EPPLER E837 HYDROFOIL AIRFOIL (e837-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER E837 HYDROFOIL AIRFOIL (e837-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.09 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e837-il-1000000.txt Download as CSV file: xf-e837-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -0.9292 0.14448 0.14221 0.0064 1.0000 0.0051
-19.500 -0.9436 0.13667 0.13430 0.0018 1.0000 0.0050
-19.250 -0.9632 0.12795 0.12543 -0.0032 1.0000 0.0050
-19.000 -0.9809 0.11993 0.11727 -0.0077 1.0000 0.0051
-18.750 -0.9924 0.11336 0.11058 -0.0114 1.0000 0.0051
-18.500 -1.0090 0.10605 0.10313 -0.0153 1.0000 0.0051
-18.250 -1.0153 0.10078 0.09777 -0.0182 1.0000 0.0051
-18.000 -1.0322 0.09391 0.09075 -0.0215 1.0000 0.0051
-17.750 -1.0411 0.08854 0.08526 -0.0241 1.0000 0.0051
-17.500 -1.0500 0.08331 0.07991 -0.0265 1.0000 0.0051
-17.250 -1.0588 0.07837 0.07485 -0.0286 1.0000 0.0051
-17.000 -1.0646 0.07395 0.07031 -0.0304 1.0000 0.0052
-16.750 -1.0685 0.06994 0.06620 -0.0319 1.0000 0.0052
-16.500 -1.0738 0.06587 0.06201 -0.0332 1.0000 0.0053
-16.250 -1.0757 0.06241 0.05845 -0.0343 1.0000 0.0053
-16.000 -1.0762 0.05917 0.05511 -0.0352 1.0000 0.0054
-15.750 -1.0784 0.05588 0.05172 -0.0358 1.0000 0.0054
-15.500 -1.0744 0.05336 0.04911 -0.0364 1.0000 0.0055
-15.250 -1.0770 0.05027 0.04592 -0.0367 1.0000 0.0054
-15.000 -1.0677 0.04846 0.04405 -0.0371 1.0000 0.0055
-14.750 -1.0871 0.04391 0.03932 -0.0367 1.0000 0.0057
-14.500 -1.0904 0.04108 0.03640 -0.0364 1.0000 0.0058
-14.250 -1.0860 0.03909 0.03434 -0.0362 1.0000 0.0059
-14.000 -1.0857 0.03680 0.03198 -0.0356 1.0000 0.0061
-13.750 -1.0816 0.03490 0.03003 -0.0351 1.0000 0.0063
-13.500 -1.0720 0.03351 0.02860 -0.0348 1.0000 0.0066
-13.250 -1.0688 0.03163 0.02663 -0.0339 1.0000 0.0065
-13.000 -1.0580 0.03039 0.02536 -0.0334 1.0000 0.0069
-12.750 -1.0538 0.02867 0.02356 -0.0324 1.0000 0.0070
-12.500 -1.0442 0.02740 0.02224 -0.0316 1.0000 0.0072
-12.250 -1.0372 0.02598 0.02075 -0.0306 1.0000 0.0073
-12.000 -1.0267 0.02484 0.01955 -0.0297 1.0000 0.0075
-11.750 -1.0170 0.02369 0.01834 -0.0286 1.0000 0.0076
-11.500 -1.0070 0.02258 0.01718 -0.0275 1.0000 0.0078
-11.250 -1.0058 0.02095 0.01547 -0.0255 1.0000 0.0083
-11.000 -0.9967 0.01990 0.01438 -0.0240 1.0000 0.0087
-10.750 -0.9861 0.01898 0.01343 -0.0226 1.0000 0.0089
-10.500 -0.9645 0.01817 0.01258 -0.0231 0.9670 0.0096
-10.250 -0.9283 0.01747 0.01168 -0.0263 0.9022 0.0103
-9.750 -0.9147 0.01614 0.01004 -0.0207 0.8448 0.0120
-9.500 -0.9030 0.01565 0.00947 -0.0186 0.8292 0.0128
-9.250 -0.8890 0.01526 0.00900 -0.0166 0.8167 0.0140
-9.000 -0.8792 0.01473 0.00838 -0.0139 0.8056 0.0153
-8.750 -0.8675 0.01430 0.00791 -0.0113 0.7960 0.0173
-8.500 -0.8496 0.01397 0.00751 -0.0099 0.7880 0.0190
-8.250 -0.8338 0.01346 0.00698 -0.0082 0.7801 0.0232
