S1223 (s1223-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1223 (s1223-il) Reynolds number: 200,000 Max Cl/Cd: 73.64 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1223-il-200000.txt Download as CSV file: xf-s1223-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: S1223
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
------ -------- --------- --------- -------- -------- --------
-6.500 0.0364 0.10133 0.09809 -0.0680 0.9421 0.0345
-6.250 0.0469 0.09868 0.09546 -0.0718 0.9334 0.0354
-6.000 0.0508 0.09669 0.09349 -0.0763 0.9232 0.0356
-5.750 0.0806 0.09179 0.08861 -0.0765 0.9190 0.0363
-5.500 0.1067 0.08822 0.08503 -0.0800 0.9150 0.0373
-5.250 0.1164 0.08572 0.08257 -0.0804 0.9030 0.0382
-5.000 0.1245 0.08324 0.08011 -0.0809 0.8906 0.0394
-4.750 0.1269 0.08100 0.07789 -0.0827 0.8762 0.0407
-4.500 0.1391 0.07730 0.07421 -0.0888 0.8604 0.0412
-4.250 0.1638 0.07385 0.07075 -0.0875 0.8526 0.0420
-4.000 0.1856 0.07076 0.06763 -0.0892 0.8355 0.0435
-3.750 0.2183 0.06637 0.06318 -0.0983 0.8131 0.0468
-3.500 0.2671 0.06098 0.05766 -0.1085 0.7882 0.0484
-3.250 0.3591 0.05325 0.04961 -0.1352 0.7497 0.0549
-3.000 0.4521 0.04675 0.04260 -0.1598 0.6965 0.0630
-2.750 0.4529 0.04601 0.04165 -0.1524 0.6584 0.0639
-2.500 0.5218 0.04093 0.03616 -0.1705 0.6254 0.0733
-2.250 0.5219 0.04093 0.03605 -0.1634 0.6040 0.0747
-2.000 0.7757 0.02427 0.01766 -0.2308 0.5711 0.0721
-1.750 0.9027 0.01890 0.01064 -0.2530 0.5513 0.0481
-1.500 0.9431 0.01846 0.01006 -0.2557 0.5387 0.0518
-1.000 1.0263 0.01778 0.00904 -0.2611 0.5177 0.0572
-0.750 1.0687 0.01778 0.00887 -0.2641 0.5086 0.0644
-0.500 1.1086 0.01768 0.00875 -0.2666 0.5000 0.0749
-0.250 1.1554 0.01758 0.00895 -0.2707 0.4921 0.2576
0.000 1.1864 0.01804 0.00925 -0.2712 0.4860 0.2928
0.250 1.2135 0.01838 0.00963 -0.2708 0.4801 0.3263
0.500 1.2420 0.01874 0.00993 -0.2708 0.4745 0.3552
0.750 1.2746 0.01909 0.01014 -0.2717 0.4694 0.3719
1.000 1.3047 0.01928 0.01035 -0.2720 0.4644 0.3835
1.250 1.3344 0.01947 0.01053 -0.2723 0.4595 0.3972
1.500 1.3650 0.01971 0.01072 -0.2728 0.4552 0.4129
1.750 1.3971 0.02001 0.01095 -0.2736 0.4513 0.4310
2.000 1.4305 0.02039 0.01132 -0.2747 0.4474 0.4534
2.250 1.4588 0.02059 0.01164 -0.2747 0.4435 0.4800
2.500 1.4884 0.02083 0.01197 -0.2750 0.4395 0.5136
2.750 1.5190 0.02110 0.01232 -0.2755 0.4359 0.5572
3.000 1.5503 0.02140 0.01269 -0.2761 0.4327 0.6156
3.250 1.5826 0.02183 0.01318 -0.2769 0.4296 0.6987
3.500 1.6008 0.02189 0.01352 -0.2746 0.4270 0.8271
3.750 1.6172 0.02196 0.01369 -0.2721 0.4240 1.0000
4.000 1.6448 0.02235 0.01404 -0.2720 0.4206 1.0000
4.250 1.6730 0.02276 0.01440 -0.2721 0.4175 1.0000
