S1223 RTL (s1223rtl-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1223 RTL (s1223rtl-il) Reynolds number: 200,000 Max Cl/Cd: 98.03 at α=-1.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1223rtl-il-200000.txt Download as CSV file: xf-s1223rtl-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: S1223 RTL
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
------ -------- --------- --------- -------- -------- --------
-6.250 0.1145 0.08921 0.08609 -0.0834 0.9043 0.0417
-6.000 0.1188 0.08675 0.08365 -0.0845 0.8921 0.0430
-5.750 0.1056 0.08536 0.08230 -0.0864 0.8792 0.0437
-5.500 0.1250 0.08139 0.07834 -0.0863 0.8645 0.0441
-5.250 0.1583 0.07728 0.07417 -0.0882 0.8400 0.0459
-5.000 0.2853 0.06628 0.06199 -0.1204 0.6366 0.0513
-4.750 0.2674 0.06673 0.06172 -0.1131 0.5227 0.0519
-4.500 0.2656 0.06572 0.06053 -0.1104 0.4958 0.0531
-4.250 0.2779 0.04885 0.04369 -0.1030 0.4613 0.0586
-4.000 0.2872 0.04737 0.04218 -0.1015 0.4528 0.0608
-3.750 0.2874 0.05957 0.05410 -0.1133 0.4605 0.0594
-3.250 0.3961 0.04745 0.04164 -0.1514 0.4434 0.0754
-3.000 0.3954 0.04723 0.04144 -0.1436 0.4373 0.0761
-2.750 0.4040 0.04660 0.04082 -0.1392 0.4313 0.0773
-2.500 0.5209 0.03875 0.03242 -0.1716 0.4223 0.0986
-2.250 0.5887 0.03447 0.02787 -0.1852 0.4158 0.1149
-2.000 0.6052 0.03385 0.02734 -0.1824 0.4110 0.1173
-1.750 0.8488 0.01008 0.00086 -0.2283 0.3968 0.0588
-1.500 0.8853 0.00973 0.00049 -0.2300 0.3926 0.0638
-1.250 0.9244 0.00943 0.00019 -0.2323 0.3883 0.0722
-1.000 0.9737 0.01995 0.01033 -0.2421 0.3867 0.0797
-0.750 1.0287 0.01957 0.01029 -0.2482 0.3824 0.2244
-0.500 1.0632 0.02011 0.01079 -0.2494 0.3788 0.3083
-0.250 1.0904 0.02039 0.01105 -0.2490 0.3757 0.3395
0.000 1.1180 0.02070 0.01138 -0.2487 0.3723 0.3653
0.250 1.1458 0.02107 0.01173 -0.2485 0.3691 0.3917
0.500 1.1748 0.02144 0.01203 -0.2485 0.3663 0.4144
0.750 1.2056 0.02178 0.01230 -0.2490 0.3635 0.4296
1.000 1.2408 0.02236 0.01275 -0.2505 0.3605 0.4454
1.250 1.2699 0.02265 0.01306 -0.2506 0.3583 0.4604
1.500 1.2975 0.02290 0.01334 -0.2504 0.3559 0.4767
1.750 1.3254 0.02319 0.01363 -0.2503 0.3530 0.4935
2.000 1.3535 0.02347 0.01393 -0.2503 0.3502 0.5092
2.250 1.3820 0.02378 0.01424 -0.2504 0.3477 0.5268
2.500 1.4115 0.02415 0.01457 -0.2506 0.3454 0.5453
2.750 1.4424 0.02462 0.01499 -0.2513 0.3432 0.5641
3.000 1.4760 0.02545 0.01577 -0.2526 0.3407 0.5848
3.250 1.5020 0.02573 0.01616 -0.2521 0.3390 0.6049
3.500 1.5283 0.02606 0.01660 -0.2518 0.3370 0.6257
3.750 1.5546 0.02641 0.01706 -0.2515 0.3346 0.6488
4.000 1.5811 0.02677 0.01750 -0.2512 0.3322 0.6765
4.250 1.6070 0.02710 0.01790 -0.2508 0.3299 0.7095
4.500 1.6316 0.02738 0.01830 -0.2501 0.3280 0.7625
4.750 1.6476 0.02745 0.01853 -0.2476 0.3264 1.0000
5.000 1.6775 0.02809 0.01906 -0.2482 0.3245 1.0000
5.250 1.7090 0.02914 0.02000 -0.2493 0.3224 1.0000
5.500 1.7331 0.02976 0.02069 -0.2486 0.3209 1.0000
5.750 1.7559 0.03028 0.02131 -0.2477 0.3191 1.0000
6.000 1.7789 0.03085 0.02195 -0.2469 0.3170 1.0000
6.250 1.8021 0.03142 0.02257 -0.2461 0.3148 1.0000
6.500 1.8254 0.03202 0.02321 -0.2454 0.3128 1.0000
6.750 1.8491 0.03263 0.02387 -0.2447 0.3110 1.0000
7.000 1.8731 0.03324 0.02450 -0.2441 0.3093 1.0000
7.250 1.8980 0.03387 0.02513 -0.2438 0.3078 1.0000
7.500 1.9241 0.03462 0.02587 -0.2437 0.3063 1.0000
7.750 1.9519 0.03582 0.02703 -0.2441 0.3045 1.0000
8.000 1.9701 0.03673 0.02810 -0.2425 0.3029 1.0000
8.250 1.9861 0.03749 0.02905 -0.2405 0.3010 1.0000
8.500 2.0031 0.03836 0.03009 -0.2387 0.2991 1.0000
8.750 2.0211 0.03929 0.03115 -0.2372 0.2973 1.0000
9.000 2.0398 0.04019 0.03216 -0.2359 0.2956 1.0000
9.250 2.0583 0.04107 0.03314 -0.2345 0.2940 1.0000
9.500 2.0775 0.04190 0.03405 -0.2332 0.2924 1.0000
9.750 2.0975 0.04271 0.03493 -0.2321 0.2910 1.0000
10.000 2.1187 0.04348 0.03573 -0.2312 0.2897 1.0000
10.250 2.1432 0.04436 0.03661 -0.2311 0.2882 1.0000
10.500 2.1622 0.04600 0.03835 -0.2302 0.2865 1.0000
10.750 2.1622 0.04750 0.04014 -0.2258 0.2850 1.0000
11.000 2.1605 0.04929 0.04222 -0.2213 0.2833 1.0000
11.250 2.1571 0.05117 0.04435 -0.2166 0.2816 1.0000
11.500 2.1518 0.05303 0.04642 -0.2118 0.2800 1.0000
11.750 2.1490 0.05482 0.04839 -0.2075 0.2784 1.0000
12.000 2.1528 0.05627 0.04997 -0.2042 0.2769 1.0000
12.250 2.1595 0.05754 0.05135 -0.2015 0.2755 1.0000
12.500 2.1704 0.05863 0.05252 -0.1994 0.2741 1.0000
12.750 2.1858 0.05963 0.05358 -0.1980 0.2729 1.0000
13.000 2.2018 0.06089 0.05490 -0.1969 0.2718 1.0000
13.250 2.2204 0.06284 0.05691 -0.1965 0.2705 1.0000
13.500 2.1175 0.07124 0.06589 -0.1824 0.2688 1.0000
13.750 1.3542 0.20888 0.20484 -0.2345 0.2501 1.0000
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Polar data table (+)
Polar graphs
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