EPPLER E836 HYDROFOIL AIRFOIL (e836-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E836 HYDROFOIL AIRFOIL (e836-il) Reynolds number: 200,000 Max Cl/Cd: 42.45 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e836-il-200000-n5.txt Download as CSV file: xf-e836-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E836 HYDROFOIL AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.6826 0.08839 0.08491 -0.0302 1.0000 0.0088
-12.500 -0.7316 0.07354 0.06981 -0.0398 1.0000 0.0080
-12.250 -0.7787 0.06271 0.05859 -0.0445 1.0000 0.0073
-12.000 -0.7920 0.05863 0.05437 -0.0456 1.0000 0.0074
-11.750 -0.7983 0.05597 0.05161 -0.0460 1.0000 0.0077
-11.500 -0.8106 0.05259 0.04807 -0.0457 1.0000 0.0079
-11.250 -0.8293 0.04829 0.04347 -0.0443 1.0000 0.0077
-11.000 -0.8380 0.04557 0.04054 -0.0427 1.0000 0.0079
-10.750 -0.8425 0.04353 0.03833 -0.0408 1.0000 0.0082
-10.500 -0.8490 0.04082 0.03535 -0.0382 1.0000 0.0082
-10.250 -0.8509 0.03887 0.03320 -0.0355 1.0000 0.0086
-10.000 -0.8514 0.03661 0.03067 -0.0325 1.0000 0.0087
-9.750 -0.8485 0.03434 0.02811 -0.0297 1.0000 0.0089
-9.500 -0.8409 0.03216 0.02565 -0.0273 1.0000 0.0090
-9.250 -0.8294 0.03020 0.02344 -0.0253 1.0000 0.0093
-9.000 -0.8156 0.02839 0.02140 -0.0235 1.0000 0.0097
-8.750 -0.8015 0.02682 0.01962 -0.0217 1.0000 0.0100
-8.500 -0.7895 0.02547 0.01813 -0.0194 1.0000 0.0105
-8.250 -0.7727 0.02419 0.01671 -0.0182 0.9954 0.0112
-8.000 -0.7448 0.02286 0.01521 -0.0192 0.9844 0.0119
-7.750 -0.7204 0.02140 0.01370 -0.0199 0.9731 0.0137
-7.500 -0.6930 0.02046 0.01268 -0.0208 0.9633 0.0161
-7.250 -0.6667 0.01941 0.01146 -0.0214 0.9543 0.0181
-7.000 -0.6449 0.01827 0.01019 -0.0211 0.9441 0.0216
-6.750 -0.6200 0.01763 0.00943 -0.0212 0.9354 0.0268
-6.500 -0.5973 0.01682 0.00861 -0.0208 0.9276 0.0365
-6.250 -0.5778 0.01609 0.00793 -0.0198 0.9188 0.0535
-6.000 -0.5585 0.01536 0.00731 -0.0187 0.9114 0.0835
-5.750 -0.5401 0.01471 0.00680 -0.0175 0.9037 0.1227
-5.500 -0.5219 0.01407 0.00633 -0.0162 0.8972 0.1708
-5.250 -0.5066 0.01333 0.00588 -0.0144 0.8900 0.2400
-5.000 -0.4954 0.01237 0.00542 -0.0119 0.8835 0.3434
-4.750 -0.4850 0.01150 0.00503 -0.0091 0.8767 0.4552
-4.500 -0.4683 0.01103 0.00492 -0.0069 0.8718 0.5437
-4.250 -0.4464 0.01088 0.00489 -0.0057 0.8661 0.5961
-4.000 -0.4224 0.01083 0.00488 -0.0047 0.8615 0.6328
-3.750 -0.3973 0.01084 0.00485 -0.0040 0.8575 0.6574
-3.500 -0.3720 0.01086 0.00482 -0.0035 0.8523 0.6759
-3.250 -0.3465 0.01088 0.00477 -0.0029 0.8480 0.6924
-3.000 -0.3203 0.01092 0.00470 -0.0025 0.8445 0.7065
-2.750 -0.2941 0.01097 0.00472 -0.0021 0.8395 0.7173
-2.500 -0.2676 0.01101 0.00471 -0.0018 0.8352 0.7272
-2.250 -0.2411 0.01105 0.00467 -0.0015 0.8317 0.7371
-2.000 -0.2151 0.01108 0.00465 -0.0011 0.8270 0.7463
-1.750 -0.1881 0.01112 0.00467 -0.0009 0.8226 0.7533
-1.500 -0.1619 0.01113 0.00460 -0.0007 0.8189 0.7615
-1.250 -0.1344 0.01117 0.00462 -0.0005 0.8149 0.7670
