SPICA 11.73% smoothed (spicasm-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SPICA 11.73% smoothed (spicasm-il) Reynolds number: 100,000 Max Cl/Cd: 55.9 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-spicasm-il-100000-n5.txt Download as CSV file: xf-spicasm-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SPICA 11.73% 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2600 0.10156 0.09674 -0.0389 1.0000 0.0592
-8.750 -0.2611 0.09918 0.09444 -0.0388 1.0000 0.0603
-8.500 -0.2651 0.09704 0.09241 -0.0385 1.0000 0.0613
-8.250 -0.2626 0.09408 0.08953 -0.0416 0.9921 0.0627
-8.000 -0.2570 0.08982 0.08529 -0.0533 0.9641 0.0642
-7.750 -0.2435 0.08413 0.07951 -0.0677 0.9381 0.0646
-7.500 -0.2179 0.08059 0.07604 -0.0606 0.9349 0.0664
-7.250 -0.1947 0.07687 0.07229 -0.0639 0.9200 0.0684
-7.000 -0.1731 0.07266 0.06800 -0.0700 0.9029 0.0705
-6.750 -0.1528 0.06823 0.06345 -0.0769 0.8852 0.0725
-6.500 -0.1409 0.06384 0.05852 -0.0884 0.8621 0.0761
-6.250 -0.1239 0.05937 0.05396 -0.0902 0.8485 0.0768
-6.000 -0.1054 0.05588 0.05044 -0.0907 0.8359 0.0776
-5.750 -0.0879 0.04977 0.04397 -0.0922 0.8230 0.0538
-5.500 -0.0707 0.04693 0.04098 -0.0927 0.8110 0.0527
-5.250 -0.0521 0.04392 0.03768 -0.0934 0.8004 0.0524
-4.750 -0.0159 0.03647 0.02908 -0.0931 0.7798 0.0466
-4.500 0.0057 0.03438 0.02679 -0.0928 0.7709 0.0462
-4.250 0.0268 0.03243 0.02457 -0.0922 0.7616 0.0459
-4.000 0.0498 0.03054 0.02233 -0.0917 0.7538 0.0456
-3.750 0.0723 0.02886 0.02033 -0.0910 0.7451 0.0455
-3.500 0.0968 0.02728 0.01836 -0.0903 0.7379 0.0456
-3.250 0.1212 0.02604 0.01666 -0.0895 0.7299 0.0466
-3.000 0.1460 0.02496 0.01550 -0.0892 0.7229 0.0479
-2.750 0.1713 0.02400 0.01435 -0.0887 0.7159 0.0487
-2.500 0.1971 0.02304 0.01316 -0.0881 0.7087 0.0490
-2.250 0.2241 0.02218 0.01208 -0.0877 0.7030 0.0496
-2.000 0.2496 0.02144 0.01122 -0.0871 0.6957 0.0504
-1.750 0.2765 0.02076 0.01039 -0.0866 0.6898 0.0515
-1.500 0.3025 0.02020 0.00972 -0.0860 0.6835 0.0529
-1.250 0.3282 0.01973 0.00918 -0.0854 0.6771 0.0555
-1.000 0.3543 0.01927 0.00873 -0.0850 0.6719 0.0588
-0.750 0.3783 0.01892 0.00837 -0.0842 0.6652 0.0616
-0.500 0.4034 0.01859 0.00797 -0.0835 0.6592 0.0648
-0.250 0.4287 0.01824 0.00759 -0.0828 0.6540 0.0698
0.000 0.4528 0.01803 0.00739 -0.0821 0.6473 0.0789
0.250 0.4790 0.01776 0.00712 -0.0816 0.6416 0.0987
0.500 0.4981 0.01604 0.00710 -0.0806 0.6362 0.5812
0.750 0.5846 0.01533 0.00694 -0.0915 0.6282 1.0000
1.000 0.6095 0.01547 0.00686 -0.0908 0.6230 1.0000
1.250 0.6311 0.01568 0.00699 -0.0896 0.6155 1.0000
1.500 0.6552 0.01583 0.00700 -0.0887 0.6093 1.0000
1.750 0.6784 0.01602 0.00708 -0.0878 0.6028 1.0000
2.000 0.7013 0.01620 0.00719 -0.0868 0.5955 1.0000
2.250 0.7261 0.01635 0.00720 -0.0860 0.5894 1.0000
2.500 0.7478 0.01656 0.00739 -0.0849 0.5812 1.0000
2.750 0.7729 0.01669 0.00740 -0.0842 0.5747 1.0000
3.000 0.7943 0.01691 0.00763 -0.0830 0.5661 1.0000
