WB-135/35 13.5% smoothed (wb13535sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: WB-135/35 13.5% smoothed (wb13535sm-il) Reynolds number: 100,000 Max Cl/Cd: 51.77 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-wb13535sm-il-100000.txt Download as CSV file: xf-wb13535sm-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: WB-135/35 13.5% smoothed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3966 0.09613 0.09142 -0.0544 1.0000 0.0789
-10.250 -0.4296 0.08380 0.07922 -0.0590 1.0000 0.0677
-10.000 -0.4391 0.07880 0.07427 -0.0597 1.0000 0.0657
-9.750 -0.4585 0.07336 0.06894 -0.0607 1.0000 0.0642
-9.500 -0.5050 0.06586 0.06160 -0.0634 1.0000 0.0619
-9.250 -0.6355 0.05884 0.05416 -0.0625 1.0000 0.0552
-9.000 -0.6555 0.05599 0.05122 -0.0595 1.0000 0.0549
-8.750 -0.6711 0.05303 0.04814 -0.0568 1.0000 0.0545
-8.500 -0.6834 0.05002 0.04490 -0.0544 1.0000 0.0543
-8.250 -0.6909 0.04702 0.04158 -0.0523 1.0000 0.0543
-8.000 -0.6819 0.04346 0.03742 -0.0530 0.9966 0.0549
-7.750 -0.6565 0.03996 0.03327 -0.0554 0.9899 0.0554
-7.500 -0.6296 0.03597 0.02884 -0.0574 0.9844 0.0562
-7.250 -0.6023 0.03319 0.02583 -0.0585 0.9787 0.0575
-7.000 -0.5713 0.03123 0.02368 -0.0599 0.9732 0.0593
-6.750 -0.5398 0.02977 0.02201 -0.0612 0.9675 0.0636
-6.500 -0.5106 0.02832 0.02034 -0.0618 0.9610 0.0678
-6.250 -0.4761 0.02684 0.01893 -0.0636 0.9564 0.0741
-6.000 -0.4552 0.02577 0.01781 -0.0628 0.9491 0.0820
-5.750 -0.4242 0.02462 0.01672 -0.0639 0.9437 0.1028
-5.500 -0.4010 0.02386 0.01641 -0.0637 0.9368 0.1918
-5.250 -0.3712 0.02459 0.01699 -0.0644 0.9299 0.2358
-5.000 -0.3409 0.02519 0.01750 -0.0651 0.9244 0.2595
-4.750 -0.3187 0.02568 0.01789 -0.0644 0.9170 0.2795
-4.500 -0.2824 0.02643 0.01875 -0.0660 0.9124 0.3044
-4.250 -0.2645 0.02663 0.01892 -0.0645 0.9052 0.3176
-4.000 -0.2341 0.02638 0.01852 -0.0653 0.9000 0.3284
-3.750 -0.1948 0.02608 0.01800 -0.0676 0.8965 0.3410
-3.500 -0.1818 0.02609 0.01800 -0.0653 0.8886 0.3483
-3.250 -0.1492 0.02588 0.01768 -0.0664 0.8841 0.3599
-3.000 -0.1147 0.02570 0.01737 -0.0678 0.8800 0.3731
-2.750 -0.1006 0.02581 0.01744 -0.0658 0.8724 0.3831
-2.500 -0.0661 0.02566 0.01725 -0.0671 0.8682 0.3976
-2.250 -0.0423 0.02572 0.01729 -0.0666 0.8625 0.4114
-2.000 -0.0204 0.02579 0.01736 -0.0659 0.8561 0.4257
-1.750 0.0177 0.02564 0.01718 -0.0677 0.8522 0.4459
-1.500 0.0320 0.02590 0.01745 -0.0656 0.8442 0.4613
-1.250 0.0760 0.02545 0.01706 -0.0680 0.8378 0.4847
-1.000 0.1042 0.02522 0.01684 -0.0677 0.8271 0.5065
-0.750 0.1688 0.02414 0.01579 -0.0729 0.8217 0.5402
-0.500 0.1891 0.02403 0.01578 -0.0713 0.8110 0.5618
-0.250 0.2366 0.02333 0.01516 -0.0740 0.8071 0.5951
0.000 0.2532 0.02344 0.01538 -0.0720 0.7975 0.6220
0.250 0.2980 0.02270 0.01481 -0.0743 0.7930 0.6656
0.750 0.4684 0.02061 0.01362 -0.0951 0.7834 1.0000
1.000 0.5066 0.02027 0.01308 -0.0966 0.7773 1.0000
1.250 0.5258 0.02051 0.01321 -0.0950 0.7671 1.0000
1.500 0.5663 0.02002 0.01260 -0.0964 0.7611 1.0000
1.750 0.5849 0.02022 0.01274 -0.0945 0.7499 1.0000
2.000 0.6143 0.02008 0.01253 -0.0942 0.7411 1.0000
2.250 0.6458 0.01981 0.01220 -0.0941 0.7321 1.0000
2.500 0.6686 0.01982 0.01218 -0.0927 0.7203 1.0000
2.750 0.6968 0.01964 0.01195 -0.0920 0.7093 1.0000
3.000 0.7331 0.01916 0.01140 -0.0925 0.6998 1.0000
3.250 0.7566 0.01909 0.01132 -0.0911 0.6860 1.0000