-1.000 -0.1083 0.01118 0.00460 -0.0003 0.8101 0.7740
-0.750 -0.0810 0.01119 0.00459 -0.0002 0.8061 0.7788
-0.500 -0.0535 0.01119 0.00458 -0.0002 0.8025 0.7836
-0.250 -0.0277 0.01119 0.00455 0.0000 0.7973 0.7894
0.000 0.0000 0.01119 0.00457 0.0000 0.7930 0.7930
0.250 0.0277 0.01119 0.00455 0.0000 0.7894 0.7973
0.500 0.0535 0.01119 0.00458 0.0002 0.7836 0.8025
0.750 0.0809 0.01119 0.00459 0.0002 0.7788 0.8061
1.000 0.1083 0.01118 0.00461 0.0003 0.7740 0.8101
1.250 0.1344 0.01117 0.00462 0.0006 0.7670 0.8149
1.500 0.1618 0.01113 0.00460 0.0007 0.7615 0.8189
1.750 0.1880 0.01112 0.00467 0.0009 0.7533 0.8226
2.000 0.2150 0.01108 0.00465 0.0012 0.7463 0.8270
2.250 0.2410 0.01105 0.00467 0.0015 0.7371 0.8317
2.500 0.2675 0.01101 0.00471 0.0018 0.7272 0.8352
2.750 0.2940 0.01097 0.00472 0.0021 0.7172 0.8395
3.000 0.3202 0.01092 0.00470 0.0025 0.7065 0.8445
3.250 0.3464 0.01088 0.00474 0.0030 0.6923 0.8480
3.500 0.3720 0.01086 0.00482 0.0035 0.6760 0.8523
3.750 0.3972 0.01084 0.00485 0.0040 0.6574 0.8575
4.000 0.4223 0.01083 0.00488 0.0047 0.6327 0.8615
4.250 0.4463 0.01088 0.00489 0.0057 0.5961 0.8661
4.500 0.4682 0.01103 0.00492 0.0069 0.5442 0.8718
4.750 0.4850 0.01149 0.00503 0.0091 0.4559 0.8767
5.000 0.4952 0.01237 0.00542 0.0120 0.3434 0.8835
5.250 0.5065 0.01332 0.00588 0.0144 0.2406 0.8900
5.500 0.5217 0.01408 0.00633 0.0162 0.1706 0.8972
5.750 0.5400 0.01471 0.00680 0.0175 0.1234 0.9037
6.000 0.5582 0.01536 0.00731 0.0188 0.0836 0.9114
6.250 0.5775 0.01610 0.00793 0.0198 0.0533 0.9188
6.500 0.5971 0.01682 0.00861 0.0209 0.0366 0.9276
6.750 0.6202 0.01760 0.00939 0.0211 0.0264 0.9354
7.000 0.6448 0.01826 0.01018 0.0212 0.0218 0.9441
7.250 0.6665 0.01943 0.01148 0.0214 0.0182 0.9543
7.500 0.6932 0.02044 0.01266 0.0208 0.0159 0.9633
7.750 0.7207 0.02134 0.01362 0.0198 0.0135 0.9730
8.000 0.7450 0.02282 0.01518 0.0192 0.0118 0.9844
8.250 0.7726 0.02419 0.01671 0.0182 0.0112 0.9954
8.500 0.7895 0.02548 0.01814 0.0194 0.0106 1.0000
8.750 0.8014 0.02682 0.01961 0.0217 0.0100 1.0000
9.000 0.8154 0.02839 0.02141 0.0236 0.0096 1.0000
9.250 0.8292 0.03017 0.02339 0.0253 0.0093 1.0000
9.500 0.8407 0.03217 0.02565 0.0273 0.0090 1.0000
9.750 0.8482 0.03431 0.02808 0.0297 0.0088 1.0000
10.000 0.8513 0.03658 0.03063 0.0326 0.0087 1.0000
10.250 0.8501 0.03898 0.03331 0.0356 0.0086 1.0000
10.500 0.8462 0.04144 0.03605 0.0385 0.0085 1.0000
10.750 0.8445 0.04311 0.03787 0.0406 0.0080 1.0000
11.000 0.8374 0.04567 0.04065 0.0427 0.0079 1.0000
11.250 0.8262 0.04879 0.04401 0.0445 0.0078 1.0000
11.500 0.8193 0.05125 0.04662 0.0454 0.0076 1.0000
11.750 0.7945 0.05659 0.05228 0.0460 0.0079 1.0000
12.000 0.7862 0.05959 0.05539 0.0455 0.0075 1.0000
12.250 0.7595 0.06600 0.06205 0.0436 0.0078 1.0000
12.500 0.7649 0.06737 0.06339 0.0424 0.0071 1.0000
12.750 0.6788 0.08964 0.08617 0.0294 0.0090 1.0000
13.000 0.6452 0.10609 0.10265 0.0203 0.0096 1.0000
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