Coanda 2 (coanda2-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: Coanda 2 (coanda2-il) Reynolds number: 50,000 Max Cl/Cd: 37.53 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-coanda2-il-50000.txt Download as CSV file: xf-coanda2-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4289 0.10733 0.10049 -0.0142 1.0000 0.1225
-8.750 -0.4346 0.10571 0.09897 -0.0155 1.0000 0.1243
-8.500 -0.4485 0.10487 0.09829 -0.0170 1.0000 0.1252
-8.250 -0.4332 0.09888 0.09232 -0.0153 1.0000 0.1284
-8.000 -0.4300 0.09566 0.08909 -0.0144 1.0000 0.1333
-7.750 -0.4351 0.09357 0.08710 -0.0157 1.0000 0.1371
-7.500 -0.4439 0.09256 0.08623 -0.0207 1.0000 0.1391
-7.250 -0.4320 0.08728 0.08095 -0.0161 1.0000 0.1505
-7.000 -0.4312 0.08405 0.07779 -0.0171 1.0000 0.1557
-6.750 -0.4276 0.08132 0.07509 -0.0175 1.0000 0.1653
-6.000 -0.0793 0.04497 0.03746 -0.0209 1.0000 1.0000
-5.750 -0.0693 0.04299 0.03546 -0.0215 1.0000 1.0000
-5.500 -0.0592 0.04113 0.03359 -0.0220 1.0000 1.0000
-5.250 -0.0490 0.03935 0.03179 -0.0224 1.0000 1.0000
-5.000 -0.0454 0.03802 0.03050 -0.0211 1.0000 0.9971
-4.750 -0.1131 0.04000 0.03284 -0.0036 1.0000 0.9520
-4.500 -0.1756 0.04099 0.03420 0.0105 1.0000 0.9084
-4.250 -0.2291 0.04102 0.03457 0.0209 1.0000 0.8599
-4.000 -0.2835 0.04087 0.03478 0.0312 1.0000 0.8269
-3.250 -0.2773 0.03439 0.02655 -0.0107 1.0000 0.3308
-3.000 -0.2451 0.03233 0.02363 -0.0123 1.0000 0.2911
-2.750 -0.2222 0.03063 0.02157 -0.0116 1.0000 0.2828
-2.500 -0.1982 0.02952 0.01996 -0.0109 1.0000 0.2769
-2.250 -0.1743 0.02826 0.01836 -0.0101 1.0000 0.2679
-2.000 -0.1497 0.02734 0.01707 -0.0094 1.0000 0.2605
-1.750 -0.1249 0.02646 0.01582 -0.0088 1.0000 0.2546
-1.500 -0.0999 0.02593 0.01490 -0.0082 1.0000 0.2497
-1.250 -0.0751 0.02520 0.01400 -0.0077 1.0000 0.2474
-1.000 -0.0503 0.02463 0.01325 -0.0072 1.0000 0.2457
-0.750 -0.0243 0.02421 0.01265 -0.0071 1.0000 0.2471
-0.500 0.0050 0.02390 0.01210 -0.0077 1.0000 0.2513
-0.250 0.0376 0.02355 0.01167 -0.0091 1.0000 0.2539
0.000 0.0684 0.02336 0.01140 -0.0102 1.0000 0.2549
0.250 0.0968 0.02328 0.01131 -0.0111 1.0000 0.2568
0.500 0.1224 0.02333 0.01139 -0.0117 1.0000 0.2598
0.750 0.1452 0.02358 0.01163 -0.0120 1.0000 0.2639
1.000 0.1668 0.02391 0.01210 -0.0126 1.0000 0.2695
1.250 0.1893 0.02456 0.01285 -0.0140 0.9982 0.2775
1.500 0.2886 0.02463 0.01396 -0.0298 0.9699 0.3705
1.750 0.4104 0.02395 0.01429 -0.0484 0.9393 1.0000
2.000 0.4934 0.02375 0.01411 -0.0584 0.9021 1.0000
2.250 0.5687 0.02296 0.01345 -0.0661 0.8637 1.0000
2.500 0.6321 0.02193 0.01257 -0.0706 0.8236 1.0000
2.750 0.6827 0.02110 0.01190 -0.0724 0.7808 1.0000
3.000 0.7222 0.02070 0.01150 -0.0723 0.7375 1.0000
3.250 0.7549 0.02074 0.01147 -0.0714 0.6949 1.0000
3.500 0.7829 0.02106 0.01167 -0.0698 0.6514 1.0000
3.750 0.8023 0.02138 0.01180 -0.0663 0.5976 1.0000
4.000 0.8229 0.02193 0.01221 -0.0638 0.5542 1.0000
4.250 0.8409 0.02241 0.01258 -0.0610 0.5115 1.0000
4.500 0.8616 0.02305 0.01326 -0.0591 0.4776 1.0000
4.750 0.8786 0.02348 0.01360 -0.0564 0.4384 1.0000
5.000 0.8992 0.02411 0.01432 -0.0546 0.4087 1.0000
5.250 0.9191 0.02469 0.01513 -0.0526 0.3800 1.0000
5.500 0.9282 0.02478 0.01519 -0.0487 0.3328 1.0000
5.750 0.9367 0.02504 0.01539 -0.0449 0.2689 1.0000
6.000 0.9452 0.02663 0.01627 -0.0417 0.1470 1.0000
6.250 0.9579 0.02919 0.01828 -0.0393 0.0961 1.0000
6.500 0.9725 0.03121 0.02026 -0.0369 0.0838 1.0000
6.750 0.9882 0.03313 0.02225 -0.0346 0.0775 1.0000
7.000 1.0052 0.03533 0.02448 -0.0325 0.0737 1.0000
7.250 1.0270 0.03762 0.02703 -0.0308 0.0701 1.0000
7.500 1.0474 0.04007 0.02964 -0.0293 0.0659 1.0000
7.750 1.0689 0.04315 0.03291 -0.0283 0.0636 1.0000
8.000 1.0891 0.04686 0.03695 -0.0270 0.0631 1.0000
8.250 1.1032 0.05051 0.04112 -0.0249 0.0636 1.0000
8.500 1.1102 0.05438 0.04561 -0.0222 0.0646 1.0000
8.750 1.1067 0.05889 0.05078 -0.0192 0.0660 1.0000
9.000 1.0956 0.06371 0.05615 -0.0163 0.0675 1.0000
9.250 1.0809 0.06840 0.06122 -0.0138 0.0687 1.0000
9.500 1.0620 0.07302 0.06609 -0.0116 0.0697 1.0000
9.750 1.0394 0.07732 0.07057 -0.0098 0.0705 1.0000
10.000 1.0158 0.08230 0.07568 -0.0099 0.0711 1.0000
10.250 0.9913 0.08840 0.08188 -0.0123 0.0719 1.0000
10.500 0.9683 0.09556 0.08908 -0.0166 0.0726 1.0000
10.750 0.9524 0.10306 0.09657 -0.0206 0.0737 1.0000
11.000 0.9066 0.11981 0.11316 -0.0337 0.0791 1.0000
11.250 0.8936 0.12825 0.12150 -0.0379 0.0828 1.0000
11.500 0.8930 0.13386 0.12708 -0.0392 0.0854 1.0000
11.750 0.9004 0.13818 0.13141 -0.0387 0.0869 1.0000
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Polar data table (+)
Polar graphs
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