S1223 RTL (s1223rtl-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1223 RTL (s1223rtl-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.75 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1223rtl-il-1000000-n5.txt Download as CSV file: xf-s1223rtl-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 0.2120 0.09464 0.08989 -0.1343 0.3797 0.0086
-7.500 0.1359 0.01960 0.01432 -0.2124 0.3856 0.0096
-7.250 0.1911 0.01776 0.01219 -0.2212 0.3755 0.0098
-7.000 0.2348 0.01677 0.01099 -0.2260 0.3673 0.0100
-6.750 0.2750 0.01604 0.01007 -0.2295 0.3598 0.0101
-6.500 0.3132 0.01545 0.00934 -0.2323 0.3547 0.0103
-6.250 0.3506 0.01493 0.00867 -0.2348 0.3487 0.0105
-6.000 0.3872 0.01449 0.00808 -0.2370 0.3425 0.0108
-5.750 0.4230 0.01411 0.00756 -0.2389 0.3386 0.0111
-5.500 0.4579 0.01378 0.00713 -0.2405 0.3353 0.0114
-5.250 0.4913 0.01355 0.00679 -0.2417 0.3317 0.0117
-5.000 0.5243 0.01336 0.00648 -0.2428 0.3281 0.0119
-4.750 0.5607 0.01303 0.00605 -0.2448 0.3241 0.0124
-4.500 0.5933 0.01288 0.00583 -0.2457 0.3212 0.0128
-4.250 0.6255 0.01275 0.00565 -0.2466 0.3189 0.0132
-4.000 0.6576 0.01263 0.00547 -0.2473 0.3161 0.0136
-3.750 0.6895 0.01254 0.00530 -0.2481 0.3133 0.0141
-3.500 0.7210 0.01247 0.00516 -0.2487 0.3106 0.0145
-3.250 0.7528 0.01240 0.00501 -0.2494 0.3078 0.0150
-3.000 0.7841 0.01235 0.00492 -0.2500 0.3048 0.0157
-2.750 0.8145 0.01233 0.00486 -0.2504 0.3033 0.0165
-2.500 0.8446 0.01231 0.00480 -0.2507 0.3019 0.0174
-2.250 0.8751 0.01229 0.00475 -0.2511 0.3002 0.0186
-2.000 0.9049 0.01229 0.00473 -0.2513 0.2982 0.0198
-1.750 0.9342 0.01232 0.00471 -0.2514 0.2959 0.0211
-1.500 0.9639 0.01234 0.00470 -0.2517 0.2935 0.0229
-1.250 0.9928 0.01240 0.00471 -0.2517 0.2912 0.0250
-1.000 1.0216 0.01246 0.00474 -0.2517 0.2889 0.0284
-0.750 1.0503 0.01252 0.00479 -0.2517 0.2867 0.0334
-0.500 1.0794 0.01255 0.00484 -0.2518 0.2859 0.0421
-0.250 1.1090 0.01257 0.00490 -0.2521 0.2847 0.0620
0.000 1.1401 0.01256 0.00497 -0.2527 0.2833 0.1073
0.250 1.1715 0.01253 0.00508 -0.2535 0.2817 0.1788
0.500 1.2000 0.01260 0.00520 -0.2535 0.2797 0.2135
0.750 1.2275 0.01271 0.00532 -0.2533 0.2778 0.2352
1.000 1.2552 0.01282 0.00546 -0.2531 0.2759 0.2644
1.250 1.2824 0.01295 0.00562 -0.2529 0.2740 0.2940
1.500 1.3087 0.01310 0.00577 -0.2524 0.2721 0.3062
1.750 1.3345 0.01327 0.00593 -0.2519 0.2703 0.3170
2.000 1.3608 0.01340 0.00608 -0.2514 0.2696 0.3279
2.250 1.3867 0.01354 0.00622 -0.2509 0.2686 0.3377
2.500 1.4128 0.01369 0.00639 -0.2504 0.2675 0.3501
2.750 1.4386 0.01384 0.00655 -0.2499 0.2662 0.3619
3.000 1.4642 0.01401 0.00673 -0.2493 0.2645 0.3735
3.250 1.4896 0.01418 0.00691 -0.2487 0.2628 0.3839
3.500 1.5148 0.01437 0.00710 -0.2481 0.2612 0.3951
3.750 1.5400 0.01456 0.00731 -0.2475 0.2596 0.4072
4.000 1.5649 0.01477 0.00752 -0.2468 0.2580 0.4194
4.250 1.5896 0.01500 0.00775 -0.2461 0.2562 0.4310
4.500 1.6141 0.01523 0.00799 -0.2454 0.2547 0.4412
