S1223 RTL (s1223rtl-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1223 RTL (s1223rtl-il) Reynolds number: 500,000 Max Cl/Cd: 84.04 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1223rtl-il-500000.txt Download as CSV file: xf-s1223rtl-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 0.0942 0.10030 0.09800 -0.0912 0.9338 0.0184
-8.250 0.1068 0.09753 0.09523 -0.0926 0.9271 0.0187
-7.750 0.1259 0.09240 0.09011 -0.0939 0.9065 0.0198
-7.500 0.1434 0.08858 0.08626 -0.0982 0.8953 0.0209
-7.250 0.1625 0.08329 0.08093 -0.1073 0.8838 0.0212
-7.000 0.2733 0.07620 0.07226 -0.1304 0.6144 0.0220
-6.750 0.2657 0.07611 0.07152 -0.1263 0.4826 0.0221
-6.500 0.2680 0.07476 0.07004 -0.1249 0.4524 0.0226
-6.250 0.2698 0.07326 0.06848 -0.1236 0.4376 0.0231
-6.000 0.2702 0.07172 0.06691 -0.1221 0.4267 0.0233
-5.750 0.2652 0.07011 0.06530 -0.1201 0.4191 0.0242
-5.500 0.2530 0.06865 0.06390 -0.1171 0.4150 0.0245
-5.250 0.2399 0.06478 0.06011 -0.1181 0.4128 0.0248
-5.000 0.2448 0.06318 0.05848 -0.1163 0.4053 0.0250
-4.750 0.2515 0.06208 0.05735 -0.1143 0.3984 0.0252
-4.500 0.2595 0.06053 0.05581 -0.1137 0.3937 0.0255
-4.250 0.2682 0.05885 0.05413 -0.1135 0.3891 0.0262
-4.000 0.2779 0.05663 0.05189 -0.1147 0.3847 0.0269
-3.750 0.2922 0.03601 0.03153 -0.1116 0.3771 0.0294
-3.500 0.6155 0.01873 0.01159 -0.2247 0.3714 0.0250
-3.250 0.6643 0.01735 0.00984 -0.2297 0.3661 0.0251
-3.000 0.7018 0.01679 0.00911 -0.2320 0.3605 0.0259
-2.750 0.7386 0.01632 0.00853 -0.2338 0.3575 0.0268
-2.500 0.7748 0.01593 0.00801 -0.2355 0.3543 0.0279
-2.250 0.8106 0.01561 0.00760 -0.2371 0.3509 0.0297
-2.000 0.8432 0.01550 0.00743 -0.2380 0.3476 0.0317
-1.750 0.8769 0.01541 0.00722 -0.2391 0.3441 0.0334
-1.500 0.9121 0.01537 0.00713 -0.2407 0.3405 0.0361
-1.250 0.9464 0.01523 0.00698 -0.2420 0.3385 0.0399
-1.000 0.9795 0.01516 0.00689 -0.2430 0.3359 0.0456
-0.750 1.0126 0.01512 0.00682 -0.2440 0.3332 0.0554
-0.500 1.0546 0.01482 0.00684 -0.2472 0.3304 0.1856
-0.250 1.0843 0.01493 0.00701 -0.2476 0.3280 0.2497
0.000 1.1119 0.01515 0.00720 -0.2474 0.3254 0.2782
0.250 1.1407 0.01551 0.00750 -0.2475 0.3221 0.3010
0.500 1.1679 0.01562 0.00765 -0.2472 0.3209 0.3209
0.750 1.1950 0.01576 0.00782 -0.2468 0.3193 0.3433
1.000 1.2217 0.01593 0.00801 -0.2464 0.3174 0.3666
1.250 1.2484 0.01609 0.00817 -0.2461 0.3153 0.3817
1.500 1.2750 0.01627 0.00833 -0.2456 0.3132 0.3961
1.750 1.3018 0.01645 0.00852 -0.2453 0.3112 0.4098
2.000 1.3283 0.01668 0.00872 -0.2449 0.3093 0.4238
2.250 1.3550 0.01697 0.00898 -0.2446 0.3072 0.4390
2.500 1.3839 0.01739 0.00935 -0.2448 0.3045 0.4542
2.750 1.4106 0.01760 0.00961 -0.2444 0.3032 0.4683
3.000 1.4363 0.01778 0.00983 -0.2439 0.3020 0.4824
3.250 1.4618 0.01798 0.01006 -0.2433 0.3005 0.4975
3.500 1.4871 0.01819 0.01029 -0.2427 0.2988 0.5130
3.750 1.5123 0.01841 0.01054 -0.2421 0.2970 0.5280
4.000 1.5374 0.01864 0.01080 -0.2415 0.2952 0.5431
4.250 1.5626 0.01888 0.01107 -0.2410 0.2936 0.5598
4.500 1.5878 0.01915 0.01135 -0.2404 0.2920 0.5782
4.750 1.6136 0.01947 0.01168 -0.2400 0.2903 0.5979
5.000 1.6417 0.01989 0.01211 -0.2402 0.2882 0.6210
