EPPLER E836 HYDROFOIL AIRFOIL (e836-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E836 HYDROFOIL AIRFOIL (e836-il) Reynolds number: 500,000 Max Cl/Cd: 49.86 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e836-il-500000-n5.txt Download as CSV file: xf-e836-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.8119 0.07702 0.07443 -0.0329 1.0000 0.0030
-13.750 -0.8312 0.06918 0.06641 -0.0378 1.0000 0.0030
-13.500 -0.8539 0.06200 0.05905 -0.0417 1.0000 0.0029
-13.250 -0.8701 0.05667 0.05355 -0.0438 1.0000 0.0029
-13.000 -0.8882 0.05159 0.04826 -0.0450 1.0000 0.0029
-12.750 -0.9016 0.04749 0.04396 -0.0453 1.0000 0.0030
-12.500 -0.9114 0.04408 0.04036 -0.0449 1.0000 0.0030
-12.250 -0.9237 0.04055 0.03660 -0.0438 1.0000 0.0030
-12.000 -0.9271 0.03809 0.03395 -0.0425 1.0000 0.0031
-11.750 -0.9276 0.03598 0.03165 -0.0410 1.0000 0.0031
-11.500 -0.9280 0.03386 0.02931 -0.0393 1.0000 0.0032
-11.250 -0.9283 0.03168 0.02692 -0.0372 1.0000 0.0032
-11.000 -0.9238 0.03002 0.02510 -0.0353 1.0000 0.0032
-10.750 -0.9288 0.02697 0.02171 -0.0321 1.0000 0.0034
-10.500 -0.9209 0.02554 0.02012 -0.0301 1.0000 0.0034
-10.250 -0.9155 0.02387 0.01828 -0.0276 1.0000 0.0037
-10.000 -0.9060 0.02272 0.01702 -0.0254 1.0000 0.0038
-9.750 -0.8960 0.02171 0.01590 -0.0232 1.0000 0.0039
-9.500 -0.8793 0.02096 0.01509 -0.0221 0.9899 0.0042
-9.250 -0.8501 0.01988 0.01388 -0.0237 0.9641 0.0044
-9.000 -0.8192 0.01926 0.01318 -0.0253 0.9456 0.0050
-8.750 -0.7982 0.01841 0.01217 -0.0248 0.9263 0.0052
-8.500 -0.7828 0.01774 0.01136 -0.0229 0.9102 0.0056
-8.250 -0.7673 0.01707 0.01055 -0.0211 0.8982 0.0059
-8.000 -0.7511 0.01643 0.00977 -0.0193 0.8879 0.0062
-7.750 -0.7330 0.01589 0.00912 -0.0178 0.8795 0.0064
-7.500 -0.7180 0.01507 0.00817 -0.0158 0.8720 0.0075
-7.250 -0.6984 0.01455 0.00759 -0.0146 0.8651 0.0086
-7.000 -0.6778 0.01414 0.00709 -0.0135 0.8591 0.0101
-6.750 -0.6554 0.01381 0.00666 -0.0127 0.8535 0.0119
-6.500 -0.6348 0.01334 0.00617 -0.0117 0.8480 0.0155
-6.250 -0.6121 0.01303 0.00578 -0.0110 0.8433 0.0182
-6.000 -0.5898 0.01264 0.00537 -0.0102 0.8382 0.0229
-5.750 -0.5672 0.01229 0.00501 -0.0095 0.8337 0.0309
-5.500 -0.5460 0.01182 0.00464 -0.0086 0.8294 0.0533
-5.250 -0.5247 0.01133 0.00429 -0.0077 0.8247 0.0856
-5.000 -0.5025 0.01092 0.00397 -0.0070 0.8205 0.1163
-4.750 -0.4803 0.01052 0.00365 -0.0062 0.8168 0.1509
-4.500 -0.4584 0.01004 0.00337 -0.0055 0.8123 0.1989
-4.250 -0.4367 0.00956 0.00308 -0.0047 0.8082 0.2527
-4.000 -0.4171 0.00895 0.00277 -0.0036 0.8045 0.3321
-3.750 -0.3994 0.00820 0.00245 -0.0021 0.8004 0.4346
-3.500 -0.3800 0.00762 0.00224 -0.0008 0.7962 0.5244
-3.250 -0.3571 0.00733 0.00214 0.0000 0.7925 0.5831
-3.000 -0.3317 0.00720 0.00204 0.0005 0.7893 0.6150
-2.750 -0.3049 0.00712 0.00199 0.0006 0.7854 0.6355
-2.500 -0.2778 0.00707 0.00194 0.0007 0.7816 0.6528
-2.250 -0.2508 0.00703 0.00191 0.0008 0.7781 0.6685
-2.000 -0.2232 0.00701 0.00185 0.0007 0.7749 0.6805
-1.750 -0.1955 0.00699 0.00183 0.0007 0.7709 0.6906
-1.500 -0.1678 0.00697 0.00182 0.0006 0.7670 0.7000
-1.250 -0.1400 0.00697 0.00179 0.0006 0.7635 0.7092
-1.000 -0.1121 0.00697 0.00178 0.0005 0.7599 0.7173
