EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.36 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e817-il-1000000-n5.txt Download as CSV file: xf-e817-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5202 0.08328 0.08158 -0.0687 0.9927 0.0015
-12.000 -0.5307 0.07516 0.07338 -0.0741 0.9907 0.0015
-11.750 -0.5480 0.06570 0.06381 -0.0813 0.9879 0.0015
-11.500 -0.5667 0.05614 0.05408 -0.0900 0.9844 0.0015
-11.000 -0.5866 0.04243 0.04002 -0.1039 0.9718 0.0014
-10.750 -0.5843 0.03712 0.03449 -0.1110 0.9649 0.0014
-10.500 -0.5764 0.03068 0.02768 -0.1213 0.9570 0.0014
-10.250 -0.5684 0.02587 0.02246 -0.1276 0.9429 0.0014
-10.000 -0.5585 0.02371 0.02005 -0.1284 0.9314 0.0014
-9.750 -0.5519 0.02142 0.01747 -0.1275 0.9215 0.0013
-9.500 -0.5400 0.01965 0.01546 -0.1267 0.9147 0.0013
-9.250 -0.5259 0.01814 0.01373 -0.1258 0.9088 0.0013
-9.000 -0.5097 0.01671 0.01209 -0.1250 0.9040 0.0013
-8.750 -0.4916 0.01550 0.01072 -0.1244 0.8999 0.0013
-8.500 -0.4713 0.01450 0.00953 -0.1240 0.8959 0.0013
-8.250 -0.4497 0.01356 0.00843 -0.1237 0.8924 0.0013
-8.000 -0.4265 0.01275 0.00748 -0.1236 0.8897 0.0013
-7.750 -0.4024 0.01205 0.00667 -0.1236 0.8871 0.0013
-7.500 -0.3773 0.01143 0.00593 -0.1236 0.8846 0.0013
-7.250 -0.3513 0.01093 0.00534 -0.1237 0.8823 0.0014
-7.000 -0.3248 0.01047 0.00477 -0.1239 0.8802 0.0014
-6.750 -0.2978 0.01011 0.00432 -0.1241 0.8783 0.0015
-6.500 -0.2703 0.00979 0.00393 -0.1244 0.8766 0.0017
-6.250 -0.2429 0.00952 0.00360 -0.1246 0.8747 0.0018
-6.000 -0.2152 0.00928 0.00329 -0.1249 0.8728 0.0023
-5.750 -0.1875 0.00901 0.00301 -0.1251 0.8708 0.0050
-5.500 -0.1601 0.00860 0.00269 -0.1255 0.8690 0.0240
-5.250 -0.1322 0.00831 0.00246 -0.1259 0.8674 0.0417
-5.000 -0.1045 0.00784 0.00216 -0.1264 0.8659 0.0866
-4.750 -0.0774 0.00696 0.00176 -0.1273 0.8644 0.2068
-4.500 -0.0491 0.00668 0.00163 -0.1278 0.8630 0.2496
-4.250 -0.0206 0.00658 0.00152 -0.1281 0.8615 0.2619
-4.000 0.0080 0.00645 0.00143 -0.1285 0.8599 0.2817
-3.750 0.0365 0.00631 0.00136 -0.1289 0.8583 0.3030
-3.500 0.0652 0.00622 0.00130 -0.1292 0.8568 0.3194
-3.250 0.0940 0.00615 0.00124 -0.1296 0.8554 0.3299
-3.000 0.1229 0.00609 0.00118 -0.1299 0.8541 0.3386
-2.750 0.1518 0.00605 0.00114 -0.1303 0.8528 0.3475
-2.500 0.1808 0.00601 0.00110 -0.1307 0.8514 0.3558
-2.250 0.2097 0.00597 0.00108 -0.1310 0.8501 0.3651
-2.000 0.2384 0.00593 0.00106 -0.1313 0.8487 0.3743
-1.750 0.2670 0.00589 0.00105 -0.1317 0.8472 0.3826
-1.500 0.2957 0.00584 0.00105 -0.1320 0.8454 0.3921
-1.250 0.3244 0.00581 0.00104 -0.1322 0.8434 0.4021
-1.000 0.3530 0.00577 0.00104 -0.1325 0.8410 0.4113
-0.750 0.3818 0.00575 0.00104 -0.1328 0.8385 0.4203
-0.500 0.4101 0.00572 0.00105 -0.1330 0.8352 0.4305
