EPPLER E836 HYDROFOIL AIRFOIL (e836-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: EPPLER E836 HYDROFOIL AIRFOIL (e836-il) Reynolds number: 50,000 Max Cl/Cd: 28.74 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e836-il-50000.txt Download as CSV file: xf-e836-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5338 0.09360 0.08736 -0.0347 1.0000 0.1281
-10.750 -0.5277 0.08823 0.08198 -0.0349 1.0000 0.1225
-10.500 -0.6910 0.08432 0.07774 -0.0408 1.0000 0.1141
-10.250 -0.6936 0.07928 0.07269 -0.0412 1.0000 0.1111
-10.000 -0.7207 0.07432 0.06766 -0.0413 1.0000 0.1067
-9.750 -0.7699 0.07092 0.06394 -0.0380 1.0000 0.1006
-9.500 -0.7770 0.06684 0.05973 -0.0362 1.0000 0.0995
-9.250 -0.7839 0.06306 0.05577 -0.0340 1.0000 0.0983
-9.000 -0.7913 0.05943 0.05189 -0.0314 1.0000 0.0974
-8.750 -0.7966 0.05601 0.04816 -0.0284 1.0000 0.0969
-8.500 -0.7994 0.05267 0.04447 -0.0251 1.0000 0.0966
-8.250 -0.7987 0.04950 0.04095 -0.0219 1.0000 0.0964
-8.000 -0.7947 0.04640 0.03746 -0.0186 1.0000 0.0961
-7.750 -0.7874 0.04345 0.03412 -0.0154 1.0000 0.0965
-7.500 -0.7767 0.04071 0.03097 -0.0124 1.0000 0.0982
-7.250 -0.7655 0.03832 0.02817 -0.0095 1.0000 0.1032
-7.000 -0.7463 0.03605 0.02577 -0.0079 1.0000 0.1117
-6.750 -0.7149 0.03328 0.02291 -0.0076 1.0000 0.1226
-6.500 -0.6854 0.03102 0.02076 -0.0070 1.0000 0.1471
-6.250 -0.6581 0.02852 0.01865 -0.0059 1.0000 0.1950
-6.000 -0.6624 0.02620 0.01713 -0.0006 1.0000 0.2675
-5.750 -0.6829 0.02373 0.01611 0.0073 1.0000 0.3925
-5.500 -0.6846 0.02554 0.01933 0.0196 1.0000 0.6429
-5.250 -0.6013 0.03346 0.02641 0.0251 1.0000 0.7408
-5.000 -0.3991 0.03808 0.02943 0.0067 1.0000 0.8094
-4.750 -0.3518 0.03779 0.02876 0.0040 1.0000 0.8419
-4.500 -0.3039 0.03713 0.02777 0.0004 1.0000 0.8710
-4.250 -0.2507 0.03612 0.02641 -0.0047 1.0000 0.8981
-4.000 -0.1987 0.03489 0.02490 -0.0103 1.0000 0.9225
-3.750 -0.1555 0.03372 0.02352 -0.0147 1.0000 0.9446
-3.500 -0.1075 0.03239 0.02196 -0.0204 1.0000 0.9653
-3.250 -0.0599 0.03103 0.02043 -0.0264 1.0000 0.9840
-3.000 -0.0069 0.02943 0.01866 -0.0336 1.0000 1.0000
-2.750 -0.0055 0.02934 0.01855 -0.0311 1.0000 1.0000
-2.500 -0.0057 0.02932 0.01851 -0.0282 1.0000 1.0000
-2.250 -0.0063 0.02933 0.01850 -0.0252 1.0000 1.0000
-2.000 -0.0068 0.02935 0.01849 -0.0223 1.0000 1.0000
-1.750 -0.0070 0.02936 0.01848 -0.0193 1.0000 1.0000
-1.500 -0.0068 0.02936 0.01847 -0.0165 1.0000 1.0000
-1.250 -0.0062 0.02936 0.01845 -0.0137 1.0000 1.0000
-1.000 -0.0053 0.02935 0.01843 -0.0109 1.0000 1.0000