-8.000 -0.8154 0.01303 0.00655 -0.0068 0.7734 0.0289
-7.750 -0.7974 0.01254 0.00610 -0.0055 0.7668 0.0408
-7.500 -0.7795 0.01203 0.00566 -0.0041 0.7608 0.0584
-7.250 -0.7602 0.01153 0.00525 -0.0030 0.7550 0.0798
-7.000 -0.7414 0.01099 0.00483 -0.0018 0.7494 0.1087
-6.750 -0.7217 0.01047 0.00445 -0.0007 0.7445 0.1417
-6.500 -0.7018 0.00991 0.00407 0.0003 0.7393 0.1807
-6.250 -0.6820 0.00934 0.00370 0.0013 0.7343 0.2278
-6.000 -0.6613 0.00881 0.00335 0.0022 0.7298 0.2750
-5.750 -0.6398 0.00827 0.00302 0.0030 0.7254 0.3252
-5.500 -0.6177 0.00779 0.00273 0.0037 0.7209 0.3764
-5.250 -0.5943 0.00742 0.00251 0.0042 0.7165 0.4219
-5.000 -0.5694 0.00713 0.00235 0.0045 0.7125 0.4626
-4.750 -0.5429 0.00694 0.00222 0.0046 0.7084 0.4872
-4.500 -0.5156 0.00684 0.00212 0.0046 0.7043 0.5049
-4.250 -0.4880 0.00678 0.00205 0.0045 0.7002 0.5215
-4.000 -0.4600 0.00669 0.00197 0.0044 0.6965 0.5339
-3.750 -0.4318 0.00662 0.00191 0.0042 0.6926 0.5436
-3.500 -0.4032 0.00661 0.00184 0.0039 0.6887 0.5525
-3.250 -0.3751 0.00657 0.00179 0.0038 0.6848 0.5611
-3.000 -0.3463 0.00653 0.00175 0.0035 0.6812 0.5690
-2.750 -0.3177 0.00649 0.00171 0.0033 0.6773 0.5762
-2.500 -0.2888 0.00650 0.00166 0.0030 0.6735 0.5825
-2.250 -0.2604 0.00648 0.00163 0.0028 0.6698 0.5886
-2.000 -0.2313 0.00646 0.00161 0.0024 0.6661 0.5949
-1.750 -0.2025 0.00643 0.00158 0.0021 0.6623 0.6007
-1.500 -0.1738 0.00643 0.00156 0.0019 0.6584 0.6064
-1.250 -0.1447 0.00646 0.00154 0.0015 0.6547 0.6114
-1.000 -0.1159 0.00641 0.00153 0.0013 0.6509 0.6164
-0.750 -0.0869 0.00641 0.00152 0.0009 0.6469 0.6214
-0.500 -0.0578 0.00644 0.00151 0.0006 0.6430 0.6259
-0.250 -0.0291 0.00642 0.00151 0.0003 0.6391 0.6306
0.000 0.0000 0.00640 0.00151 0.0000 0.6349 0.6349
0.250 0.0291 0.00642 0.00151 -0.0003 0.6306 0.6391
0.500 0.0578 0.00644 0.00151 -0.0006 0.6259 0.6430
0.750 0.0868 0.00641 0.00152 -0.0009 0.6214 0.6469
1.000 0.1159 0.00641 0.00153 -0.0012 0.6164 0.6509
1.250 0.1447 0.00646 0.00154 -0.0015 0.6114 0.6547
1.500 0.1737 0.00643 0.00156 -0.0019 0.6064 0.6584
1.750 0.2025 0.00643 0.00158 -0.0021 0.6008 0.6622
2.000 0.2312 0.00646 0.00161 -0.0024 0.5949 0.6661
2.250 0.2604 0.00648 0.00163 -0.0027 0.5886 0.6698
2.500 0.2888 0.00650 0.00166 -0.0030 0.5825 0.6735
2.750 0.3177 0.00649 0.00171 -0.0033 0.5762 0.6773
3.000 0.3462 0.00653 0.00175 -0.0035 0.5690 0.6812
3.250 0.3750 0.00657 0.00179 -0.0038 0.5612 0.6848
3.750 0.4317 0.00663 0.00191 -0.0042 0.5435 0.6926
4.000 0.4600 0.00669 0.00197 -0.0044 0.5342 0.6965
4.250 0.4880 0.00678 0.00205 -0.0045 0.5215 0.7002
4.500 0.5155 0.00684 0.00212 -0.0046 0.5050 0.7043
4.750 0.5429 0.00694 0.00222 -0.0046 0.4875 0.7084
5.000 0.5694 0.00712 0.00235 -0.0045 0.4631 0.7125
5.250 0.5943 0.00742 0.00251 -0.0042 0.4220 0.7165
5.500 0.6176 0.00779 0.00273 -0.0037 0.3765 0.7208
