EPPLER E837 HYDROFOIL AIRFOIL (e837-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER E837 HYDROFOIL AIRFOIL (e837-il) Reynolds number: 100,000 Max Cl/Cd: 37.75 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e837-il-100000-n5.txt Download as CSV file: xf-e837-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E837 HYDROFOIL AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.7237 0.12703 0.12197 -0.0104 1.0000 0.0198
-15.750 -0.7704 0.11090 0.10560 -0.0203 1.0000 0.0189
-15.500 -0.7980 0.10099 0.09550 -0.0263 1.0000 0.0187
-15.250 -0.8191 0.09319 0.08748 -0.0307 1.0000 0.0187
-15.000 -0.8366 0.08657 0.08063 -0.0340 1.0000 0.0186
-14.750 -0.8501 0.08102 0.07488 -0.0365 1.0000 0.0187
-14.500 -0.8615 0.07598 0.06962 -0.0384 1.0000 0.0188
-14.250 -0.8701 0.07160 0.06504 -0.0397 1.0000 0.0190
-14.000 -0.8761 0.06766 0.06091 -0.0407 1.0000 0.0192
-13.750 -0.8802 0.06405 0.05710 -0.0412 1.0000 0.0196
-13.500 -0.8816 0.06078 0.05359 -0.0415 1.0000 0.0201
-13.250 -0.8804 0.05786 0.05047 -0.0415 1.0000 0.0207
-13.000 -0.8772 0.05519 0.04759 -0.0414 1.0000 0.0215
-12.750 -0.8736 0.05274 0.04488 -0.0412 1.0000 0.0227
-12.500 -0.8670 0.05035 0.04244 -0.0408 1.0000 0.0239
-12.250 -0.8602 0.04827 0.04031 -0.0403 1.0000 0.0250
-12.000 -0.8517 0.04636 0.03832 -0.0398 1.0000 0.0261
-11.750 -0.8424 0.04452 0.03639 -0.0391 1.0000 0.0275
-11.500 -0.8329 0.04276 0.03449 -0.0383 1.0000 0.0292
-11.250 -0.8245 0.04100 0.03263 -0.0374 1.0000 0.0313
-11.000 -0.8198 0.03912 0.03075 -0.0366 1.0000 0.0337
-10.750 -0.8125 0.03749 0.02903 -0.0358 1.0000 0.0368
-10.500 -0.8044 0.03593 0.02735 -0.0348 1.0000 0.0396
-10.250 -0.8007 0.03413 0.02558 -0.0336 1.0000 0.0436
-10.000 -0.7939 0.03263 0.02403 -0.0325 1.0000 0.0489
-9.750 -0.7896 0.03101 0.02241 -0.0310 1.0000 0.0541
-9.500 -0.7842 0.02954 0.02093 -0.0295 1.0000 0.0618
-9.250 -0.7806 0.02807 0.01954 -0.0278 1.0000 0.0728
-9.000 -0.7772 0.02671 0.01828 -0.0258 1.0000 0.0881
-8.750 -0.7761 0.02545 0.01717 -0.0234 1.0000 0.1060
-8.500 -0.7781 0.02443 0.01630 -0.0201 1.0000 0.1266
-8.250 -0.7707 0.02323 0.01528 -0.0189 0.9773 0.1597
-8.000 -0.7525 0.02179 0.01410 -0.0197 0.9519 0.2130
-7.750 -0.7382 0.02043 0.01307 -0.0194 0.9323 0.2754
-7.500 -0.7253 0.01940 0.01236 -0.0181 0.9163 0.3397
-7.250 -0.7102 0.01883 0.01202 -0.0164 0.9029 0.3966
-7.000 -0.6916 0.01858 0.01184 -0.0149 0.8916 0.4408
