.0706 0.0025 1.0000
8.250 0.9918 0.05966 0.05788 -0.0668 0.0025 1.0000
8.500 0.9711 0.06338 0.06172 -0.0622 0.0025 1.0000
8.750 0.9491 0.06761 0.06608 -0.0589 0.0025 1.0000
9.000 0.9245 0.07296 0.07156 -0.0569 0.0025 1.0000
9.250 0.8988 0.07902 0.07773 -0.0566 0.0026 1.0000
9.500 0.8703 0.08686 0.08569 -0.0585 0.0026 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EPPLER 818 HYDROFOIL AIRFOIL (e818-il)