S1223 (s1223-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1223 (s1223-il) Reynolds number: 200,000 Max Cl/Cd: 75.26 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1223-il-200000-n5.txt Download as CSV file: xf-s1223-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 0.0667 0.09842 0.09487 -0.0763 0.9040 0.0254
-6.750 0.0725 0.09608 0.09256 -0.0767 0.8926 0.0259
-6.500 0.0805 0.09346 0.08995 -0.0782 0.8821 0.0262
-6.000 0.0941 0.08841 0.08490 -0.0820 0.8553 0.0264
-5.750 0.1166 0.08481 0.08128 -0.0834 0.8412 0.0268
-5.500 0.1460 0.08112 0.07753 -0.0878 0.8237 0.0273
-5.250 0.1899 0.07651 0.07276 -0.0968 0.7995 0.0283
-5.000 0.2411 0.07140 0.06739 -0.1088 0.7613 0.0297
-4.750 0.2695 0.06699 0.06271 -0.1186 0.7172 0.0307
-4.500 0.2893 0.06363 0.05909 -0.1239 0.6727 0.0308
-4.250 0.3000 0.06209 0.05734 -0.1225 0.6362 0.0311
-4.000 0.3079 0.06067 0.05576 -0.1211 0.6086 0.0316
-3.750 0.3164 0.05900 0.05398 -0.1208 0.5878 0.0322
-3.500 0.3360 0.05240 0.04729 -0.1297 0.5753 0.0225
-3.250 0.3493 0.05111 0.04591 -0.1295 0.5594 0.0221
-3.000 0.3716 0.04831 0.04301 -0.1334 0.5462 0.0214
-2.750 0.7154 0.02037 0.01253 -0.2351 0.5196 0.0222
-2.500 0.7671 0.01927 0.01095 -0.2408 0.5067 0.0230
-2.250 0.8084 0.01871 0.01016 -0.2439 0.4952 0.0241
-2.000 0.8473 0.01838 0.00949 -0.2463 0.4856 0.0264
-1.750 0.8846 0.01807 0.00913 -0.2485 0.4766 0.0284
-1.500 0.9219 0.01787 0.00875 -0.2504 0.4689 0.0299
-1.250 0.9601 0.01767 0.00849 -0.2526 0.4617 0.0316
-1.000 0.9950 0.01766 0.00838 -0.2540 0.4548 0.0353
-0.500 1.0668 0.01767 0.00817 -0.2573 0.4429 0.0430
-0.250 1.1020 0.01768 0.00812 -0.2588 0.4368 0.0557
0.000 1.1435 0.01758 0.00827 -0.2620 0.4310 0.1819
0.250 1.1730 0.01778 0.00846 -0.2622 0.4265 0.2324
0.500 1.2015 0.01799 0.00872 -0.2622 0.4220 0.2776
0.750 1.2298 0.01822 0.00893 -0.2622 0.4177 0.3013
1.000 1.2582 0.01846 0.00908 -0.2622 0.4139 0.3130
1.250 1.2871 0.01873 0.00927 -0.2623 0.4103 0.3233
1.750 1.3446 0.01911 0.00966 -0.2624 0.4026 0.3463
2.000 1.3729 0.01935 0.00989 -0.2623 0.3990 0.3609
2.250 1.4012 0.01961 0.01014 -0.2623 0.3958 0.3782
2.500 1.4297 0.01991 0.01041 -0.2624 0.3930 0.3977
2.750 1.4584 0.02020 0.01070 -0.2625 0.3901 0.4199
3.000 1.4865 0.02043 0.01102 -0.2625 0.3870 0.4460
3.250 1.5143 0.02069 0.01134 -0.2624 0.3838 0.4772
3.500 1.5420 0.02096 0.01168 -0.2623 0.3809 0.5148
3.750 1.5696 0.02125 0.01203 -0.2622 0.3783 0.5584
4.000 1.5966 0.02156 0.01240 -0.2620 0.3759 0.6082
4.250 1.6235 0.02189 0.01277 -0.2617 0.3735 0.6698