-6.750 -0.6711 0.01849 0.01169 -0.0136 0.8820 0.4752
-6.500 -0.6513 0.01847 0.01158 -0.0121 0.8717 0.5021
-6.250 -0.6282 0.01857 0.01159 -0.0110 0.8634 0.5233
-6.000 -0.6059 0.01861 0.01150 -0.0099 0.8552 0.5415
-5.750 -0.5832 0.01868 0.01142 -0.0089 0.8474 0.5572
-5.500 -0.5591 0.01879 0.01137 -0.0080 0.8403 0.5708
-5.250 -0.5341 0.01891 0.01139 -0.0073 0.8334 0.5824
-5.000 -0.5094 0.01898 0.01132 -0.0066 0.8267 0.5932
-4.750 -0.4860 0.01896 0.01115 -0.0059 0.8206 0.6040
-4.500 -0.4591 0.01910 0.01118 -0.0055 0.8141 0.6122
-4.250 -0.4339 0.01911 0.01107 -0.0049 0.8090 0.6210
-4.000 -0.4097 0.01912 0.01097 -0.0044 0.8022 0.6296
-3.750 -0.3833 0.01916 0.01092 -0.0040 0.7968 0.6363
-3.500 -0.3587 0.01912 0.01075 -0.0035 0.7915 0.6440
-3.250 -0.3330 0.01913 0.01069 -0.0032 0.7855 0.6501
-3.000 -0.3070 0.01911 0.01058 -0.0029 0.7807 0.6564
-2.750 -0.2828 0.01904 0.01042 -0.0025 0.7751 0.6632
-2.500 -0.2560 0.01908 0.01040 -0.0023 0.7697 0.6682
-2.250 -0.2325 0.01892 0.01011 -0.0018 0.7653 0.6756
-2.000 -0.2055 0.01898 0.01017 -0.0017 0.7596 0.6797
-1.750 -0.1796 0.01896 0.01010 -0.0015 0.7545 0.6849
-1.500 -0.1550 0.01882 0.00986 -0.0011 0.7504 0.6914
-1.250 -0.1285 0.01888 0.00994 -0.0010 0.7447 0.6953
-1.000 -0.1028 0.01886 0.00988 -0.0008 0.7396 0.7004
-0.750 -0.0775 0.01875 0.00970 -0.0005 0.7357 0.7064
-0.500 -0.0514 0.01882 0.00980 -0.0004 0.7300 0.7102
-0.250 -0.0258 0.01881 0.00978 -0.0002 0.7249 0.7154
0.000 0.0000 0.01873 0.00964 0.0000 0.7211 0.7211
0.250 0.0258 0.01881 0.00978 0.0002 0.7154 0.7249
0.500 0.0514 0.01882 0.00980 0.0004 0.7102 0.7300
0.750 0.0775 0.01875 0.00970 0.0005 0.7064 0.7357
1.000 0.1028 0.01886 0.00988 0.0008 0.7004 0.7396
1.250 0.1285 0.01888 0.00994 0.0010 0.6953 0.7447
1.500 0.1550 0.01882 0.00986 0.0011 0.6914 0.7504
1.750 0.1796 0.01896 0.01010 0.0015 0.6849 0.7545
2.000 0.2055 0.01897 0.01017 0.0017 0.6797 0.7597
2.250 0.2325 0.01892 0.01012 0.0018 0.6756 0.7653
2.500 0.2560 0.01907 0.01040 0.0023 0.6682 0.7697
2.750 0.2829 0.01904 0.01042 0.0025 0.6632 0.7751
3.000 0.3070 0.01911 0.01058 0.0029 0.6564 0.7807
3.250 0.3330 0.01913 0.01069 0.0032 0.6501 0.7855
3.500 0.3587 0.01912 0.01075 0.0035 0.6439 0.7915
3.750 0.3833 0.01916 0.01092 0.0040 0.6363 0.7968
4.000 0.4097 0.01912 0.01097 0.0044 0.6296 0.8022
4.250 0.4340 0.01911 0.01106 0.0049 0.6210 0.8090
4.500 0.4592 0.01910 0.01118 0.0055 0.6123 0.8141
