EPPLER E836 HYDROFOIL AIRFOIL (e836-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E836 HYDROFOIL AIRFOIL (e836-il) Reynolds number: 200,000 Max Cl/Cd: 45.63 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e836-il-200000.txt Download as CSV file: xf-e836-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.7690 0.03566 0.03098 -0.0331 1.0000 0.0353
-9.000 -0.8237 0.04108 0.03534 -0.0244 1.0000 0.0269
-8.750 -0.8246 0.03752 0.03152 -0.0208 1.0000 0.0259
-8.500 -0.8267 0.03491 0.02864 -0.0163 1.0000 0.0251
-8.250 -0.8325 0.03313 0.02664 -0.0110 1.0000 0.0246
-8.000 -0.8340 0.03133 0.02458 -0.0062 1.0000 0.0243
-7.750 -0.8293 0.02950 0.02248 -0.0024 1.0000 0.0243
-7.500 -0.8026 0.02713 0.01982 -0.0025 0.9978 0.0247
-7.250 -0.7684 0.02511 0.01756 -0.0039 0.9949 0.0261
-7.000 -0.7357 0.02367 0.01592 -0.0053 0.9913 0.0286
-6.750 -0.7067 0.02150 0.01374 -0.0062 0.9877 0.0317
-6.500 -0.6746 0.02018 0.01235 -0.0077 0.9839 0.0365
-6.250 -0.6504 0.01885 0.01101 -0.0080 0.9780 0.0440
-6.000 -0.6234 0.01763 0.00978 -0.0086 0.9728 0.0569
-5.750 -0.6043 0.01578 0.00846 -0.0083 0.9670 0.1334
-5.500 -0.5904 0.01410 0.00764 -0.0073 0.9598 0.2875
-5.250 -0.5700 0.01264 0.00703 -0.0072 0.9557 0.4578
-5.000 -0.5561 0.01218 0.00701 -0.0046 0.9478 0.5635
-4.750 -0.5262 0.01218 0.00722 -0.0046 0.9441 0.6440
-4.500 -0.4939 0.01245 0.00747 -0.0050 0.9411 0.6878
-4.250 -0.4707 0.01273 0.00770 -0.0037 0.9347 0.7078
-4.000 -0.4389 0.01301 0.00788 -0.0041 0.9309 0.7273
-3.750 -0.4051 0.01327 0.00804 -0.0049 0.9282 0.7435
-3.500 -0.3802 0.01357 0.00829 -0.0039 0.9225 0.7545
-3.250 -0.3501 0.01382 0.00848 -0.0039 0.9183 0.7654
-3.000 -0.3181 0.01402 0.00858 -0.0044 0.9151 0.7762
-2.750 -0.2951 0.01416 0.00865 -0.0034 0.9097 0.7869
-2.500 -0.2646 0.01442 0.00889 -0.0034 0.9052 0.7933
-2.250 -0.2361 0.01450 0.00887 -0.0034 0.9015 0.8026
-2.000 -0.2062 0.01471 0.00906 -0.0034 0.8977 0.8091
-1.750 -0.1846 0.01478 0.00909 -0.0022 0.8914 0.8172
-1.500 -0.1535 0.01489 0.00917 -0.0026 0.8879 0.8228
-1.250 -0.1302 0.01490 0.00913 -0.0018 0.8831 0.8305
-1.000 -0.1033 0.01504 0.00927 -0.0015 0.8776 0.8355
-0.750 -0.0791 0.01497 0.00914 -0.0009 0.8733 0.8434
-0.500 -0.0505 0.01508 0.00926 -0.0009 0.8687 0.8472
-0.250 -0.0260 0.01513 0.00930 -0.0003 0.8628 0.8528
0.000 0.0000 0.01503 0.00918 0.0000 0.8588 0.8588
0.250 0.0259 0.01513 0.00930 0.0003 0.8528 0.8629
0.500 0.0505 0.01508 0.00926 0.0009 0.8472 0.8687
0.750 0.0791 0.01497 0.00915 0.0009 0.8435 0.8733
1.000 0.1032 0.01505 0.00927 0.0015 0.8355 0.8776
1.250 0.1302 0.01490 0.00913 0.0018 0.8305 0.8831
1.500 0.1535 0.01489 0.00917 0.0026 0.8228 0.8879
1.750 0.1846 0.01478 0.00909 0.0022 0.8172 0.8914
2.000 0.2062 0.01471 0.00906 0.0034 0.8091 0.8977
2.250 0.2361 0.01450 0.00887 0.0034 0.8026 0.9015
2.500 0.2647 0.01443 0.00889 0.0034 0.7933 0.9052
2.750 0.2952 0.01417 0.00865 0.0034 0.7869 0.9096
3.000 0.3181 0.01402 0.00858 0.0044 0.7762 0.9151
3.250 0.3501 0.01382 0.00848 0.0039 0.7653 0.9182
3.500 0.3803 0.01357 0.00829 0.0039 0.7544 0.9225
3.750 0.4050 0.01327 0.00804 0.0049 0.7434 0.9282
4.000 0.4389 0.01301 0.00787 0.0041 0.7270 0.9309
4.250 0.4709 0.01273 0.00771 0.0037 0.7078 0.9346
4.500 0.4946 0.01246 0.00748 0.0049 0.6877 0.9409
4.750 0.5261 0.01218 0.00722 0.0046 0.6435 0.9441
5.000 0.5562 0.01219 0.00701 0.0046 0.5632 0.9477
5.250 0.5706 0.01266 0.00703 0.0071 0.4560 0.9554
5.500 0.5903 0.01411 0.00764 0.0073 0.2866 0.9597
5.750 0.6039 0.01583 0.00848 0.0083 0.1301 0.9670
6.000 0.6233 0.01764 0.00979 0.0087 0.0568 0.9728
6.250 0.6506 0.01882 0.01098 0.0079 0.0432 0.9779
6.500 0.6746 0.02018 0.01235 0.0077 0.0362 0.9838
6.750 0.7067 0.02149 0.01373 0.0062 0.0320 0.9876
7.000 0.7348 0.02415 0.01640 0.0055 0.0281 0.9909
7.250 0.7681 0.02517 0.01761 0.0040 0.0262 0.9948
7.500 0.8024 0.02714 0.01982 0.0026 0.0247 0.9977
7.750 0.8295 0.02953 0.02252 0.0024 0.0241 1.0000
8.000 0.8345 0.03138 0.02463 0.0061 0.0244 1.0000
8.250 0.8331 0.03317 0.02667 0.0108 0.0246 1.0000
8.500 0.8272 0.03492 0.02865 0.0162 0.0251 1.0000
8.750 0.8248 0.03746 0.03145 0.0208 0.0258 1.0000
9.000 0.8236 0.04100 0.03527 0.0245 0.0268 1.0000
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Polar data table (+)
Polar graphs
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