S1223 (s1223-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1223 (s1223-il) Reynolds number: 500,000 Max Cl/Cd: 98.85 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1223-il-500000.txt Download as CSV file: xf-s1223-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 0.1102 0.09424 0.09192 -0.0898 0.9418 0.0171
-7.000 0.1307 0.09089 0.08857 -0.0936 0.9397 0.0176
-6.750 0.1353 0.08865 0.08636 -0.0931 0.9307 0.0179
-6.500 0.2154 0.06577 0.06359 -0.0983 0.8856 0.0193
-6.250 0.2372 0.06215 0.05994 -0.1016 0.8715 0.0196
-6.000 0.1502 0.08059 0.07832 -0.0979 0.9033 0.0189
-5.750 0.1624 0.07791 0.07565 -0.0969 0.8924 0.0191
-5.500 0.1830 0.07507 0.07280 -0.0988 0.8812 0.0193
-5.250 0.2136 0.07167 0.06935 -0.1039 0.8662 0.0197
-5.000 0.2652 0.06686 0.06438 -0.1153 0.8393 0.0203
-4.750 0.3237 0.06171 0.05885 -0.1292 0.7801 0.0214
-4.500 0.3306 0.05955 0.05633 -0.1301 0.7119 0.0220
-4.250 0.3303 0.05680 0.05335 -0.1316 0.6643 0.0224
-3.750 0.3379 0.05285 0.04910 -0.1305 0.5962 0.0228
-3.500 0.3471 0.05148 0.04761 -0.1299 0.5719 0.0230
-3.250 0.3608 0.04986 0.04590 -0.1305 0.5533 0.0234
-3.000 0.4487 0.03815 0.03399 -0.1613 0.5391 0.0265
-2.750 0.4581 0.03829 0.03407 -0.1581 0.5251 0.0268
-2.500 0.4860 0.03691 0.03260 -0.1608 0.5121 0.0274
-2.250 0.8394 0.01585 0.00887 -0.2507 0.4852 0.0263
-2.000 0.8859 0.01498 0.00774 -0.2547 0.4750 0.0262
-1.750 0.9290 0.01439 0.00699 -0.2580 0.4658 0.0272
-1.500 0.9657 0.01417 0.00670 -0.2598 0.4575 0.0288
-1.250 0.9988 0.01418 0.00656 -0.2608 0.4496 0.0307
-1.000 1.0374 0.01397 0.00635 -0.2631 0.4433 0.0336
-0.750 1.0715 0.01396 0.00625 -0.2642 0.4369 0.0356
-0.500 1.1069 0.01398 0.00619 -0.2658 0.4308 0.0393
-0.250 1.1406 0.01398 0.00616 -0.2669 0.4259 0.0453
0.000 1.1850 0.01374 0.00623 -0.2706 0.4204 0.1905
0.250 1.2132 0.01392 0.00640 -0.2705 0.4156 0.2364
0.500 1.2409 0.01419 0.00659 -0.2703 0.4106 0.2569
1.000 1.2962 0.01448 0.00691 -0.2699 0.4041 0.2953
1.250 1.3244 0.01464 0.00709 -0.2698 0.4005 0.3115
1.500 1.3524 0.01484 0.00726 -0.2697 0.3969 0.3253
1.750 1.3804 0.01511 0.00747 -0.2696 0.3929 0.3384
2.000 1.4089 0.01530 0.00767 -0.2696 0.3901 0.3532
2.250 1.4373 0.01544 0.00786 -0.2696 0.3877 0.3712
2.500 1.4655 0.01561 0.00807 -0.2695 0.3851 0.3931
2.750 1.4939 0.01579 0.00830 -0.2696 0.3824 0.4201
3.000 1.5218 0.01599 0.00855 -0.2695 0.3797 0.4536
3.250 1.5500 0.01624 0.00883 -0.2695 0.3768 0.4925
3.500 1.5799 0.01659 0.00921 -0.2699 0.3734 0.5385
3.750 1.6082 0.01676 0.00951 -0.2699 0.3716 0.5921
4.250 1.6651 0.01710 0.01017 -0.2700 0.3675 0.7489
4.500 1.6794 0.01699 0.01030 -0.2669 0.3655 1.0000
4.750 1.7050 0.01726 0.01054 -0.2664 0.3632 1.0000