4.750 0.4860 0.01896 0.01115 0.0059 0.6040 0.8206
5.000 0.5095 0.01898 0.01132 0.0066 0.5932 0.8268
5.250 0.5342 0.01891 0.01139 0.0073 0.5824 0.8334
5.500 0.5592 0.01879 0.01137 0.0080 0.5709 0.8403
5.750 0.5833 0.01868 0.01142 0.0088 0.5572 0.8474
6.000 0.6060 0.01861 0.01149 0.0099 0.5415 0.8552
6.250 0.6283 0.01857 0.01159 0.0110 0.5234 0.8634
6.500 0.6514 0.01847 0.01158 0.0121 0.5022 0.8717
6.750 0.6713 0.01849 0.01169 0.0135 0.4753 0.8820
7.000 0.6917 0.01857 0.01183 0.0149 0.4408 0.8917
7.250 0.7104 0.01882 0.01201 0.0164 0.3966 0.9030
7.500 0.7256 0.01940 0.01236 0.0181 0.3398 0.9164
7.750 0.7386 0.02042 0.01307 0.0194 0.2757 0.9323
8.000 0.7528 0.02180 0.01410 0.0196 0.2129 0.9520
8.250 0.7711 0.02324 0.01528 0.0188 0.1592 0.9775
8.500 0.7783 0.02443 0.01629 0.0201 0.1260 1.0000
8.750 0.7766 0.02544 0.01716 0.0233 0.1058 1.0000
9.000 0.7776 0.02671 0.01828 0.0257 0.0880 1.0000
9.250 0.7811 0.02807 0.01955 0.0277 0.0725 1.0000
9.500 0.7848 0.02954 0.02092 0.0294 0.0619 1.0000
9.750 0.7904 0.03099 0.02240 0.0309 0.0542 1.0000
10.000 0.7947 0.03262 0.02402 0.0324 0.0485 1.0000
10.250 0.8015 0.03413 0.02558 0.0335 0.0436 1.0000
10.500 0.8050 0.03594 0.02735 0.0347 0.0399 1.0000
10.750 0.8134 0.03747 0.02902 0.0357 0.0363 1.0000
11.000 0.8207 0.03912 0.03075 0.0365 0.0336 1.0000
11.250 0.8251 0.04105 0.03267 0.0373 0.0311 1.0000
11.500 0.8340 0.04275 0.03448 0.0381 0.0291 1.0000
11.750 0.8435 0.04451 0.03638 0.0389 0.0274 1.0000
12.000 0.8527 0.04637 0.03833 0.0396 0.0260 1.0000
12.250 0.8611 0.04829 0.04033 0.0402 0.0249 1.0000
12.500 0.8673 0.05039 0.04246 0.0405 0.0237 1.0000
12.750 0.8745 0.05274 0.04489 0.0411 0.0226 1.0000
13.000 0.8785 0.05519 0.04759 0.0412 0.0215 1.0000
13.250 0.8822 0.05786 0.05047 0.0414 0.0208 1.0000
13.500 0.8823 0.06083 0.05364 0.0413 0.0199 1.0000
13.750 0.8815 0.06406 0.05710 0.0410 0.0196 1.0000
14.000 0.8776 0.06766 0.06091 0.0405 0.0192 1.0000
14.250 0.8716 0.07160 0.06505 0.0395 0.0190 1.0000
14.500 0.8630 0.07604 0.06969 0.0382 0.0189 1.0000
14.750 0.8520 0.08091 0.07475 0.0363 0.0186 1.0000
15.000 0.8379 0.08664 0.08070 0.0337 0.0185 1.0000
15.250 0.8210 0.09314 0.08742 0.0304 0.0186 1.0000
15.500 0.7993 0.10108 0.09559 0.0260 0.0187 1.0000
15.750 0.7721 0.11093 0.10566 0.0201 0.0189 1.0000
16.000 0.7229 0.12783 0.12279 0.0097 0.0198 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EPPLER E837 HYDROFOIL AIRFOIL (e837-il)