3.500 0.7821 0.01894 0.01114 -0.0900 0.6716 1.0000
3.750 0.8087 0.01873 0.01090 -0.0890 0.6562 1.0000
4.000 0.8361 0.01849 0.01060 -0.0881 0.6397 1.0000
4.250 0.8565 0.01847 0.01057 -0.0862 0.6192 1.0000
4.500 0.8805 0.01836 0.01040 -0.0848 0.5985 1.0000
4.750 0.9052 0.01830 0.01025 -0.0836 0.5774 1.0000
5.000 0.9258 0.01842 0.01031 -0.0818 0.5544 1.0000
5.250 0.9504 0.01853 0.01029 -0.0808 0.5347 1.0000
5.500 0.9702 0.01886 0.01058 -0.0791 0.5145 1.0000
5.750 0.9921 0.01919 0.01085 -0.0779 0.4969 1.0000
6.000 1.0147 0.01960 0.01118 -0.0768 0.4814 1.0000
6.250 1.0373 0.02006 0.01159 -0.0758 0.4674 1.0000
6.500 1.0606 0.02058 0.01208 -0.0750 0.4551 1.0000
6.750 1.0856 0.02112 0.01257 -0.0745 0.4441 1.0000
7.000 1.1087 0.02172 0.01318 -0.0737 0.4333 1.0000
7.250 1.1290 0.02229 0.01378 -0.0724 0.4208 1.0000
7.500 1.1479 0.02278 0.01426 -0.0708 0.4062 1.0000
7.750 1.1658 0.02328 0.01474 -0.0691 0.3914 1.0000
8.000 1.1851 0.02387 0.01535 -0.0677 0.3795 1.0000
8.250 1.2023 0.02440 0.01589 -0.0659 0.3660 1.0000
8.500 1.2221 0.02497 0.01646 -0.0646 0.3543 1.0000
8.750 1.2389 0.02550 0.01705 -0.0628 0.3425 1.0000
9.000 1.2492 0.02596 0.01760 -0.0600 0.3288 1.0000
9.250 1.2581 0.02642 0.01817 -0.0569 0.3158 1.0000
9.500 1.2661 0.02688 0.01874 -0.0537 0.3035 1.0000
9.750 1.2700 0.02731 0.01926 -0.0499 0.2906 1.0000
10.000 1.2630 0.02774 0.01977 -0.0444 0.2753 1.0000
10.250 1.2562 0.02839 0.02053 -0.0395 0.2586 1.0000
10.500 1.2486 0.02933 0.02151 -0.0352 0.2381 1.0000
10.750 1.2401 0.03070 0.02292 -0.0314 0.2054 1.0000
11.000 1.2274 0.03293 0.02485 -0.0280 0.1531 1.0000
11.250 1.2060 0.03648 0.02783 -0.0248 0.0893 1.0000
11.500 1.1912 0.03994 0.03105 -0.0224 0.0694 1.0000
11.750 1.1824 0.04303 0.03416 -0.0207 0.0617 1.0000
12.000 1.1737 0.04625 0.03745 -0.0194 0.0578 1.0000
12.250 1.1637 0.04977 0.04108 -0.0184 0.0547 1.0000
12.500 1.1566 0.05315 0.04462 -0.0177 0.0526 1.0000
12.750 1.1487 0.05675 0.04836 -0.0173 0.0512 1.0000
13.000 1.1399 0.06062 0.05237 -0.0173 0.0499 1.0000
13.250 1.1306 0.06471 0.05657 -0.0174 0.0486 1.0000
13.500 1.1203 0.06902 0.06096 -0.0177 0.0473 1.0000
13.750 1.1144 0.07273 0.06470 -0.0178 0.0457 1.0000
14.000 1.1161 0.07555 0.06765 -0.0175 0.0444 1.0000
14.250 1.1209 0.07788 0.07006 -0.0171 0.0431 1.0000
14.500 1.1298 0.07960 0.07184 -0.0160 0.0416 1.0000
14.750 1.1454 0.08038 0.07263 -0.0143 0.0405 1.0000
15.000 1.1666 0.08066 0.07290 -0.0122 0.0395 1.0000
15.250 1.1917 0.08098 0.07322 -0.0099 0.0387 1.0000
15.500 1.2242 0.08155 0.07380 -0.0074 0.0378 1.0000
15.750 1.2416 0.08439 0.07677 -0.0063 0.0371 1.0000
16.000 1.2380 0.08828 0.08091 -0.0066 0.0369 1.0000
16.250 1.2312 0.09249 0.08538 -0.0073 0.0368 1.0000
16.500 1.2214 0.09713 0.09027 -0.0085 0.0368 1.0000
16.750 1.2113 0.10210 0.09546 -0.0099 0.0368 1.0000
17.000 1.1969 0.10764 0.10123 -0.0121 0.0368 1.0000
17.250 1.1826 0.11353 0.10733 -0.0145 0.0369 1.0000
17.500 1.1705 0.11949 0.11348 -0.0170 0.0371 1.0000
17.750 1.1540 0.12589 0.12011 -0.0206 0.0374 1.0000
18.000 1.1304 0.13375 0.12822 -0.0260 0.0377 1.0000
18.250 1.0157 0.16534 0.16043 -0.0492 0.0430 1.0000
18.500 0.9879 0.17872 0.17382 -0.0569 0.0451 1.0000
18.750 0.9832 0.18568 0.18075 -0.0601 0.0460 1.0000
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Polar data table (+)
Polar graphs
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