SD6080 (9.2%) (sd6080-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD6080 (9.2%) (sd6080-il) Reynolds number: 500,000 Max Cl/Cd: 104.38 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd6080-il-500000-n5.txt Download as CSV file: xf-sd6080-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3689 0.10965 0.10733 -0.0247 1.0000 0.0094
-10.000 -0.3632 0.10634 0.10403 -0.0260 1.0000 0.0094
-8.500 -0.3399 0.08641 0.08424 -0.0336 1.0000 0.0101
-8.250 -0.3211 0.08286 0.08069 -0.0384 0.9689 0.0108
-8.000 -0.3056 0.07619 0.07397 -0.0464 0.9445 0.0084
-7.250 -0.3014 0.06254 0.06014 -0.0579 0.8731 0.0091
-7.000 -0.2952 0.05802 0.05554 -0.0624 0.8581 0.0088
-6.750 -0.2859 0.05276 0.05017 -0.0674 0.8449 0.0085
-6.500 -0.2991 0.02776 0.02414 -0.0793 0.8317 0.0068
-6.250 -0.2817 0.02255 0.01820 -0.0800 0.8227 0.0067
-6.000 -0.2597 0.01981 0.01496 -0.0800 0.8140 0.0067
-5.750 -0.2360 0.01765 0.01239 -0.0799 0.8057 0.0068
-5.500 -0.2110 0.01623 0.01065 -0.0797 0.7975 0.0069
-5.250 -0.1850 0.01512 0.00931 -0.0795 0.7893 0.0071
-5.000 -0.1588 0.01422 0.00820 -0.0793 0.7815 0.0074
-4.750 -0.1320 0.01343 0.00724 -0.0792 0.7733 0.0077
-4.500 -0.1052 0.01276 0.00641 -0.0790 0.7656 0.0081
-4.250 -0.0782 0.01214 0.00565 -0.0788 0.7576 0.0084
-4.000 -0.0511 0.01161 0.00499 -0.0786 0.7501 0.0088
-3.750 -0.0237 0.01121 0.00450 -0.0785 0.7421 0.0092
-3.500 0.0035 0.01070 0.00389 -0.0784 0.7347 0.0100
-3.250 0.0310 0.01032 0.00342 -0.0783 0.7269 0.0106
-3.000 0.0587 0.01000 0.00303 -0.0782 0.7196 0.0113
-2.750 0.0865 0.00975 0.00269 -0.0781 0.7118 0.0121
-2.500 0.1144 0.00954 0.00240 -0.0780 0.7046 0.0132
-2.250 0.1422 0.00932 0.00212 -0.0779 0.6971 0.0160
-2.000 0.1700 0.00905 0.00192 -0.0779 0.6900 0.0347
-1.750 0.1978 0.00885 0.00177 -0.0779 0.6826 0.0623
-1.500 0.2255 0.00864 0.00166 -0.0779 0.6756 0.0991
-1.250 0.2532 0.00843 0.00157 -0.0779 0.6682 0.1470
-1.000 0.2806 0.00814 0.00151 -0.0780 0.6613 0.2278
-0.750 0.3081 0.00792 0.00145 -0.0781 0.6539 0.3000
-0.500 0.3356 0.00773 0.00142 -0.0781 0.6469 0.3715
-0.250 0.3625 0.00742 0.00142 -0.0781 0.6394 0.4855
0.000 0.3890 0.00713 0.00143 -0.0779 0.6323 0.5997
0.250 0.4143 0.00683 0.00146 -0.0773 0.6244 0.7176
0.500 0.4364 0.00651 0.00151 -0.0757 0.6167 0.8474
0.750 0.4762 0.00634 0.00146 -0.0779 0.6074 0.9991
1.000 0.5039 0.00642 0.00146 -0.0779 0.5985 1.0000
1.250 0.5314 0.00651 0.00148 -0.0777 0.5898 1.0000
1.500 0.5589 0.00659 0.00151 -0.0777 0.5801 1.0000
1.750 0.5864 0.00668 0.00154 -0.0776 0.5705 1.0000
2.000 0.6138 0.00679 0.00159 -0.0775 0.5602 1.0000
2.250 0.6411 0.00690 0.00164 -0.0773 0.5487 1.0000
2.500 0.6685 0.00701 0.00171 -0.0773 0.5367 1.0000
2.750 0.6957 0.00714 0.00178 -0.0771 0.5241 1.0000
3.000 0.7228 0.00727 0.00187 -0.0770 0.5109 1.0000
3.250 0.7498 0.00742 0.00197 -0.0769 0.4971 1.0000
3.500 0.7766 0.00758 0.00208 -0.0767 0.4822 1.0000
3.750 0.8033 0.00777 0.00221 -0.0766 0.4657 1.0000
4.000 0.8297 0.00798 0.00235 -0.0764 0.4474 1.0000
4.250 0.8559 0.00820 0.00252 -0.0761 0.4280 1.0000
4.500 0.8819 0.00845 0.00270 -0.0759 0.4065 1.0000
4.750 0.9075 0.00874 0.00290 -0.0756 0.3840 1.0000
