CLARK-Y 11.7% smoothed (clarkysm-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK-Y 11.7% smoothed (clarkysm-il) Reynolds number: 200,000 Max Cl/Cd: 74.36 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkysm-il-200000.txt Download as CSV file: xf-clarkysm-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: CLARK-Y 11.7% smoothed
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4179 0.09019 0.08698 -0.0375 1.0000 0.0673
-8.250 -0.4464 0.08856 0.08544 -0.0353 1.0000 0.0674
-8.000 -0.4700 0.08090 0.07770 -0.0471 0.9945 0.0678
-7.750 -0.4579 0.07498 0.07182 -0.0489 0.9906 0.0689
-7.500 -0.4350 0.07305 0.06991 -0.0482 0.9873 0.0700
-7.250 -0.4642 0.04657 0.04243 -0.0659 0.9730 0.0472
-7.000 -0.4524 0.04073 0.03619 -0.0675 0.9660 0.0461
-6.750 -0.4361 0.03499 0.02973 -0.0688 0.9597 0.0467
-6.500 -0.4153 0.03096 0.02501 -0.0691 0.9542 0.0475
-6.250 -0.3932 0.02826 0.02173 -0.0688 0.9475 0.0483
-6.000 -0.3614 0.02590 0.01922 -0.0705 0.9444 0.0504
-5.750 -0.3297 0.02502 0.01825 -0.0716 0.9400 0.0535
-5.500 -0.3035 0.02377 0.01664 -0.0712 0.9332 0.0563
-5.250 -0.2688 0.02196 0.01461 -0.0727 0.9301 0.0595
-5.000 -0.2288 0.02124 0.01382 -0.0752 0.9278 0.0647
-4.750 -0.2059 0.02050 0.01286 -0.0740 0.9198 0.0686
-4.500 -0.1700 0.01953 0.01194 -0.0757 0.9161 0.0747
-4.250 -0.1297 0.01857 0.01085 -0.0780 0.9138 0.0818
-4.000 -0.0868 0.01783 0.01013 -0.0809 0.9122 0.0909
-3.750 -0.0658 0.01720 0.00951 -0.0795 0.9032 0.0977
-3.500 -0.0271 0.01659 0.00886 -0.0814 0.8999 0.1086
-3.250 0.0127 0.01590 0.00819 -0.0836 0.8973 0.1220
-3.000 0.0360 0.01542 0.00780 -0.0826 0.8890 0.1349
-2.750 0.0701 0.01478 0.00726 -0.0837 0.8842 0.1557
-2.500 0.1074 0.01406 0.00674 -0.0854 0.8809 0.1932
-2.250 0.1273 0.01364 0.00655 -0.0837 0.8711 0.2483
-2.000 0.1598 0.01292 0.00620 -0.0845 0.8663 0.3398
-1.750 0.1799 0.01245 0.00607 -0.0828 0.8570 0.4329
-1.500 0.2042 0.01160 0.00585 -0.0816 0.8507 0.5970
-1.250 0.2342 0.01088 0.00589 -0.0808 0.8420 0.8228
-1.000 0.3398 0.01062 0.00563 -0.0954 0.8379 0.9498
-0.750 0.4041 0.01058 0.00542 -0.1022 0.8313 0.9792
-0.500 0.4770 0.01046 0.00517 -0.1114 0.8228 1.0000
-0.250 0.4987 0.01041 0.00501 -0.1101 0.8118 1.0000
0.000 0.5234 0.01034 0.00481 -0.1093 0.8018 1.0000
0.250 0.5429 0.01034 0.00474 -0.1076 0.7894 1.0000
0.500 0.5642 0.01035 0.00466 -0.1061 0.7776 1.0000
0.750 0.5872 0.01036 0.00457 -0.1050 0.7665 1.0000
1.000 0.6105 0.01037 0.00449 -0.1038 0.7552 1.0000
1.250 0.6312 0.01042 0.00448 -0.1022 0.7421 1.0000
1.500 0.6528 0.01047 0.00447 -0.1008 0.7293 1.0000
1.750 0.6752 0.01054 0.00446 -0.0995 0.7167 1.0000
2.000 0.6978 0.01061 0.00445 -0.0982 0.7039 1.0000
2.250 0.7201 0.01069 0.00445 -0.0969 0.6902 1.0000
2.500 0.7421 0.01078 0.00446 -0.0955 0.6759 1.0000
2.750 0.7633 0.01090 0.00452 -0.0939 0.6608 1.0000
3.000 0.7845 0.01102 0.00459 -0.0924 0.6454 1.0000
3.250 0.8057 0.01117 0.00466 -0.0909 0.6294 1.0000
3.500 0.8265 0.01133 0.00474 -0.0893 0.6124 1.0000
3.750 0.8464 0.01150 0.00487 -0.0875 0.5939 1.0000
4.000 0.8663 0.01170 0.00500 -0.0858 0.5750 1.0000
4.250 0.8861 0.01192 0.00515 -0.0840 0.5560 1.0000
4.500 0.9057 0.01218 0.00530 -0.0823 0.5369 1.0000
