Coanda 3 (coanda3-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: Coanda 3 (coanda3-il) Reynolds number: 500,000 Max Cl/Cd: 75.96 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-coanda3-il-500000-n5.txt Download as CSV file: xf-coanda3-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Coanda 3
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4208 0.09145 0.08933 -0.0239 1.0000 0.0069
-8.750 -0.4254 0.08860 0.08651 -0.0236 1.0000 0.0071
-8.500 -0.4324 0.08613 0.08408 -0.0227 1.0000 0.0072
-8.250 -0.4319 0.08242 0.08041 -0.0252 0.9985 0.0072
-8.000 -0.4188 0.07736 0.07534 -0.0320 0.9941 0.0074
-7.750 -0.4015 0.07167 0.06964 -0.0394 0.9896 0.0074
-7.500 -0.3838 0.06580 0.06373 -0.0465 0.9858 0.0075
-7.250 -0.3659 0.05996 0.05783 -0.0528 0.9809 0.0075
-7.000 -0.3436 0.05372 0.05147 -0.0593 0.9775 0.0075
-6.500 -0.3104 0.03451 0.03168 -0.0680 0.9653 0.0050
-6.250 -0.2958 0.02746 0.02412 -0.0682 0.9597 0.0046
-6.000 -0.2748 0.02308 0.01916 -0.0682 0.9569 0.0043
-5.750 -0.2502 0.02002 0.01554 -0.0680 0.9548 0.0041
-5.500 -0.2326 0.01814 0.01328 -0.0658 0.9491 0.0039
-5.250 -0.2067 0.01634 0.01111 -0.0652 0.9462 0.0038
-5.000 -0.1779 0.01495 0.00947 -0.0653 0.9441 0.0040
-4.750 -0.1480 0.01374 0.00804 -0.0656 0.9423 0.0040
-4.500 -0.1220 0.01284 0.00699 -0.0650 0.9385 0.0044
-4.250 -0.0952 0.01201 0.00604 -0.0646 0.9336 0.0047
-4.000 -0.0620 0.01157 0.00548 -0.0655 0.9297 0.0055
-3.750 -0.0349 0.01063 0.00450 -0.0654 0.9247 0.0065
-3.500 -0.0070 0.01011 0.00391 -0.0652 0.9189 0.0070
-3.250 0.0262 0.00966 0.00333 -0.0662 0.9144 0.0077
-3.000 0.0517 0.00935 0.00292 -0.0655 0.9071 0.0090
-2.750 0.0823 0.00898 0.00241 -0.0660 0.9011 0.0114
-2.500 0.1081 0.00873 0.00205 -0.0653 0.8928 0.0154
-2.250 0.1361 0.00836 0.00182 -0.0654 0.8857 0.0652
-2.000 0.1622 0.00831 0.00181 -0.0649 0.8763 0.0776
-1.750 0.1896 0.00830 0.00175 -0.0648 0.8653 0.0830
-1.500 0.2165 0.00824 0.00169 -0.0645 0.8524 0.0895
-1.250 0.2430 0.00818 0.00159 -0.0641 0.8355 0.0928
-1.000 0.2689 0.00813 0.00144 -0.0636 0.8065 0.0947
-0.750 0.2933 0.00818 0.00129 -0.0626 0.7651 0.0966
-0.500 0.3155 0.00829 0.00122 -0.0613 0.7261 0.0992
-0.250 0.3380 0.00837 0.00119 -0.0601 0.6976 0.1027
0.000 0.3610 0.00846 0.00119 -0.0590 0.6734 0.1063
0.250 0.3842 0.00854 0.00119 -0.0580 0.6487 0.1096
0.500 0.4070 0.00864 0.00120 -0.0569 0.6213 0.1130
0.750 0.4296 0.00872 0.00123 -0.0558 0.5935 0.1192
1.250 0.4723 0.00905 0.00134 -0.0532 0.5126 0.1396
1.500 0.4911 0.00931 0.00144 -0.0514 0.4516 0.1664
1.750 0.4883 0.00799 0.00157 -0.0454 0.4168 0.7407
2.250 0.6447 0.00875 0.00249 -0.0689 0.3258 0.9913
2.500 0.6879 0.00915 0.00271 -0.0728 0.2845 0.9978
2.750 0.7201 0.00948 0.00287 -0.0741 0.2443 1.0000
3.000 0.7377 0.01000 0.00308 -0.0723 0.1816 1.0000
3.250 0.7501 0.01099 0.00352 -0.0697 0.0797 1.0000
3.500 0.7659 0.01178 0.00407 -0.0674 0.0141 1.0000
3.750 0.7864 0.01216 0.00455 -0.0658 0.0092 1.0000
4.000 0.8071 0.01253 0.00501 -0.0643 0.0079 1.0000
4.250 0.8276 0.01290 0.00548 -0.0629 0.0067 1.0000
4.500 0.8468 0.01342 0.00605 -0.0613 0.0054 1.0000
4.750 0.8649 0.01406 0.00679 -0.0594 0.0050 1.0000
5.000 0.8830 0.01470 0.00751 -0.0574 0.0046 1.0000
5.250 0.8994 0.01547 0.00837 -0.0552 0.0043 1.0000
5.500 0.9148 0.01632 0.00930 -0.0528 0.0040 1.0000
5.750 0.9294 0.01726 0.01032 -0.0502 0.0039 1.0000
6.000 0.9454 0.01807 0.01122 -0.0481 0.0036 1.0000
6.250 0.9601 0.01902 0.01220 -0.0459 0.0033 1.0000
6.500 0.9762 0.02005 0.01337 -0.0436 0.0026 1.0000
6.750 0.9916 0.02138 0.01481 -0.0413 0.0025 1.0000
7.000 1.0080 0.02301 0.01657 -0.0392 0.0024 1.0000
7.250 1.0249 0.02465 0.01837 -0.0372 0.0022 1.0000
7.500 1.0417 0.02659 0.02049 -0.0352 0.0022 1.0000
7.750 1.0560 0.02851 0.02261 -0.0329 0.0020 1.0000
8.000 1.0684 0.03097 0.02534 -0.0302 0.0021 1.0000
8.250 1.0769 0.03357 0.02824 -0.0269 0.0021 1.0000
8.500 1.0826 0.03620 0.03115 -0.0235 0.0023 1.0000
8.750 1.0838 0.03898 0.03423 -0.0195 0.0023 1.0000
9.000 1.0829 0.04142 0.03692 -0.0156 0.0024 1.0000
9.250 1.0767 0.04400 0.03974 -0.0111 0.0025 1.0000
9.500 1.0645 0.04634 0.04228 -0.0059 0.0026 1.0000
9.750 1.0503 0.04894 0.04508 -0.0012 0.0026 1.0000
10.000 1.0384 0.05139 0.04774 0.0021 0.0027 1.0000
10.250 1.0215 0.05464 0.05118 0.0050 0.0027 1.0000
10.500 1.0060 0.05799 0.05469 0.0065 0.0027 1.0000
10.750 0.9901 0.06182 0.05868 0.0070 0.0028 1.0000
11.000 0.9724 0.06650 0.06352 0.0061 0.0028 1.0000
11.250 0.9536 0.07212 0.06925 0.0037 0.0028 1.0000
11.500 0.9366 0.07833 0.07559 0.0002 0.0028 1.0000
11.750 0.9226 0.08499 0.08238 -0.0044 0.0028 1.0000
12.000 0.9060 0.09330 0.09081 -0.0101 0.0028 1.0000
12.250 0.8914 0.10205 0.09966 -0.0159 0.0028 1.0000
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Polar data table (+)
Polar graphs
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