-0.750 -0.0841 0.00696 0.00178 0.0004 0.7556 0.7240
-0.500 -0.0561 0.00696 0.00178 0.0003 0.7515 0.7312
0.000 0.0000 0.00696 0.00178 0.0000 0.7428 0.7428
0.500 0.0560 0.00696 0.00177 -0.0002 0.7311 0.7515
0.750 0.0840 0.00696 0.00178 -0.0003 0.7240 0.7556
1.000 0.1120 0.00697 0.00178 -0.0005 0.7173 0.7599
1.250 0.1399 0.00697 0.00179 -0.0006 0.7092 0.7635
1.500 0.1677 0.00697 0.00182 -0.0006 0.7001 0.7670
1.750 0.1954 0.00699 0.00183 -0.0007 0.6906 0.7709
2.000 0.2231 0.00701 0.00185 -0.0007 0.6805 0.7749
2.250 0.2507 0.00703 0.00190 -0.0007 0.6684 0.7781
2.500 0.2778 0.00707 0.00194 -0.0006 0.6530 0.7816
2.750 0.3048 0.00712 0.00199 -0.0006 0.6354 0.7854
3.000 0.3316 0.00721 0.00204 -0.0004 0.6145 0.7893
3.250 0.3569 0.00734 0.00213 0.0000 0.5822 0.7925
3.500 0.3799 0.00762 0.00224 0.0008 0.5245 0.7962
3.750 0.3991 0.00821 0.00246 0.0022 0.4332 0.8005
4.000 0.4171 0.00894 0.00277 0.0036 0.3338 0.8045
4.250 0.4366 0.00956 0.00308 0.0047 0.2531 0.8082
4.500 0.4581 0.01005 0.00337 0.0055 0.1977 0.8124
4.750 0.4801 0.01052 0.00365 0.0063 0.1512 0.8168
5.000 0.5023 0.01092 0.00397 0.0070 0.1161 0.8205
5.250 0.5245 0.01133 0.00429 0.0078 0.0858 0.8247
5.500 0.5454 0.01184 0.00464 0.0087 0.0521 0.8295
5.750 0.5671 0.01227 0.00501 0.0095 0.0317 0.8337
6.000 0.5894 0.01264 0.00537 0.0103 0.0227 0.8383
6.250 0.6118 0.01303 0.00577 0.0110 0.0182 0.8433
6.500 0.6345 0.01334 0.00616 0.0118 0.0156 0.8480
6.750 0.6550 0.01381 0.00666 0.0128 0.0119 0.8535
7.000 0.6774 0.01413 0.00709 0.0136 0.0103 0.8591
7.250 0.6981 0.01454 0.00757 0.0146 0.0085 0.8651
7.500 0.7174 0.01508 0.00818 0.0159 0.0073 0.8720
7.750 0.7329 0.01586 0.00909 0.0179 0.0064 0.8795
8.000 0.7508 0.01641 0.00976 0.0193 0.0061 0.8879
8.250 0.7670 0.01706 0.01054 0.0211 0.0059 0.8982
8.500 0.7825 0.01772 0.01134 0.0230 0.0056 0.9103
8.750 0.7974 0.01844 0.01219 0.0249 0.0053 0.9264
9.000 0.8204 0.01908 0.01298 0.0251 0.0048 0.9451
9.250 0.8495 0.01998 0.01399 0.0238 0.0044 0.9646
9.500 0.8800 0.02085 0.01495 0.0220 0.0041 0.9896
9.750 0.8953 0.02177 0.01597 0.0233 0.0039 1.0000
10.000 0.9053 0.02279 0.01710 0.0256 0.0038 1.0000
10.250 0.9145 0.02397 0.01839 0.0278 0.0037 1.0000
10.500 0.9236 0.02523 0.01978 0.0298 0.0036 1.0000
10.750 0.9267 0.02722 0.02199 0.0324 0.0034 1.0000
11.000 0.9243 0.02995 0.02502 0.0352 0.0032 1.0000
11.250 0.9267 0.03190 0.02716 0.0373 0.0032 1.0000
11.500 0.9306 0.03357 0.02902 0.0391 0.0032 1.0000
11.750 0.9275 0.03599 0.03167 0.0410 0.0032 1.0000
12.000 0.9263 0.03820 0.03407 0.0426 0.0031 1.0000
12.250 0.9206 0.04091 0.03698 0.0439 0.0031 1.0000
12.500 0.9166 0.04354 0.03979 0.0447 0.0030 1.0000
12.750 0.8994 0.04780 0.04429 0.0453 0.0030 1.0000
13.000 0.8875 0.05169 0.04836 0.0450 0.0030 1.0000
13.250 0.8716 0.05649 0.05336 0.0438 0.0030 1.0000
13.500 0.8524 0.06229 0.05935 0.0415 0.0030 1.0000
13.750 0.8324 0.06908 0.06631 0.0378 0.0030 1.0000
14.000 0.8062 0.07839 0.07582 0.0319 0.0030 1.0000
14.250 0.7837 0.08871 0.08629 0.0252 0.0030 1.0000
14.750 0.6426 0.10684 0.10472 0.0147 0.0033 1.0000
15.000 0.6186 0.11667 0.11462 0.0098 0.0034 1.0000
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