4.750 1.6389 0.01542 0.00822 -0.2448 0.2540 0.4529
5.000 1.6638 0.01561 0.00845 -0.2441 0.2531 0.4658
5.250 1.6882 0.01582 0.00869 -0.2434 0.2519 0.4781
5.500 1.7123 0.01604 0.00894 -0.2426 0.2506 0.4900
5.750 1.7362 0.01627 0.00921 -0.2419 0.2490 0.5032
6.000 1.7599 0.01651 0.00948 -0.2411 0.2476 0.5172
6.500 1.8069 0.01704 0.01007 -0.2394 0.2448 0.5483
6.750 1.8303 0.01732 0.01039 -0.2386 0.2433 0.5664
7.000 1.8535 0.01763 0.01073 -0.2378 0.2417 0.5872
7.250 1.8765 0.01796 0.01111 -0.2369 0.2399 0.6121
7.500 1.9004 0.01821 0.01145 -0.2363 0.2392 0.6436
7.750 1.9251 0.01847 0.01183 -0.2358 0.2382 0.7006
8.250 1.9672 0.01882 0.01255 -0.2334 0.2359 1.0000
8.500 1.9889 0.01916 0.01291 -0.2323 0.2347 1.0000
8.750 2.0103 0.01951 0.01329 -0.2312 0.2335 1.0000
9.000 2.0315 0.01988 0.01368 -0.2301 0.2321 1.0000
9.250 2.0522 0.02028 0.01410 -0.2289 0.2308 1.0000
9.500 2.0722 0.02071 0.01454 -0.2276 0.2294 1.0000
9.750 2.0919 0.02116 0.01502 -0.2263 0.2278 1.0000
10.000 2.1112 0.02166 0.01553 -0.2250 0.2261 1.0000
10.250 2.1313 0.02208 0.01600 -0.2238 0.2250 1.0000
10.500 2.1511 0.02251 0.01648 -0.2225 0.2241 1.0000
10.750 2.1706 0.02295 0.01698 -0.2212 0.2232 1.0000
11.000 2.1898 0.02342 0.01749 -0.2200 0.2222 1.0000
11.250 2.2089 0.02390 0.01803 -0.2187 0.2210 1.0000
11.500 2.2272 0.02443 0.01860 -0.2173 0.2198 1.0000
11.750 2.2450 0.02498 0.01920 -0.2158 0.2184 1.0000
12.000 2.2626 0.02556 0.01983 -0.2144 0.2170 1.0000
12.250 2.2795 0.02620 0.02050 -0.2129 0.2154 1.0000
12.500 2.2954 0.02690 0.02124 -0.2112 0.2138 1.0000
12.750 2.3104 0.02767 0.02205 -0.2095 0.2117 1.0000
13.000 2.3280 0.02824 0.02269 -0.2082 0.2105 1.0000
13.250 2.3447 0.02887 0.02339 -0.2068 0.2085 1.0000
13.500 2.3605 0.02958 0.02416 -0.2053 0.2065 1.0000
13.750 2.3756 0.03035 0.02498 -0.2037 0.2043 1.0000
14.000 2.3888 0.03127 0.02594 -0.2020 0.2015 1.0000
14.250 2.4009 0.03231 0.02700 -0.2001 0.1981 1.0000
14.500 2.4157 0.03311 0.02789 -0.1987 0.1963 1.0000
14.750 2.4270 0.03423 0.02901 -0.1969 0.1894 1.0000
15.000 2.4351 0.03566 0.03043 -0.1948 0.1804 1.0000
15.250 2.4392 0.03747 0.03221 -0.1924 0.1708 1.0000
15.500 2.4400 0.03963 0.03435 -0.1897 0.1603 1.0000
15.750 2.4425 0.04168 0.03641 -0.1874 0.1519 1.0000
16.000 2.4344 0.04485 0.03955 -0.1844 0.1392 1.0000
16.250 2.4239 0.04837 0.04307 -0.1814 0.1280 1.0000
16.500 2.3987 0.05372 0.04840 -0.1780 0.1124 1.0000
16.750 2.3790 0.05876 0.05348 -0.1756 0.1031 1.0000
17.000 2.3440 0.06610 0.06087 -0.1735 0.0911 1.0000
17.250 2.3041 0.07488 0.06975 -0.1727 0.0819 1.0000
17.500 2.2652 0.08440 0.07944 -0.1735 0.0767 1.0000
17.750 2.2327 0.09374 0.08898 -0.1756 0.0757 1.0000
18.000 2.2000 0.10363 0.09911 -0.1786 0.0759 1.0000
18.250 2.1468 0.11734 0.11308 -0.1835 0.0753 1.0000
18.500 2.1066 0.12834 0.12429 -0.1876 0.0760 1.0000
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