SD6080 (9.2%) (sd6080-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD6080 (9.2%) (sd6080-il) Reynolds number: 200,000 Max Cl/Cd: 83.56 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd6080-il-200000.txt Download as CSV file: xf-sd6080-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: SD6080 (9.2%)
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2644 0.09377 0.09061 -0.0358 1.0000 0.0411
-9.000 -0.2684 0.09071 0.08760 -0.0387 1.0000 0.0415
-8.750 -0.2699 0.08741 0.08434 -0.0407 1.0000 0.0416
-8.500 -0.2641 0.08143 0.07841 -0.0392 1.0000 0.0427
-8.250 -0.2554 0.07833 0.07534 -0.0377 1.0000 0.0437
-8.000 -0.2563 0.07592 0.07299 -0.0363 1.0000 0.0446
-7.750 -0.2758 0.07555 0.07274 -0.0319 1.0000 0.0448
-7.500 -0.2677 0.07172 0.06893 -0.0345 0.9959 0.0462
-7.250 -0.2547 0.06686 0.06406 -0.0393 0.9898 0.0480
-7.000 -0.3608 0.07857 0.07568 -0.0354 0.9955 0.0437
-6.750 -0.3349 0.07432 0.07141 -0.0408 0.9892 0.0457
-6.500 -0.3043 0.06890 0.06594 -0.0507 0.9823 0.0483
-6.250 -0.2499 0.05943 0.05596 -0.0763 0.9721 0.0532
-6.000 -0.2329 0.05304 0.04968 -0.0789 0.9652 0.0548
-5.750 -0.2038 0.05000 0.04664 -0.0817 0.9604 0.0570
-5.500 -0.1743 0.04615 0.04264 -0.0863 0.9522 0.0608
-5.250 -0.1412 0.04006 0.03603 -0.0934 0.9443 0.0681
-5.000 -0.1188 0.03767 0.03362 -0.0939 0.9343 0.0707
-4.750 -0.0930 0.03452 0.02990 -0.0958 0.9244 0.0812
-4.500 -0.0651 0.02514 0.01954 -0.0953 0.9163 0.0380
-4.250 -0.0398 0.02146 0.01492 -0.0940 0.9066 0.0325
-4.000 -0.0145 0.01958 0.01283 -0.0936 0.8995 0.0343
-3.750 0.0103 0.01841 0.01147 -0.0928 0.8898 0.0360
-3.500 0.0363 0.01699 0.00979 -0.0918 0.8820 0.0362
-3.250 0.0620 0.01590 0.00855 -0.0908 0.8737 0.0373
-3.000 0.0875 0.01503 0.00757 -0.0900 0.8653 0.0397
-2.750 0.1127 0.01405 0.00653 -0.0890 0.8578 0.0446
-2.500 0.1382 0.01340 0.00590 -0.0884 0.8489 0.0595
-2.250 0.1635 0.01239 0.00516 -0.0877 0.8420 0.1352
-2.000 0.1879 0.01167 0.00500 -0.0874 0.8329 0.2720
-1.750 0.2109 0.01086 0.00486 -0.0865 0.8263 0.4734
-1.500 0.2301 0.01015 0.00488 -0.0844 0.8171 0.6859
-1.250 0.2686 0.00948 0.00465 -0.0848 0.8119 0.9613
-1.000 0.3048 0.00948 0.00447 -0.0866 0.8029 1.0000
-0.750 0.3307 0.00954 0.00432 -0.0860 0.7958 1.0000
-0.500 0.3567 0.00962 0.00426 -0.0856 0.7870 1.0000
-0.250 0.3830 0.00970 0.00418 -0.0851 0.7795 1.0000
0.000 0.4094 0.00977 0.00413 -0.0847 0.7713 1.0000
0.250 0.4359 0.00987 0.00411 -0.0843 0.7633 1.0000
0.500 0.4626 0.00995 0.00407 -0.0839 0.7555 1.0000
0.750 0.4892 0.01005 0.00409 -0.0836 0.7470 1.0000
1.000 0.5162 0.01013 0.00405 -0.0832 0.7396 1.0000
1.250 0.5427 0.01024 0.00411 -0.0829 0.7302 1.0000
1.500 0.5697 0.01032 0.00410 -0.0825 0.7225 1.0000
1.750 0.5963 0.01042 0.00415 -0.0822 0.7130 1.0000
2.000 0.6231 0.01052 0.00421 -0.0818 0.7039 1.0000
2.250 0.6502 0.01061 0.00421 -0.0815 0.6955 1.0000
2.500 0.6767 0.01072 0.00433 -0.0811 0.6852 1.0000
2.750 0.7034 0.01082 0.00439 -0.0808 0.6758 1.0000
