S1223 (s1223-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1223 (s1223-il) Reynolds number: 500,000 Max Cl/Cd: 97.44 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1223-il-500000-n5.txt Download as CSV file: xf-s1223-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 0.0436 0.11148 0.10895 -0.0851 0.9422 0.0125
-9.000 0.0483 0.10878 0.10626 -0.0854 0.9340 0.0126
-8.250 0.0686 0.10056 0.09807 -0.0879 0.9120 0.0127
-7.750 0.1049 0.09444 0.09193 -0.0922 0.8896 0.0129
-7.500 0.1606 0.08870 0.08605 -0.1050 0.8698 0.0134
-7.250 0.2416 0.08095 0.07795 -0.1268 0.8261 0.0154
-7.000 0.2676 0.07759 0.07406 -0.1336 0.7367 0.0156
-6.750 0.2651 0.07643 0.07260 -0.1312 0.6753 0.0156
-6.500 0.2636 0.07513 0.07110 -0.1291 0.6316 0.0156
-6.250 0.2640 0.07361 0.06945 -0.1275 0.6022 0.0156
-6.000 0.2642 0.07203 0.06780 -0.1259 0.5789 0.0156
-5.750 0.2635 0.07043 0.06613 -0.1242 0.5614 0.0156
-5.500 0.2621 0.06904 0.06470 -0.1220 0.5463 0.0156
-5.250 0.2601 0.06749 0.06314 -0.1200 0.5343 0.0156
-5.000 0.2636 0.06555 0.06118 -0.1192 0.5234 0.0156
-4.500 0.2713 0.06049 0.05607 -0.1182 0.5052 0.0126
-4.000 0.5776 0.01777 0.01162 -0.2346 0.4835 0.0123
-3.750 0.6441 0.01604 0.00930 -0.2443 0.4704 0.0129
-3.500 0.6801 0.01579 0.00893 -0.2463 0.4616 0.0134
-3.250 0.7163 0.01556 0.00854 -0.2483 0.4530 0.0141
-3.000 0.7573 0.01511 0.00785 -0.2512 0.4456 0.0151
-2.750 0.7974 0.01472 0.00722 -0.2538 0.4384 0.0157
-2.500 0.8359 0.01443 0.00683 -0.2562 0.4313 0.0164
-2.250 0.8713 0.01427 0.00659 -0.2578 0.4256 0.0172
-2.000 0.9065 0.01413 0.00636 -0.2593 0.4197 0.0182
-1.750 0.9414 0.01405 0.00617 -0.2607 0.4136 0.0193
-1.500 0.9745 0.01402 0.00609 -0.2618 0.4083 0.0209
-1.250 1.0076 0.01399 0.00598 -0.2628 0.4031 0.0223
-1.000 1.0417 0.01395 0.00588 -0.2640 0.3980 0.0236
-0.750 1.0733 0.01401 0.00586 -0.2647 0.3934 0.0252
-0.500 1.1048 0.01405 0.00585 -0.2653 0.3897 0.0278
-0.250 1.1355 0.01409 0.00585 -0.2658 0.3861 0.0307
0.000 1.1665 0.01415 0.00590 -0.2663 0.3824 0.0376
0.250 1.2030 0.01410 0.00600 -0.2682 0.3782 0.1183
0.500 1.2343 0.01420 0.00619 -0.2689 0.3742 0.1954
0.750 1.2630 0.01432 0.00636 -0.2690 0.3713 0.2244
1.000 1.2912 0.01445 0.00652 -0.2689 0.3686 0.2498
1.250 1.3189 0.01460 0.00667 -0.2687 0.3658 0.2658
1.500 1.3462 0.01477 0.00683 -0.2684 0.3629 0.2791
1.750 1.3733 0.01496 0.00700 -0.2681 0.3598 0.2895
2.000 1.3999 0.01517 0.00718 -0.2677 0.3569 0.2985
2.250 1.4267 0.01537 0.00738 -0.2674 0.3544 0.3097
2.500 1.4539 0.01553 0.00757 -0.2671 0.3526 0.3218
2.750 1.4808 0.01571 0.00777 -0.2668 0.3506 0.3366
3.250 1.5340 0.01610 0.00823 -0.2661 0.3462 0.3731
3.750 1.5862 0.01656 0.00874 -0.2652 0.3414 0.4159