5.000 0.9328 0.00907 0.00314 -0.0753 0.3592 1.0000
5.250 0.9578 0.00941 0.00340 -0.0750 0.3331 1.0000
5.500 0.9820 0.00984 0.00369 -0.0745 0.3026 1.0000
5.750 1.0055 0.01035 0.00404 -0.0740 0.2668 1.0000
6.000 1.0276 0.01099 0.00446 -0.0734 0.2234 1.0000
6.250 1.0498 0.01160 0.00489 -0.0728 0.1872 1.0000
6.500 1.0731 0.01210 0.00528 -0.0722 0.1633 1.0000
6.750 1.0960 0.01261 0.00569 -0.0717 0.1404 1.0000
7.000 1.1183 0.01315 0.00615 -0.0710 0.1185 1.0000
7.250 1.1394 0.01381 0.00666 -0.0702 0.0927 1.0000
7.500 1.1603 0.01445 0.00719 -0.0694 0.0717 1.0000
7.750 1.1813 0.01506 0.00773 -0.0686 0.0548 1.0000
8.000 1.2000 0.01586 0.00841 -0.0675 0.0348 1.0000
8.250 1.2182 0.01667 0.00914 -0.0663 0.0191 1.0000
8.500 1.2366 0.01743 0.00987 -0.0651 0.0127 1.0000
8.750 1.2560 0.01805 0.01054 -0.0640 0.0112 1.0000
9.000 1.2742 0.01874 0.01129 -0.0628 0.0100 1.0000
9.250 1.2927 0.01935 0.01197 -0.0616 0.0096 1.0000
9.500 1.3098 0.02002 0.01273 -0.0602 0.0091 1.0000
9.750 1.3249 0.02072 0.01351 -0.0585 0.0086 1.0000
10.000 1.3371 0.02149 0.01436 -0.0564 0.0083 1.0000
10.250 1.3478 0.02235 0.01530 -0.0542 0.0080 1.0000
10.500 1.3576 0.02329 0.01633 -0.0521 0.0078 1.0000
10.750 1.3656 0.02442 0.01754 -0.0500 0.0076 1.0000
11.000 1.3721 0.02570 0.01893 -0.0479 0.0074 1.0000
11.250 1.3754 0.02730 0.02064 -0.0457 0.0071 1.0000
11.500 1.3779 0.02906 0.02250 -0.0438 0.0070 1.0000
11.750 1.3842 0.03059 0.02414 -0.0423 0.0069 1.0000
12.000 1.3898 0.03227 0.02592 -0.0410 0.0068 1.0000
12.250 1.3933 0.03420 0.02796 -0.0398 0.0068 1.0000
12.500 1.3969 0.03623 0.03010 -0.0388 0.0067 1.0000
12.750 1.3989 0.03849 0.03248 -0.0379 0.0066 1.0000
13.000 1.4009 0.04085 0.03496 -0.0372 0.0065 1.0000
13.250 1.4018 0.04341 0.03765 -0.0367 0.0064 1.0000
13.500 1.4046 0.04583 0.04019 -0.0364 0.0062 1.0000
13.750 1.4028 0.04890 0.04338 -0.0362 0.0061 1.0000
14.000 1.4018 0.05195 0.04655 -0.0362 0.0060 1.0000
14.250 1.4008 0.05511 0.04983 -0.0365 0.0059 1.0000
14.500 1.3983 0.05859 0.05344 -0.0369 0.0057 1.0000
14.750 1.3944 0.06240 0.05738 -0.0375 0.0057 1.0000
15.000 1.3913 0.06625 0.06135 -0.0385 0.0056 1.0000
15.250 1.3869 0.07043 0.06566 -0.0396 0.0056 1.0000
15.500 1.3814 0.07492 0.07028 -0.0410 0.0055 1.0000
15.750 1.3754 0.07963 0.07513 -0.0426 0.0055 1.0000
16.000 1.3689 0.08462 0.08025 -0.0445 0.0054 1.0000
16.250 1.3616 0.08985 0.08561 -0.0466 0.0054 1.0000
16.500 1.3543 0.09529 0.09118 -0.0490 0.0053 1.0000
16.750 1.3463 0.10096 0.09699 -0.0515 0.0053 1.0000
17.000 1.3376 0.10692 0.10308 -0.0544 0.0052 1.0000
17.250 1.3287 0.11304 0.10933 -0.0574 0.0052 1.0000
17.500 1.3198 0.11930 0.11573 -0.0607 0.0052 1.0000
17.750 1.3103 0.12584 0.12240 -0.0642 0.0051 1.0000
18.000 1.3011 0.13245 0.12915 -0.0679 0.0051 1.0000
18.250 1.2916 0.13924 0.13607 -0.0718 0.0051 1.0000
18.500 1.2822 0.14614 0.14310 -0.0758 0.0051 1.0000
18.750 1.2730 0.15319 0.15027 -0.0801 0.0051 1.0000
19.000 1.2635 0.16047 0.15767 -0.0846 0.0051 1.0000
19.250 1.2539 0.16790 0.16523 -0.0893 0.0050 1.0000
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Polar data table (+)
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