S1223 RTL (s1223rtl-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1223 RTL (s1223rtl-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.7 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1223rtl-il-1000000.txt Download as CSV file: xf-s1223rtl-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 0.0740 0.10979 0.10801 -0.0969 0.9489 0.0119
-9.750 0.0806 0.10648 0.10471 -0.0986 0.9437 0.0119
-9.500 0.0849 0.10361 0.10185 -0.0977 0.9356 0.0121
-9.250 0.0972 0.10088 0.09912 -0.0989 0.9279 0.0121
-9.000 0.1231 0.09729 0.09549 -0.1036 0.9152 0.0123
-8.750 0.2506 0.08668 0.08401 -0.1377 0.7921 0.0136
-8.500 0.2414 0.08728 0.08320 -0.1331 0.4904 0.0139
-8.250 0.2478 0.08495 0.08072 -0.1337 0.4544 0.0144
-8.000 0.2478 0.08221 0.07792 -0.1345 0.4378 0.0147
-7.750 0.2517 0.08000 0.07569 -0.1346 0.4258 0.0147
-7.500 0.2554 0.07778 0.07344 -0.1343 0.4151 0.0148
-7.250 0.2598 0.07565 0.07128 -0.1334 0.4036 0.0150
-7.000 0.2669 0.07414 0.06975 -0.1326 0.3948 0.0151
-6.750 0.2732 0.07270 0.06829 -0.1316 0.3882 0.0152
-6.500 0.2778 0.07124 0.06682 -0.1305 0.3806 0.0154
-6.250 0.2808 0.06969 0.06528 -0.1293 0.3770 0.0155
-6.000 0.2818 0.06814 0.06376 -0.1278 0.3734 0.0156
-5.750 0.2808 0.06678 0.06241 -0.1257 0.3698 0.0159
-5.500 0.2752 0.06551 0.06116 -0.1228 0.3665 0.0160
-5.250 0.2702 0.06401 0.05968 -0.1201 0.3626 0.0164
-5.000 0.4702 0.01653 0.01054 -0.2289 0.3636 0.0150
-4.750 0.5191 0.01524 0.00898 -0.2344 0.3580 0.0153
-4.500 0.5571 0.01469 0.00829 -0.2369 0.3537 0.0157
-4.250 0.5909 0.01442 0.00791 -0.2382 0.3490 0.0162
-4.000 0.6259 0.01410 0.00743 -0.2398 0.3434 0.0169
-3.750 0.6620 0.01373 0.00691 -0.2416 0.3397 0.0175
-3.500 0.7009 0.01323 0.00628 -0.2440 0.3373 0.0182
-3.250 0.7354 0.01299 0.00600 -0.2454 0.3344 0.0189
-3.000 0.7677 0.01287 0.00582 -0.2462 0.3314 0.0197
-2.750 0.8000 0.01278 0.00564 -0.2470 0.3281 0.0206
-2.500 0.8325 0.01270 0.00547 -0.2479 0.3242 0.0214
-2.250 0.8658 0.01260 0.00533 -0.2490 0.3215 0.0228
-2.000 0.8962 0.01257 0.00527 -0.2493 0.3199 0.0245
-1.750 0.9292 0.01246 0.00513 -0.2503 0.3179 0.0264
-1.500 0.9595 0.01246 0.00509 -0.2507 0.3157 0.0285
-1.250 0.9908 0.01243 0.00502 -0.2512 0.3135 0.0316
-1.000 1.0209 0.01245 0.00501 -0.2516 0.3111 0.0363
-0.750 1.0510 0.01249 0.00503 -0.2519 0.3085 0.0459
-0.500 1.0835 0.01250 0.00512 -0.2529 0.3051 0.0960
-0.250 1.1176 0.01240 0.00526 -0.2543 0.3035 0.2034
0.000 1.1463 0.01245 0.00535 -0.2543 0.3023 0.2369
0.250 1.1743 0.01252 0.00545 -0.2542 0.3009 0.2598
0.500 1.2019 0.01262 0.00556 -0.2540 0.2992 0.2791
0.750 1.2291 0.01272 0.00567 -0.2537 0.2974 0.2968
1.000 1.2561 0.01285 0.00581 -0.2534 0.2957 0.3193
1.250 1.2829 0.01299 0.00598 -0.2530 0.2938 0.3433
1.500 1.3088 0.01316 0.00613 -0.2525 0.2918 0.3571
1.750 1.3346 0.01338 0.00634 -0.2519 0.2894 0.3713
2.000 1.3596 0.01365 0.00661 -0.2512 0.2868 0.3840
2.250 1.3858 0.01377 0.00674 -0.2507 0.2861 0.3968
2.500 1.4121 0.01390 0.00690 -0.2503 0.2851 0.4107
2.750 1.4381 0.01404 0.00706 -0.2498 0.2839 0.4242
3.250 1.4895 0.01435 0.00740 -0.2487 0.2809 0.4500
3.500 1.5149 0.01452 0.00759 -0.2481 0.2795 0.4624
3.750 1.5400 0.01472 0.00779 -0.2474 0.2780 0.4755
4.000 1.5650 0.01493 0.00802 -0.2468 0.2764 0.4898