4.500 1.7018 0.02319 0.01477 -0.2723 0.4148 1.0000
4.750 1.7319 0.02371 0.01522 -0.2728 0.4121 1.0000
5.000 1.7614 0.02435 0.01581 -0.2732 0.4093 1.0000
5.250 1.7847 0.02474 0.01630 -0.2723 0.4064 1.0000
5.500 1.8093 0.02518 0.01680 -0.2716 0.4033 1.0000
5.750 1.8348 0.02563 0.01730 -0.2712 0.4004 1.0000
6.000 1.8609 0.02606 0.01772 -0.2708 0.3974 1.0000
6.250 1.8886 0.02652 0.01812 -0.2708 0.3945 1.0000
6.500 1.9197 0.02729 0.01880 -0.2717 0.3915 1.0000
6.750 1.9392 0.02771 0.01940 -0.2700 0.3886 1.0000
7.000 1.9602 0.02819 0.02000 -0.2687 0.3853 1.0000
7.250 1.9826 0.02863 0.02052 -0.2676 0.3819 1.0000
7.500 2.0067 0.02903 0.02093 -0.2669 0.3785 1.0000
7.750 2.0339 0.02946 0.02130 -0.2669 0.3753 1.0000
8.000 2.0592 0.03015 0.02202 -0.2666 0.3720 1.0000
8.250 2.0753 0.03067 0.02275 -0.2643 0.3686 1.0000
8.500 2.0938 0.03118 0.02338 -0.2626 0.3649 1.0000
8.750 2.1151 0.03159 0.02385 -0.2614 0.3614 1.0000
9.000 2.1400 0.03193 0.02415 -0.2609 0.3580 1.0000
9.250 2.1647 0.03255 0.02477 -0.2605 0.3542 1.0000
9.500 2.1738 0.03312 0.02558 -0.2569 0.3501 1.0000
9.750 2.1881 0.03358 0.02617 -0.2543 0.3458 1.0000
10.000 2.2074 0.03388 0.02649 -0.2527 0.3419 1.0000
10.250 2.2356 0.03427 0.02675 -0.2530 0.3375 1.0000
10.500 2.2334 0.03499 0.02779 -0.2473 0.3333 1.0000
10.750 2.2372 0.03556 0.02851 -0.2428 0.3287 1.0000
11.000 2.2491 0.03592 0.02890 -0.2399 0.3244 1.0000
11.250 2.2719 0.03633 0.02923 -0.2392 0.3200 1.0000
11.500 2.2654 0.03739 0.03060 -0.2331 0.3160 1.0000
11.750 2.2678 0.03827 0.03165 -0.2287 0.3114 1.0000
12.000 2.2764 0.03890 0.03234 -0.2256 0.3070 1.0000
12.250 2.2901 0.03956 0.03299 -0.2234 0.3026 1.0000
12.500 2.2823 0.04106 0.03479 -0.2178 0.2977 1.0000
12.750 2.2837 0.04222 0.03610 -0.2139 0.2928 1.0000
13.000 2.2919 0.04308 0.03696 -0.2111 0.2881 1.0000
13.250 2.2866 0.04490 0.03903 -0.2067 0.2828 1.0000
13.500 2.2836 0.04662 0.04092 -0.2029 0.2770 1.0000
13.750 2.2883 0.04791 0.04219 -0.2001 0.2718 1.0000
14.000 2.2781 0.05052 0.04510 -0.1961 0.2651 1.0000
14.250 2.2747 0.05267 0.04732 -0.1931 0.2586 1.0000
14.500 2.2675 0.05551 0.05034 -0.1902 0.2514 1.0000
14.750 2.2602 0.05848 0.05337 -0.1876 0.2440 1.0000
15.000 2.2502 0.06209 0.05715 -0.1854 0.2361 1.0000
15.250 2.2389 0.06600 0.06107 -0.1835 0.2284 1.0000
15.500 2.2241 0.07075 0.06600 -0.1821 0.2198 1.0000
15.750 2.2082 0.07580 0.07108 -0.1811 0.2121 1.0000
16.000 2.1887 0.08179 0.07721 -0.1807 0.2035 1.0000
16.250 2.1686 0.08806 0.08356 -0.1809 0.1957 1.0000
16.500 2.1474 0.09474 0.09029 -0.1815 0.1879 1.0000
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Polar data table (+)
Polar graphs
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