3.250 0.8189 0.01705 0.00767 -0.0822 0.5591 1.0000
3.500 0.8407 0.01728 0.00791 -0.0811 0.5507 1.0000
3.750 0.8649 0.01743 0.00799 -0.0803 0.5435 1.0000
4.000 0.8868 0.01766 0.00825 -0.0792 0.5351 1.0000
4.250 0.9107 0.01782 0.00838 -0.0784 0.5277 1.0000
4.500 0.9324 0.01806 0.00865 -0.0773 0.5189 1.0000
4.750 0.9562 0.01822 0.00876 -0.0764 0.5112 1.0000
5.000 0.9773 0.01848 0.00909 -0.0753 0.5016 1.0000
5.250 1.0007 0.01865 0.00922 -0.0744 0.4936 1.0000
5.500 1.0215 0.01891 0.00954 -0.0732 0.4834 1.0000
5.750 1.0433 0.01914 0.00979 -0.0721 0.4740 1.0000
6.000 1.0653 0.01935 0.01000 -0.0710 0.4646 1.0000
6.250 1.0856 0.01964 0.01035 -0.0697 0.4536 1.0000
6.500 1.1065 0.01992 0.01063 -0.0685 0.4433 1.0000
6.750 1.1275 0.02017 0.01088 -0.0673 0.4331 1.0000
7.000 1.1465 0.02053 0.01129 -0.0659 0.4214 1.0000
7.250 1.1657 0.02089 0.01168 -0.0645 0.4102 1.0000
7.500 1.1848 0.02126 0.01204 -0.0631 0.3993 1.0000
7.750 1.2029 0.02168 0.01248 -0.0615 0.3880 1.0000
8.000 1.2199 0.02215 0.01300 -0.0599 0.3763 1.0000
8.250 1.2367 0.02264 0.01351 -0.0582 0.3654 1.0000
8.500 1.2531 0.02314 0.01399 -0.0565 0.3551 1.0000
8.750 1.2679 0.02371 0.01464 -0.0547 0.3442 1.0000
9.000 1.2825 0.02430 0.01528 -0.0528 0.3343 1.0000
9.500 1.3074 0.02557 0.01661 -0.0484 0.3156 1.0000
9.750 1.3195 0.02625 0.01732 -0.0463 0.3074 1.0000
10.000 1.3302 0.02700 0.01815 -0.0440 0.2988 1.0000
10.250 1.3414 0.02779 0.01897 -0.0420 0.2910 1.0000
10.500 1.3515 0.02864 0.01990 -0.0399 0.2831 1.0000
10.750 1.3618 0.02954 0.02085 -0.0380 0.2757 1.0000
11.000 1.3703 0.03052 0.02193 -0.0360 0.2680 1.0000
11.250 1.3790 0.03155 0.02303 -0.0341 0.2607 1.0000
11.500 1.3849 0.03272 0.02427 -0.0321 0.2527 1.0000
11.750 1.3894 0.03401 0.02565 -0.0303 0.2443 1.0000
12.000 1.3924 0.03542 0.02709 -0.0284 0.2358 1.0000
12.250 1.3930 0.03711 0.02893 -0.0268 0.2267 1.0000
12.500 1.3937 0.03885 0.03068 -0.0253 0.2181 1.0000
12.750 1.3917 0.04094 0.03290 -0.0240 0.2086 1.0000
13.000 1.3899 0.04315 0.03520 -0.0229 0.1995 1.0000
13.250 1.3869 0.04553 0.03761 -0.0220 0.1907 1.0000
13.500 1.3836 0.04818 0.04041 -0.0214 0.1813 1.0000
13.750 1.3784 0.05108 0.04339 -0.0210 0.1718 1.0000
14.250 1.3660 0.05756 0.05007 -0.0208 0.1528 1.0000
14.500 1.3596 0.06105 0.05364 -0.0210 0.1440 1.0000
14.750 1.3518 0.06483 0.05749 -0.0214 0.1358 1.0000
15.000 1.3440 0.06883 0.06160 -0.0220 0.1264 1.0000
15.250 1.3341 0.07322 0.06608 -0.0228 0.1175 1.0000
15.500 1.3215 0.07815 0.07105 -0.0240 0.1086 1.0000
15.750 1.3086 0.08334 0.07632 -0.0254 0.0990 1.0000
16.000 1.2939 0.08903 0.08206 -0.0272 0.0891 1.0000
16.250 1.2790 0.09489 0.08798 -0.0291 0.0805 1.0000
16.500 1.2623 0.10122 0.09434 -0.0314 0.0724 1.0000
16.750 1.2468 0.10752 0.10069 -0.0339 0.0658 1.0000
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Polar data table (+)
Polar graphs
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