5.750 0.6398 0.00827 0.00302 -0.0030 0.3250 0.7254
6.000 0.6612 0.00881 0.00335 -0.0022 0.2748 0.7298
6.250 0.6820 0.00934 0.00369 -0.0013 0.2279 0.7344
6.500 0.7018 0.00991 0.00407 -0.0003 0.1810 0.7393
6.750 0.7217 0.01047 0.00445 0.0007 0.1418 0.7445
7.000 0.7414 0.01099 0.00483 0.0018 0.1089 0.7495
7.250 0.7604 0.01151 0.00524 0.0029 0.0808 0.7550
7.500 0.7794 0.01204 0.00566 0.0041 0.0581 0.7608
7.750 0.7972 0.01254 0.00610 0.0055 0.0404 0.7669
8.000 0.8153 0.01303 0.00655 0.0068 0.0289 0.7735
8.250 0.8336 0.01347 0.00699 0.0082 0.0230 0.7801
8.500 0.8498 0.01396 0.00750 0.0099 0.0191 0.7880
8.750 0.8675 0.01430 0.00791 0.0113 0.0175 0.7960
9.000 0.8795 0.01472 0.00837 0.0138 0.0155 0.8056
9.250 0.8898 0.01523 0.00896 0.0165 0.0139 0.8168
9.500 0.9028 0.01566 0.00948 0.0186 0.0128 0.8294
9.750 0.9148 0.01614 0.01004 0.0207 0.0119 0.8449
10.250 0.9288 0.01745 0.01165 0.0263 0.0104 0.9024
10.500 0.9647 0.01819 0.01261 0.0230 0.0097 0.9676
10.750 0.9864 0.01898 0.01343 0.0225 0.0090 1.0000
11.000 0.9981 0.01982 0.01429 0.0239 0.0086 1.0000
11.250 1.0058 0.02096 0.01547 0.0255 0.0082 1.0000
11.500 1.0085 0.02249 0.01708 0.0273 0.0078 1.0000
11.750 1.0171 0.02369 0.01834 0.0286 0.0076 1.0000
12.000 1.0299 0.02463 0.01932 0.0294 0.0074 1.0000
12.250 1.0383 0.02592 0.02068 0.0305 0.0073 1.0000
12.500 1.0455 0.02733 0.02216 0.0315 0.0072 1.0000
12.750 1.0549 0.02861 0.02349 0.0323 0.0069 1.0000
13.000 1.0601 0.03025 0.02521 0.0333 0.0069 1.0000
13.250 1.0680 0.03172 0.02674 0.0339 0.0067 1.0000
13.500 1.0783 0.03302 0.02808 0.0344 0.0064 1.0000
13.750 1.0845 0.03468 0.02979 0.0349 0.0062 1.0000
14.000 1.0839 0.03701 0.03221 0.0357 0.0063 1.0000
14.250 1.0863 0.03910 0.03435 0.0361 0.0058 1.0000
14.500 1.0918 0.04100 0.03632 0.0363 0.0058 1.0000
14.750 1.0933 0.04337 0.03877 0.0365 0.0058 1.0000
15.000 1.0734 0.04793 0.04349 0.0369 0.0055 1.0000
15.250 1.0773 0.05029 0.04595 0.0366 0.0055 1.0000
15.500 1.0771 0.05315 0.04890 0.0363 0.0055 1.0000
15.750 1.0802 0.05578 0.05162 0.0357 0.0053 1.0000
16.000 1.0796 0.05889 0.05483 0.0350 0.0053 1.0000
16.250 1.0777 0.06226 0.05830 0.0341 0.0053 1.0000
16.500 1.0768 0.06562 0.06176 0.0331 0.0052 1.0000
16.750 1.0716 0.06964 0.06589 0.0318 0.0052 1.0000
17.000 1.0655 0.07392 0.07028 0.0303 0.0052 1.0000
17.250 1.0613 0.07815 0.07462 0.0285 0.0051 1.0000
17.500 1.0530 0.08303 0.07962 0.0264 0.0051 1.0000
17.750 1.0423 0.08854 0.08526 0.0239 0.0050 1.0000
18.000 1.0313 0.09421 0.09106 0.0213 0.0051 1.0000
18.250 1.0220 0.09982 0.09678 0.0184 0.0051 1.0000
18.500 1.0102 0.10605 0.10314 0.0151 0.0050 1.0000
18.750 0.9930 0.11348 0.11071 0.0112 0.0051 1.0000
19.000 0.9817 0.12004 0.11738 0.0075 0.0050 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EPPLER E837 HYDROFOIL AIRFOIL (e837-il)