4.000 1.6120 0.01683 0.00904 -0.2647 0.3391 0.4414
4.500 1.6647 0.01729 0.00963 -0.2640 0.3358 0.5049
4.750 1.6915 0.01750 0.00994 -0.2637 0.3342 0.5465
5.000 1.7182 0.01773 0.01028 -0.2635 0.3323 0.5929
5.250 1.7449 0.01797 0.01062 -0.2632 0.3300 0.6456
5.500 1.7715 0.01822 0.01099 -0.2629 0.3278 0.7119
5.750 1.7968 0.01844 0.01138 -0.2624 0.3256 0.8176
6.250 1.8326 0.01892 0.01193 -0.2582 0.3207 1.0000
6.500 1.8563 0.01920 0.01225 -0.2574 0.3187 1.0000
6.750 1.8799 0.01948 0.01258 -0.2565 0.3163 1.0000
7.000 1.9028 0.01978 0.01291 -0.2555 0.3134 1.0000
7.250 1.9251 0.02013 0.01327 -0.2544 0.3103 1.0000
7.500 1.9467 0.02051 0.01366 -0.2533 0.3076 1.0000
7.750 1.9679 0.02094 0.01410 -0.2520 0.3051 1.0000
8.000 1.9893 0.02136 0.01454 -0.2508 0.3026 1.0000
8.250 2.0117 0.02166 0.01492 -0.2498 0.2997 1.0000
8.500 2.0330 0.02203 0.01534 -0.2486 0.2962 1.0000
8.750 2.0530 0.02247 0.01580 -0.2472 0.2919 1.0000
9.000 2.0719 0.02299 0.01632 -0.2456 0.2883 1.0000
9.250 2.0924 0.02341 0.01680 -0.2443 0.2843 1.0000
9.500 2.1121 0.02386 0.01730 -0.2429 0.2785 1.0000
9.750 2.1285 0.02450 0.01792 -0.2410 0.2720 1.0000
10.000 2.1478 0.02499 0.01848 -0.2395 0.2664 1.0000
10.250 2.1652 0.02561 0.01912 -0.2378 0.2603 1.0000
10.500 2.1814 0.02631 0.01984 -0.2359 0.2551 1.0000
10.750 2.1977 0.02700 0.02057 -0.2341 0.2477 1.0000
11.000 2.2117 0.02787 0.02145 -0.2319 0.2409 1.0000
11.250 2.2261 0.02871 0.02233 -0.2299 0.2334 1.0000
11.500 2.2379 0.02976 0.02339 -0.2275 0.2256 1.0000
11.750 2.2488 0.03089 0.02454 -0.2250 0.2161 1.0000
12.000 2.2586 0.03213 0.02579 -0.2225 0.2072 1.0000
12.250 2.2639 0.03375 0.02739 -0.2194 0.1954 1.0000
12.500 2.2680 0.03550 0.02914 -0.2164 0.1853 1.0000
12.750 2.2723 0.03729 0.03095 -0.2134 0.1754 1.0000
13.000 2.2750 0.03928 0.03296 -0.2105 0.1671 1.0000
13.250 2.2750 0.04157 0.03528 -0.2075 0.1587 1.0000
13.500 2.2765 0.04379 0.03755 -0.2048 0.1515 1.0000
13.750 2.2735 0.04656 0.04036 -0.2020 0.1446 1.0000
14.000 2.2721 0.04927 0.04313 -0.1995 0.1378 1.0000
14.250 2.2659 0.05264 0.04656 -0.1970 0.1320 1.0000
14.500 2.2614 0.05598 0.04999 -0.1950 0.1260 1.0000
14.750 2.2525 0.06002 0.05411 -0.1932 0.1210 1.0000
15.000 2.2438 0.06426 0.05845 -0.1918 0.1163 1.0000
15.250 2.2313 0.06927 0.06356 -0.1908 0.1112 1.0000
15.500 2.2156 0.07501 0.06942 -0.1902 0.1074 1.0000
15.750 2.2020 0.08068 0.07522 -0.1902 0.1038 1.0000
16.000 2.1834 0.08736 0.08204 -0.1906 0.1003 1.0000
16.250 2.1607 0.09491 0.08971 -0.1916 0.0973 1.0000
16.500 2.1422 0.10184 0.09679 -0.1927 0.0947 1.0000
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Polar data table (+)
Polar graphs
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