5.000 1.7303 0.01755 0.01081 -0.2658 0.3609 1.0000
5.250 1.7560 0.01790 0.01111 -0.2654 0.3584 1.0000
5.500 1.7849 0.01837 0.01151 -0.2656 0.3552 1.0000
5.750 1.8082 0.01859 0.01180 -0.2646 0.3535 1.0000
6.000 1.8316 0.01885 0.01209 -0.2637 0.3514 1.0000
6.250 1.8547 0.01912 0.01239 -0.2627 0.3488 1.0000
6.500 1.8777 0.01941 0.01269 -0.2617 0.3463 1.0000
6.750 1.9003 0.01972 0.01302 -0.2606 0.3436 1.0000
7.000 1.9234 0.02011 0.01337 -0.2597 0.3406 1.0000
7.250 1.9495 0.02059 0.01382 -0.2594 0.3373 1.0000
7.500 1.9706 0.02087 0.01418 -0.2581 0.3355 1.0000
7.750 1.9920 0.02118 0.01457 -0.2568 0.3332 1.0000
8.000 2.0132 0.02151 0.01495 -0.2555 0.3305 1.0000
8.250 2.0331 0.02185 0.01532 -0.2540 0.3273 1.0000
8.500 2.0533 0.02227 0.01575 -0.2525 0.3243 1.0000
8.750 2.0760 0.02284 0.01627 -0.2517 0.3202 1.0000
9.000 2.0941 0.02317 0.01672 -0.2498 0.3179 1.0000
9.250 2.1121 0.02352 0.01717 -0.2480 0.3144 1.0000
9.500 2.1296 0.02392 0.01762 -0.2461 0.3104 1.0000
9.750 2.1463 0.02444 0.01814 -0.2441 0.3064 1.0000
10.000 2.1645 0.02503 0.01875 -0.2425 0.3026 1.0000
10.250 2.1826 0.02543 0.01928 -0.2408 0.2994 1.0000
10.500 2.2002 0.02590 0.01984 -0.2390 0.2957 1.0000
10.750 2.2165 0.02647 0.02044 -0.2371 0.2916 1.0000
11.000 2.2310 0.02722 0.02120 -0.2349 0.2876 1.0000
11.250 2.2486 0.02773 0.02183 -0.2333 0.2837 1.0000
11.500 2.2650 0.02831 0.02250 -0.2315 0.2789 1.0000
11.750 2.2779 0.02912 0.02334 -0.2291 0.2738 1.0000
12.000 2.2927 0.02986 0.02416 -0.2272 0.2688 1.0000
12.250 2.3063 0.03066 0.02503 -0.2251 0.2619 1.0000
12.500 2.3169 0.03171 0.02610 -0.2226 0.2556 1.0000
12.750 2.3293 0.03266 0.02714 -0.2205 0.2482 1.0000
13.000 2.3370 0.03399 0.02847 -0.2177 0.2405 1.0000
13.250 2.3453 0.03532 0.02986 -0.2152 0.2316 1.0000
13.500 2.3509 0.03692 0.03149 -0.2125 0.2225 1.0000
13.750 2.3523 0.03894 0.03352 -0.2094 0.2123 1.0000
14.000 2.3534 0.04107 0.03567 -0.2065 0.2015 1.0000
14.250 2.3524 0.04349 0.03812 -0.2036 0.1914 1.0000
14.500 2.3470 0.04644 0.04109 -0.2005 0.1816 1.0000
14.750 2.3388 0.04985 0.04453 -0.1976 0.1727 1.0000
15.000 2.3327 0.05321 0.04796 -0.1952 0.1644 1.0000
15.250 2.3201 0.05751 0.05231 -0.1929 0.1569 1.0000
15.500 2.3096 0.06179 0.05668 -0.1911 0.1498 1.0000
15.750 2.2926 0.06719 0.06216 -0.1897 0.1437 1.0000
16.000 2.2771 0.07270 0.06778 -0.1889 0.1374 1.0000
16.250 2.2516 0.08003 0.07520 -0.1888 0.1321 1.0000
16.500 2.2347 0.08627 0.08158 -0.1890 0.1270 1.0000
16.750 2.2066 0.09454 0.08997 -0.1900 0.1222 1.0000
17.000 2.1825 0.10230 0.09785 -0.1913 0.1183 1.0000
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Polar data table (+)
Polar graphs
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