-0.250 0.4381 0.00568 0.00105 -0.1331 0.8309 0.4412
0.000 0.4664 0.00565 0.00105 -0.1332 0.8260 0.4507
0.250 0.4944 0.00563 0.00108 -0.1333 0.8209 0.4606
0.500 0.5222 0.00560 0.00110 -0.1333 0.8147 0.4715
0.750 0.5499 0.00558 0.00111 -0.1333 0.8074 0.4820
1.000 0.5773 0.00557 0.00113 -0.1332 0.7978 0.4918
1.250 0.6042 0.00556 0.00115 -0.1331 0.7850 0.5025
1.500 0.6292 0.00560 0.00118 -0.1324 0.7556 0.5132
1.750 0.6440 0.00609 0.00128 -0.1296 0.6587 0.5233
2.000 0.6536 0.00701 0.00165 -0.1259 0.5305 0.5326
2.250 0.6678 0.00781 0.00200 -0.1234 0.4178 0.5427
2.500 0.6881 0.00830 0.00225 -0.1221 0.3530 0.5537
3.000 0.7284 0.00934 0.00281 -0.1195 0.2191 0.5765
3.250 0.7461 0.01009 0.00322 -0.1178 0.1279 0.5874
3.500 0.7656 0.01074 0.00358 -0.1164 0.0606 0.5988
3.750 0.7890 0.01109 0.00386 -0.1157 0.0372 0.6106
4.000 0.8130 0.01139 0.00413 -0.1151 0.0229 0.6230
4.250 0.8358 0.01179 0.00447 -0.1142 0.0073 0.6352
4.500 0.8593 0.01215 0.00487 -0.1134 0.0033 0.6478
4.750 0.8835 0.01244 0.00524 -0.1127 0.0031 0.6608
5.000 0.9073 0.01275 0.00564 -0.1120 0.0028 0.6743
5.250 0.9309 0.01308 0.00604 -0.1113 0.0025 0.6879
5.500 0.9543 0.01341 0.00648 -0.1105 0.0023 0.7017
5.750 0.9774 0.01377 0.00690 -0.1097 0.0020 0.7160
6.000 0.9999 0.01419 0.00740 -0.1088 0.0019 0.7302
6.250 1.0219 0.01466 0.00797 -0.1078 0.0018 0.7442
6.500 1.0434 0.01518 0.00859 -0.1067 0.0017 0.7584
6.750 1.0640 0.01580 0.00933 -0.1054 0.0016 0.7741
7.000 1.0833 0.01658 0.01025 -0.1039 0.0015 0.7918
7.250 1.0996 0.01788 0.01177 -0.1018 0.0013 0.8106
7.500 1.1197 0.01847 0.01249 -0.1005 0.0013 0.8332
7.750 1.1392 0.01898 0.01313 -0.0991 0.0012 0.8598
8.000 1.1563 0.01940 0.01371 -0.0971 0.0012 0.8968
8.250 1.1689 0.01975 0.01426 -0.0942 0.0012 1.0000
8.500 1.1887 0.02049 0.01508 -0.0929 0.0011 1.0000
8.750 1.2078 0.02133 0.01601 -0.0916 0.0010 1.0000
9.000 1.2264 0.02225 0.01704 -0.0903 0.0010 1.0000
9.250 1.2438 0.02334 0.01826 -0.0887 0.0009 1.0000
9.500 1.2600 0.02465 0.01972 -0.0870 0.0008 1.0000
9.750 1.2748 0.02610 0.02134 -0.0851 0.0008 1.0000
10.000 1.2873 0.02782 0.02327 -0.0829 0.0007 1.0000
10.250 1.2966 0.02980 0.02548 -0.0803 0.0007 1.0000
10.500 1.3024 0.03204 0.02798 -0.0773 0.0007 1.0000
10.750 1.3035 0.03463 0.03084 -0.0738 0.0006 1.0000
11.000 1.2987 0.03772 0.03425 -0.0698 0.0006 1.0000
11.250 1.2877 0.04134 0.03818 -0.0655 0.0006 1.0000
11.500 1.2686 0.04581 0.04300 -0.0610 0.0006 1.0000
11.750 1.2418 0.05122 0.04875 -0.0568 0.0006 1.0000
12.000 1.2107 0.05741 0.05525 -0.0536 0.0006 1.0000
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Polar data table (+)
Polar graphs
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