Coanda 2 (coanda2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Coanda 2 (coanda2-il) Reynolds number: 1,000,000 Max Cl/Cd: 58.34 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-coanda2-il-1000000.txt Download as CSV file: xf-coanda2-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: Coanda 2
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4446 0.09932 0.09772 -0.0132 1.0000 0.0072
-9.500 -0.4598 0.09277 0.09121 -0.0150 1.0000 0.0077
-9.250 -0.4612 0.08938 0.08784 -0.0157 1.0000 0.0078
-9.000 -0.4595 0.08737 0.08585 -0.0158 1.0000 0.0082
-8.750 -0.4682 0.08327 0.08178 -0.0164 1.0000 0.0080
-8.500 -0.4637 0.08289 0.08142 -0.0155 1.0000 0.0087
-8.250 -0.4807 0.07950 0.07807 -0.0141 1.0000 0.0084
-8.000 -0.4759 0.07820 0.07677 -0.0139 1.0000 0.0095
-7.750 -0.4775 0.07523 0.07382 -0.0144 1.0000 0.0101
-7.500 -0.4800 0.07185 0.07045 -0.0150 1.0000 0.0104
-7.250 -0.4682 0.06652 0.06510 -0.0201 0.9989 0.0106
-6.750 -0.4408 0.02546 0.02277 -0.0467 0.9864 0.0076
-6.500 -0.4109 0.02264 0.01963 -0.0480 0.9845 0.0074
-6.250 -0.3858 0.01882 0.01531 -0.0486 0.9827 0.0075
-6.000 -0.3679 0.01666 0.01284 -0.0468 0.9773 0.0076
-5.750 -0.3404 0.01520 0.01114 -0.0467 0.9745 0.0075
-5.500 -0.3108 0.01383 0.00955 -0.0470 0.9725 0.0074
-5.250 -0.2797 0.01232 0.00779 -0.0476 0.9708 0.0074
-5.000 -0.2493 0.01054 0.00571 -0.0480 0.9694 0.0086
-4.750 -0.2273 0.00992 0.00497 -0.0464 0.9636 0.0095
-4.500 -0.1964 0.00938 0.00435 -0.0468 0.9611 0.0105
-4.250 -0.1639 0.00889 0.00376 -0.0476 0.9592 0.0112
-4.000 -0.1295 0.00846 0.00326 -0.0488 0.9574 0.0122
-3.750 -0.0940 0.00805 0.00271 -0.0503 0.9559 0.0147
-3.500 -0.0704 0.00770 0.00230 -0.0491 0.9495 0.0197
-3.250 -0.0357 0.00778 0.00264 -0.0504 0.9457 0.0617
-3.000 0.0041 0.00843 0.00338 -0.0529 0.9426 0.0675
-2.750 0.0327 0.00865 0.00358 -0.0528 0.9349 0.0700
-2.500 0.0692 0.00867 0.00357 -0.0546 0.9291 0.0716
-2.250 0.0996 0.00929 0.00419 -0.0549 0.9190 0.0731
-2.000 0.1299 0.00851 0.00336 -0.0555 0.9091 0.0765
-1.750 0.1599 0.00834 0.00315 -0.0559 0.8970 0.0776
-1.500 0.1880 0.00816 0.00293 -0.0558 0.8823 0.0784
-1.250 0.2148 0.00801 0.00272 -0.0554 0.8636 0.0790
-1.000 0.2402 0.00789 0.00252 -0.0547 0.8400 0.0796
-0.750 0.2632 0.00783 0.00233 -0.0534 0.8017 0.0800
-0.500 0.2818 0.00792 0.00217 -0.0512 0.7346 0.0803
-0.250 0.2978 0.00815 0.00207 -0.0484 0.6532 0.0806
0.000 0.3183 0.00826 0.00199 -0.0468 0.6051 0.0808
0.250 0.3401 0.00833 0.00191 -0.0454 0.5640 0.0811
0.500 0.3625 0.00839 0.00183 -0.0442 0.5248 0.0814
0.750 0.3857 0.00842 0.00176 -0.0432 0.4919 0.0817
1.000 0.4092 0.00846 0.00171 -0.0422 0.4650 0.0822
1.500 0.4556 0.00869 0.00172 -0.0403 0.4025 0.0840
1.750 0.4788 0.00881 0.00172 -0.0393 0.3679 0.0847
2.000 0.5019 0.00898 0.00175 -0.0384 0.3309 0.0856
2.250 0.5244 0.00924 0.00181 -0.0373 0.2822 0.0863
2.500 0.5432 0.00971 0.00188 -0.0357 0.1960 0.0880
2.750 0.5571 0.01073 0.00224 -0.0332 0.0546 0.0903
3.000 0.5795 0.01108 0.00244 -0.0321 0.0176 0.0918
3.250 0.6045 0.01118 0.00262 -0.0315 0.0148 0.0934
3.500 0.6292 0.01131 0.00284 -0.0308 0.0129 0.0947
3.750 0.6536 0.01148 0.00306 -0.0301 0.0121 0.0962
4.000 0.6775 0.01170 0.00337 -0.0292 0.0111 0.0975
4.250 0.7007 0.01201 0.00378 -0.0282 0.0100 0.0987
4.500 0.7226 0.01246 0.00430 -0.0270 0.0090 0.1001
4.750 0.7436 0.01297 0.00491 -0.0255 0.0085 0.1053
5.000 0.7654 0.01340 0.00543 -0.0243 0.0088 0.1122
7.250 1.1031 0.03163 0.02671 -0.0491 0.0073 1.0000
7.500 1.1192 0.03196 0.02723 -0.0469 0.0071 1.0000
7.750 1.1374 0.03193 0.02736 -0.0451 0.0066 1.0000
8.000 1.1514 0.03319 0.02882 -0.0428 0.0062 1.0000
8.250 1.1617 0.03505 0.03091 -0.0401 0.0058 1.0000
8.500 1.1698 0.03708 0.03314 -0.0374 0.0055 1.0000
8.750 1.1751 0.03936 0.03562 -0.0344 0.0053 1.0000
9.000 1.1780 0.04170 0.03816 -0.0314 0.0052 1.0000
9.250 1.1776 0.04415 0.04079 -0.0281 0.0051 1.0000
9.500 1.1747 0.04672 0.04353 -0.0247 0.0050 1.0000
9.750 1.1651 0.04912 0.04610 -0.0204 0.0050 1.0000
10.000 1.1515 0.05101 0.04809 -0.0158 0.0049 1.0000
10.250 1.1355 0.05358 0.05080 -0.0123 0.0048 1.0000
10.500 1.1182 0.05677 0.05415 -0.0102 0.0049 1.0000
10.750 1.1000 0.06077 0.05830 -0.0097 0.0048 1.0000
11.000 1.0828 0.06544 0.06310 -0.0110 0.0048 1.0000
11.250 1.0616 0.07195 0.06979 -0.0148 0.0049 1.0000
11.500 1.0459 0.07858 0.07654 -0.0194 0.0049 1.0000
11.750 1.0225 0.08810 0.08622 -0.0263 0.0050 1.0000
12.000 0.9986 0.09864 0.09690 -0.0334 0.0051 1.0000
12.250 0.9747 0.10998 0.10835 -0.0403 0.0053 1.0000
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Polar data table (+)
Polar graphs
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