5.250 1.6708 0.02029 0.01257 -0.2405 0.2864 0.6509
5.500 1.6960 0.02049 0.01292 -0.2400 0.2854 0.6949
5.750 1.7119 0.02037 0.01316 -0.2375 0.2842 1.0000
6.000 1.7352 0.02066 0.01347 -0.2366 0.2828 1.0000
6.250 1.7583 0.02096 0.01378 -0.2357 0.2812 1.0000
6.500 1.7815 0.02129 0.01411 -0.2349 0.2797 1.0000
6.750 1.8046 0.02162 0.01445 -0.2340 0.2782 1.0000
7.000 1.8274 0.02197 0.01480 -0.2331 0.2768 1.0000
7.250 1.8499 0.02234 0.01517 -0.2322 0.2754 1.0000
7.500 1.8728 0.02275 0.01557 -0.2313 0.2740 1.0000
7.750 1.8976 0.02325 0.01605 -0.2309 0.2723 1.0000
8.000 1.9257 0.02385 0.01663 -0.2312 0.2702 1.0000
8.250 1.9447 0.02419 0.01705 -0.2296 0.2693 1.0000
8.500 1.9646 0.02457 0.01750 -0.2282 0.2681 1.0000
8.750 1.9852 0.02498 0.01798 -0.2270 0.2669 1.0000
9.000 2.0056 0.02541 0.01846 -0.2258 0.2655 1.0000
9.250 2.0260 0.02586 0.01896 -0.2246 0.2642 1.0000
9.500 2.0460 0.02631 0.01946 -0.2233 0.2628 1.0000
9.750 2.0658 0.02679 0.01998 -0.2221 0.2615 1.0000
10.000 2.0854 0.02727 0.02050 -0.2208 0.2602 1.0000
10.250 2.1046 0.02777 0.02103 -0.2195 0.2589 1.0000
10.500 2.1246 0.02833 0.02161 -0.2183 0.2574 1.0000
10.750 2.1501 0.02904 0.02231 -0.2183 0.2553 1.0000
11.000 2.1689 0.02965 0.02301 -0.2170 0.2542 1.0000
11.250 2.1848 0.03025 0.02372 -0.2152 0.2533 1.0000
11.500 2.2008 0.03088 0.02446 -0.2134 0.2521 1.0000
11.750 2.2170 0.03153 0.02521 -0.2117 0.2509 1.0000
12.000 2.2329 0.03220 0.02598 -0.2100 0.2497 1.0000
12.250 2.2483 0.03289 0.02675 -0.2083 0.2483 1.0000
12.500 2.2634 0.03358 0.02752 -0.2065 0.2469 1.0000
12.750 2.2781 0.03429 0.02829 -0.2048 0.2455 1.0000
13.000 2.2934 0.03503 0.02909 -0.2032 0.2443 1.0000
13.250 2.3087 0.03582 0.02994 -0.2016 0.2431 1.0000
13.500 2.3261 0.03665 0.03081 -0.2004 0.2415 1.0000
13.750 2.3452 0.03760 0.03182 -0.1996 0.2396 1.0000
14.000 2.3510 0.03867 0.03305 -0.1967 0.2384 1.0000
14.250 2.3559 0.03979 0.03432 -0.1939 0.2366 1.0000
14.500 2.3633 0.04091 0.03557 -0.1915 0.2348 1.0000
14.750 2.3710 0.04203 0.03679 -0.1893 0.2329 1.0000
15.000 2.3798 0.04315 0.03800 -0.1873 0.2311 1.0000
15.250 2.3881 0.04437 0.03929 -0.1854 0.2294 1.0000
15.500 2.3976 0.04561 0.04056 -0.1836 0.2274 1.0000
15.750 2.4032 0.04719 0.04223 -0.1816 0.2247 1.0000
16.000 2.4006 0.04915 0.04438 -0.1790 0.2216 1.0000
16.250 2.4023 0.05095 0.04629 -0.1770 0.2180 1.0000
16.500 2.4036 0.05293 0.04831 -0.1752 0.2142 1.0000
16.750 2.4037 0.05526 0.05072 -0.1735 0.2103 1.0000
17.000 2.4061 0.05746 0.05310 -0.1721 0.2067 1.0000
17.250 2.4072 0.05989 0.05562 -0.1708 0.2031 1.0000
17.500 2.4041 0.06289 0.05868 -0.1695 0.1998 1.0000
17.750 2.4022 0.06591 0.06183 -0.1685 0.1969 1.0000
18.000 2.4012 0.06894 0.06504 -0.1677 0.1934 1.0000
18.250 2.3940 0.07284 0.06904 -0.1670 0.1894 1.0000
18.500 2.3802 0.07780 0.07408 -0.1667 0.1859 1.0000
18.750 2.3705 0.08244 0.07890 -0.1668 0.1818 1.0000
19.000 2.3531 0.08841 0.08503 -0.1675 0.1777 1.0000
19.250 2.3258 0.09621 0.09296 -0.1691 0.1740 1.0000
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Polar data table (+)
Polar graphs
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