4.750 0.9249 0.01247 0.00550 -0.0805 0.5176 1.0000
5.000 0.9436 0.01276 0.00573 -0.0786 0.4977 1.0000
5.250 0.9618 0.01308 0.00596 -0.0766 0.4780 1.0000
5.500 0.9797 0.01343 0.00621 -0.0746 0.4589 1.0000
5.750 0.9974 0.01379 0.00646 -0.0726 0.4407 1.0000
6.000 1.0154 0.01415 0.00674 -0.0707 0.4239 1.0000
6.250 1.0338 0.01451 0.00704 -0.0689 0.4089 1.0000
6.500 1.0521 0.01487 0.00737 -0.0671 0.3946 1.0000
6.750 1.0703 0.01522 0.00770 -0.0653 0.3809 1.0000
7.000 1.0888 0.01557 0.00805 -0.0636 0.3685 1.0000
7.250 1.1077 0.01595 0.00842 -0.0620 0.3578 1.0000
7.750 1.1436 0.01669 0.00918 -0.0585 0.3359 1.0000
8.000 1.1612 0.01707 0.00958 -0.0567 0.3256 1.0000
8.250 1.1776 0.01749 0.00998 -0.0547 0.3151 1.0000
8.500 1.1925 0.01784 0.01039 -0.0524 0.3033 1.0000
8.750 1.2059 0.01821 0.01080 -0.0499 0.2916 1.0000
9.000 1.2174 0.01861 0.01123 -0.0470 0.2792 1.0000
9.250 1.2277 0.01904 0.01169 -0.0441 0.2652 1.0000
9.500 1.2366 0.01952 0.01221 -0.0410 0.2473 1.0000
9.750 1.2422 0.02018 0.01281 -0.0376 0.2242 1.0000
10.000 1.2458 0.02107 0.01359 -0.0341 0.1894 1.0000
10.250 1.2448 0.02238 0.01468 -0.0303 0.1573 1.0000
10.500 1.2450 0.02381 0.01595 -0.0270 0.1388 1.0000
10.750 1.2464 0.02526 0.01731 -0.0240 0.1277 1.0000
11.000 1.2520 0.02655 0.01863 -0.0216 0.1191 1.0000
11.250 1.2543 0.02811 0.02014 -0.0191 0.1129 1.0000
11.500 1.2616 0.02940 0.02151 -0.0171 0.1074 1.0000
11.750 1.2651 0.03103 0.02309 -0.0150 0.1028 1.0000
12.000 1.2723 0.03248 0.02461 -0.0133 0.0987 1.0000
12.250 1.2805 0.03386 0.02607 -0.0118 0.0948 1.0000
12.500 1.2866 0.03546 0.02767 -0.0102 0.0910 1.0000
12.750 1.2951 0.03707 0.02928 -0.0088 0.0874 1.0000
13.000 1.3028 0.03854 0.03090 -0.0075 0.0842 1.0000
13.250 1.3100 0.04012 0.03255 -0.0063 0.0810 1.0000
13.500 1.3192 0.04176 0.03413 -0.0051 0.0777 1.0000
13.750 1.3270 0.04348 0.03597 -0.0040 0.0748 1.0000
14.000 1.3311 0.04532 0.03799 -0.0030 0.0721 1.0000
14.250 1.3361 0.04717 0.03992 -0.0021 0.0694 1.0000
14.500 1.3435 0.04897 0.04168 -0.0013 0.0665 1.0000
14.750 1.3492 0.05108 0.04392 -0.0003 0.0640 1.0000
15.000 1.3487 0.05346 0.04650 0.0003 0.0619 1.0000
15.250 1.3497 0.05583 0.04898 0.0007 0.0596 1.0000
15.500 1.3524 0.05805 0.05123 0.0011 0.0573 1.0000
15.750 1.3584 0.06036 0.05356 0.0018 0.0547 1.0000
16.000 1.3528 0.06355 0.05699 0.0017 0.0532 1.0000
16.250 1.3491 0.06674 0.06037 0.0016 0.0514 1.0000
16.500 1.3462 0.06986 0.06359 0.0012 0.0496 1.0000
16.750 1.3474 0.07255 0.06630 0.0008 0.0478 1.0000
17.000 1.3483 0.07553 0.06932 0.0010 0.0459 1.0000
17.250 1.3385 0.07988 0.07392 -0.0002 0.0449 1.0000
17.500 1.3291 0.08438 0.07863 -0.0015 0.0436 1.0000
17.750 1.3207 0.08885 0.08328 -0.0031 0.0423 1.0000
18.000 1.3150 0.09299 0.08753 -0.0045 0.0411 1.0000
18.250 1.3139 0.09641 0.09101 -0.0057 0.0400 1.0000
18.500 1.3144 0.09954 0.09411 -0.0062 0.0384 1.0000
18.750 1.2972 0.10590 0.10073 -0.0093 0.0379 1.0000
19.000 1.2784 0.11283 0.10792 -0.0130 0.0372 1.0000
19.250 1.2599 0.11994 0.11526 -0.0167 0.0367 1.0000
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Polar data table (+)
Polar graphs
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