4.500 1.6469 0.02207 0.01314 -0.2607 0.3711 0.7589
5.000 1.6836 0.02237 0.01365 -0.2565 0.3661 1.0000
5.250 1.7090 0.02274 0.01402 -0.2560 0.3637 1.0000
5.500 1.7340 0.02313 0.01440 -0.2554 0.3614 1.0000
5.750 1.7587 0.02353 0.01478 -0.2548 0.3591 1.0000
6.000 1.7838 0.02397 0.01519 -0.2543 0.3568 1.0000
6.250 1.8091 0.02442 0.01562 -0.2538 0.3544 1.0000
6.500 1.8319 0.02482 0.01610 -0.2529 0.3520 1.0000
6.750 1.8545 0.02524 0.01659 -0.2519 0.3494 1.0000
7.000 1.8763 0.02566 0.01708 -0.2507 0.3465 1.0000
7.250 1.8978 0.02610 0.01756 -0.2495 0.3437 1.0000
7.500 1.9192 0.02656 0.01803 -0.2483 0.3410 1.0000
7.750 1.9420 0.02707 0.01850 -0.2474 0.3383 1.0000
8.000 1.9617 0.02757 0.01910 -0.2460 0.3354 1.0000
8.250 1.9798 0.02806 0.01972 -0.2442 0.3321 1.0000
8.500 1.9980 0.02858 0.02033 -0.2424 0.3287 1.0000
8.750 2.0163 0.02911 0.02093 -0.2408 0.3256 1.0000
9.000 2.0348 0.02967 0.02152 -0.2391 0.3227 1.0000
9.250 2.0542 0.03028 0.02213 -0.2377 0.3198 1.0000
9.500 2.0691 0.03091 0.02295 -0.2355 0.3163 1.0000
9.750 2.0837 0.03155 0.02373 -0.2332 0.3123 1.0000
10.000 2.0975 0.03223 0.02450 -0.2309 0.3082 1.0000
10.250 2.1117 0.03295 0.02523 -0.2286 0.3046 1.0000
10.500 2.1247 0.03374 0.02617 -0.2263 0.3005 1.0000
10.750 2.1370 0.03456 0.02715 -0.2238 0.2958 1.0000
11.000 2.1469 0.03545 0.02811 -0.2211 0.2906 1.0000
11.250 2.1566 0.03643 0.02917 -0.2184 0.2857 1.0000
11.500 2.1669 0.03743 0.03035 -0.2159 0.2798 1.0000
11.750 2.1749 0.03858 0.03158 -0.2131 0.2744 1.0000
12.000 2.1832 0.03979 0.03290 -0.2105 0.2692 1.0000
12.250 2.1911 0.04109 0.03435 -0.2080 0.2630 1.0000
12.500 2.1951 0.04265 0.03597 -0.2051 0.2571 1.0000
12.750 2.2015 0.04419 0.03767 -0.2027 0.2506 1.0000
13.000 2.2033 0.04609 0.03965 -0.1999 0.2439 1.0000
13.250 2.2055 0.04811 0.04178 -0.1974 0.2366 1.0000
13.500 2.2037 0.05057 0.04432 -0.1947 0.2291 1.0000
13.750 2.2028 0.05312 0.04699 -0.1924 0.2216 1.0000
14.000 2.1966 0.05632 0.05026 -0.1900 0.2141 1.0000
14.250 2.1912 0.05965 0.05371 -0.1881 0.2059 1.0000
14.500 2.1798 0.06386 0.05799 -0.1863 0.1984 1.0000
14.750 2.1685 0.06833 0.06258 -0.1849 0.1902 1.0000
15.000 2.1524 0.07369 0.06803 -0.1841 0.1835 1.0000
15.250 2.1359 0.07943 0.07390 -0.1837 0.1762 1.0000
15.500 2.1150 0.08606 0.08064 -0.1840 0.1701 1.0000
15.750 2.0959 0.09269 0.08740 -0.1847 0.1635 1.0000
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Polar data table (+)
Polar graphs
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