3.000 0.7304 0.01091 0.00442 -0.0804 0.6663 1.0000
3.250 0.7568 0.01101 0.00454 -0.0801 0.6552 1.0000
3.500 0.7833 0.01112 0.00465 -0.0797 0.6443 1.0000
3.750 0.8099 0.01123 0.00473 -0.0793 0.6335 1.0000
4.000 0.8365 0.01133 0.00480 -0.0789 0.6224 1.0000
4.250 0.8626 0.01144 0.00494 -0.0785 0.6096 1.0000
4.500 0.8887 0.01156 0.00510 -0.0781 0.5965 1.0000
4.750 0.9147 0.01168 0.00523 -0.0776 0.5828 1.0000
5.000 0.9404 0.01181 0.00538 -0.0771 0.5681 1.0000
5.250 0.9660 0.01195 0.00553 -0.0766 0.5524 1.0000
5.500 0.9913 0.01211 0.00570 -0.0760 0.5356 1.0000
5.750 1.0162 0.01228 0.00592 -0.0754 0.5165 1.0000
6.000 1.0406 0.01249 0.00613 -0.0747 0.4952 1.0000
6.250 1.0645 0.01274 0.00640 -0.0740 0.4717 1.0000
6.500 1.0877 0.01306 0.00668 -0.0732 0.4453 1.0000
6.750 1.1099 0.01345 0.00703 -0.0723 0.4147 1.0000
7.000 1.1309 0.01395 0.00743 -0.0712 0.3803 1.0000
7.250 1.1505 0.01456 0.00794 -0.0700 0.3420 1.0000
7.500 1.1685 0.01531 0.00852 -0.0687 0.3018 1.0000
7.750 1.1852 0.01618 0.00919 -0.0673 0.2614 1.0000
8.000 1.2020 0.01704 0.00991 -0.0659 0.2242 1.0000
8.250 1.2184 0.01793 0.01068 -0.0645 0.1935 1.0000
8.500 1.2341 0.01886 0.01151 -0.0631 0.1647 1.0000
8.750 1.2492 0.01980 0.01237 -0.0616 0.1381 1.0000
9.000 1.2623 0.02088 0.01332 -0.0599 0.1088 1.0000
9.250 1.2690 0.02244 0.01461 -0.0574 0.0687 1.0000
9.500 1.2665 0.02444 0.01639 -0.0535 0.0439 1.0000
9.750 1.2672 0.02614 0.01812 -0.0502 0.0370 1.0000
10.000 1.2700 0.02776 0.01980 -0.0476 0.0333 1.0000
10.250 1.2669 0.02995 0.02206 -0.0447 0.0312 1.0000
10.500 1.2727 0.03163 0.02388 -0.0427 0.0299 1.0000
10.750 1.2781 0.03343 0.02579 -0.0409 0.0284 1.0000
11.000 1.2840 0.03526 0.02772 -0.0394 0.0270 1.0000
11.250 1.2894 0.03720 0.02972 -0.0380 0.0257 1.0000
11.500 1.2933 0.03956 0.03211 -0.0366 0.0244 1.0000
11.750 1.3026 0.04207 0.03470 -0.0350 0.0237 1.0000
12.000 1.3131 0.04409 0.03690 -0.0338 0.0232 1.0000
12.250 1.3238 0.04634 0.03934 -0.0327 0.0228 1.0000
12.500 1.3331 0.04885 0.04208 -0.0316 0.0225 1.0000
12.750 1.3398 0.05166 0.04512 -0.0305 0.0222 1.0000
13.000 1.3426 0.05482 0.04854 -0.0296 0.0221 1.0000
13.250 1.3417 0.05838 0.05237 -0.0288 0.0220 1.0000
13.500 1.3365 0.06231 0.05657 -0.0283 0.0220 1.0000
13.750 1.3279 0.06658 0.06111 -0.0283 0.0220 1.0000
14.000 1.3166 0.07112 0.06591 -0.0287 0.0218 1.0000
14.250 1.3027 0.07627 0.07131 -0.0297 0.0219 1.0000
14.500 1.2868 0.08180 0.07709 -0.0313 0.0219 1.0000
14.750 1.2695 0.08777 0.08329 -0.0335 0.0219 1.0000
15.000 1.2502 0.09452 0.09027 -0.0366 0.0220 1.0000
15.250 1.2292 0.10206 0.09802 -0.0404 0.0222 1.0000
15.500 1.2087 0.11002 0.10619 -0.0449 0.0224 1.0000
15.750 1.1866 0.11895 0.11530 -0.0505 0.0226 1.0000
16.000 1.1644 0.12857 0.12508 -0.0566 0.0230 1.0000
16.250 1.1417 0.13904 0.13567 -0.0633 0.0234 1.0000
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Polar data table (+)
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