4.250 1.5896 0.01517 0.00826 -0.2461 0.2745 0.5029
4.500 1.6135 0.01548 0.00857 -0.2453 0.2723 0.5161
4.750 1.6374 0.01581 0.00892 -0.2445 0.2703 0.5303
5.000 1.6627 0.01597 0.00913 -0.2439 0.2696 0.5467
5.250 1.6877 0.01615 0.00935 -0.2433 0.2686 0.5641
5.500 1.7124 0.01634 0.00960 -0.2427 0.2674 0.5824
5.750 1.7370 0.01655 0.00987 -0.2421 0.2662 0.6045
6.000 1.7617 0.01678 0.01016 -0.2415 0.2649 0.6331
6.250 1.7867 0.01700 0.01046 -0.2410 0.2636 0.6749
6.500 1.8085 0.01695 0.01080 -0.2398 0.2623 1.0000
6.750 1.8314 0.01724 0.01109 -0.2389 0.2608 1.0000
7.000 1.8539 0.01758 0.01141 -0.2379 0.2593 1.0000
7.250 1.8756 0.01798 0.01180 -0.2368 0.2572 1.0000
7.500 1.8966 0.01849 0.01230 -0.2356 0.2548 1.0000
7.750 1.9194 0.01874 0.01259 -0.2346 0.2541 1.0000
8.000 1.9417 0.01903 0.01291 -0.2337 0.2534 1.0000
8.250 1.9638 0.01933 0.01325 -0.2326 0.2524 1.0000
8.500 1.9856 0.01965 0.01360 -0.2316 0.2513 1.0000
8.750 2.0073 0.01999 0.01397 -0.2306 0.2502 1.0000
9.000 2.0288 0.02034 0.01434 -0.2295 0.2490 1.0000
9.250 2.0498 0.02070 0.01474 -0.2284 0.2477 1.0000
9.500 2.0701 0.02111 0.01517 -0.2271 0.2464 1.0000
9.750 2.0899 0.02155 0.01563 -0.2258 0.2449 1.0000
10.000 2.1091 0.02205 0.01614 -0.2245 0.2432 1.0000
10.250 2.1273 0.02268 0.01677 -0.2230 0.2410 1.0000
10.500 2.1460 0.02325 0.01739 -0.2216 0.2396 1.0000
10.750 2.1658 0.02366 0.01786 -0.2204 0.2390 1.0000
11.000 2.1854 0.02409 0.01835 -0.2191 0.2381 1.0000
11.250 2.2048 0.02455 0.01887 -0.2179 0.2372 1.0000
11.500 2.2235 0.02504 0.01942 -0.2166 0.2360 1.0000
11.750 2.2418 0.02555 0.01998 -0.2152 0.2348 1.0000
12.000 2.2600 0.02608 0.02057 -0.2139 0.2335 1.0000
12.250 2.2776 0.02665 0.02118 -0.2124 0.2322 1.0000
12.500 2.2940 0.02730 0.02188 -0.2109 0.2309 1.0000
12.750 2.3093 0.02803 0.02264 -0.2092 0.2290 1.0000
13.000 2.3228 0.02897 0.02360 -0.2073 0.2265 1.0000
13.250 2.3386 0.02966 0.02436 -0.2058 0.2249 1.0000
13.500 2.3557 0.03023 0.02502 -0.2045 0.2237 1.0000
13.750 2.3725 0.03085 0.02571 -0.2031 0.2222 1.0000
14.000 2.3883 0.03152 0.02645 -0.2017 0.2203 1.0000
14.250 2.4035 0.03224 0.02723 -0.2002 0.2180 1.0000
14.500 2.4168 0.03316 0.02819 -0.1986 0.2160 1.0000
14.750 2.4254 0.03444 0.02948 -0.1964 0.2114 1.0000
15.000 2.4451 0.03479 0.02991 -0.1957 0.2071 1.0000
15.250 2.4568 0.03584 0.03098 -0.1940 0.2026 1.0000
15.500 2.4650 0.03724 0.03240 -0.1920 0.1980 1.0000
15.750 2.4789 0.03815 0.03340 -0.1907 0.1954 1.0000
16.000 2.4893 0.03939 0.03468 -0.1891 0.1909 1.0000
16.250 2.4942 0.04116 0.03647 -0.1870 0.1860 1.0000
16.500 2.5040 0.04250 0.03788 -0.1855 0.1814 1.0000
16.750 2.5075 0.04448 0.03989 -0.1835 0.1755 1.0000
17.000 2.5108 0.04653 0.04199 -0.1816 0.1702 1.0000
17.250 2.5113 0.04890 0.04441 -0.1797 0.1639 1.0000
17.500 2.5072 0.05186 0.04740 -0.1776 0.1569 1.0000
17.750 2.4937 0.05599 0.05154 -0.1753 0.1469 1.0000
18.000 2.4733 0.06118 0.05676 -0.1732 0.1367 1.0000
18.250 2.4564 0.06619 0.06184 -0.1718 0.1292 1.0000
18.500 2.4252 0.07349 0.06922 -0.1708 0.1207 1.0000
18.750 2.3833 0.08301 0.07887 -0.1712 0.1136 1.0000
19.000 2.3549 0.09110 0.08714 -0.1725 0.1114 1.0000
19.250 2.3125 0.10212 0.09837 -0.1756 0.1090 1.0000
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