-0.750 -0.0042 0.02935 0.01841 -0.0081 1.0000 1.0000
-0.500 -0.0029 0.02935 0.01840 -0.0054 1.0000 1.0000
-0.250 -0.0015 0.02934 0.01839 -0.0027 1.0000 1.0000
0.000 0.0000 0.02934 0.01839 0.0000 1.0000 1.0000
0.250 0.0015 0.02934 0.01839 0.0027 1.0000 1.0000
0.500 0.0029 0.02934 0.01839 0.0054 1.0000 1.0000
0.750 0.0042 0.02935 0.01841 0.0081 1.0000 1.0000
1.000 0.0053 0.02935 0.01843 0.0109 1.0000 1.0000
1.250 0.0062 0.02935 0.01844 0.0137 1.0000 1.0000
1.500 0.0067 0.02935 0.01845 0.0165 1.0000 1.0000
1.750 0.0070 0.02935 0.01847 0.0194 1.0000 1.0000
2.000 0.0068 0.02934 0.01848 0.0223 1.0000 1.0000
2.250 0.0063 0.02932 0.01848 0.0252 1.0000 1.0000
2.500 0.0056 0.02931 0.01850 0.0282 1.0000 1.0000
2.750 0.0055 0.02932 0.01853 0.0311 1.0000 1.0000
3.000 0.0068 0.02941 0.01864 0.0336 1.0000 1.0000
3.250 0.0591 0.03098 0.02039 0.0265 0.9842 1.0000
3.500 0.1075 0.03237 0.02194 0.0204 0.9653 1.0000
3.750 0.1548 0.03369 0.02349 0.0148 0.9448 1.0000
4.000 0.1987 0.03487 0.02488 0.0102 0.9225 1.0000
4.250 0.2508 0.03612 0.02640 0.0047 0.8982 1.0000
4.500 0.3046 0.03713 0.02777 -0.0005 0.8713 1.0000
4.750 0.3520 0.03777 0.02875 -0.0040 0.8420 1.0000
5.000 0.3994 0.03806 0.02941 -0.0067 0.8093 1.0000
5.250 0.5568 0.03539 0.02800 -0.0213 0.7521 1.0000
5.500 0.6844 0.02553 0.01932 -0.0195 0.6423 1.0000
5.750 0.6826 0.02375 0.01611 -0.0072 0.3903 1.0000
6.000 0.6623 0.02623 0.01716 0.0007 0.2660 1.0000
6.250 0.6582 0.02852 0.01865 0.0058 0.1951 1.0000
6.500 0.6855 0.03103 0.02076 0.0070 0.1470 1.0000
6.750 0.7151 0.03328 0.02290 0.0075 0.1226 1.0000
7.000 0.7465 0.03607 0.02580 0.0079 0.1115 1.0000
7.250 0.7661 0.03839 0.02821 0.0094 0.1028 1.0000
7.500 0.7769 0.04074 0.03099 0.0124 0.0982 1.0000
7.750 0.7874 0.04347 0.03414 0.0154 0.0964 1.0000
8.000 0.7948 0.04641 0.03747 0.0186 0.0961 1.0000
8.250 0.7988 0.04951 0.04095 0.0218 0.0965 1.0000
8.500 0.7996 0.05268 0.04448 0.0251 0.0968 1.0000
8.750 0.7967 0.05596 0.04810 0.0284 0.0968 1.0000
9.000 0.7910 0.05938 0.05184 0.0314 0.0972 1.0000
9.250 0.7850 0.06303 0.05573 0.0339 0.0985 1.0000
9.500 0.7748 0.06678 0.05968 0.0364 0.0992 1.0000
9.750 0.7682 0.07082 0.06385 0.0381 0.1005 1.0000
10.000 0.7183 0.07443 0.06778 0.0413 0.1076 1.0000
10.250 0.6919 0.07920 0.07262 0.0412 0.1105 1.0000
10.500 0.6791 0.08439 0.07781 0.0403 0.1132 1.0000
10.750 0.6355 0.09359 0.08702 0.0339 0.1264 1.0000
11.000 0.5321 0.09353 0.08728 0.0346 0.1280 1.0000
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