S1223 (s1223-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1223 (s1223-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.38 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1223-il-1000000.txt Download as CSV file: xf-s1223-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 0.1302 0.09491 0.09315 -0.1002 0.9451 0.0111
-7.750 0.1438 0.09210 0.09034 -0.1022 0.9414 0.0115
-7.500 0.1477 0.08930 0.08755 -0.1025 0.9339 0.0125
-7.250 0.1547 0.08588 0.08413 -0.1053 0.9280 0.0126
-6.750 0.1784 0.08025 0.07848 -0.1085 0.9065 0.0127
-6.500 0.2218 0.07527 0.07343 -0.1173 0.8916 0.0129
-6.250 0.3142 0.06875 0.06644 -0.1393 0.8206 0.0133
-6.000 0.3098 0.06818 0.06542 -0.1357 0.7309 0.0134
-5.750 0.3021 0.06766 0.06458 -0.1314 0.6598 0.0136
-5.500 0.3003 0.06669 0.06343 -0.1289 0.6172 0.0138
-5.250 0.2976 0.06552 0.06216 -0.1263 0.5889 0.0139
-5.000 0.2945 0.06443 0.06099 -0.1237 0.5651 0.0142
-4.750 0.2976 0.06264 0.05914 -0.1228 0.5474 0.0146
-4.500 0.3027 0.06059 0.05706 -0.1225 0.5335 0.0148
-4.250 0.3087 0.05827 0.05472 -0.1230 0.5221 0.0151
-4.000 0.3200 0.05435 0.05077 -0.1271 0.5126 0.0155
-3.750 0.3372 0.05082 0.04721 -0.1312 0.5036 0.0156
-3.500 0.3597 0.04733 0.04368 -0.1362 0.4939 0.0156
-3.250 0.3917 0.04220 0.03850 -0.1455 0.4854 0.0159
-3.000 0.4257 0.03943 0.03567 -0.1519 0.4762 0.0161
-2.750 0.4777 0.03536 0.03149 -0.1636 0.4665 0.0165
-2.500 0.8683 0.01239 0.00596 -0.2633 0.4429 0.0170
-2.250 0.9015 0.01231 0.00578 -0.2643 0.4348 0.0182
-2.000 0.9399 0.01206 0.00540 -0.2665 0.4273 0.0194
-1.750 0.9755 0.01191 0.00521 -0.2681 0.4212 0.0206
-1.500 1.0088 0.01188 0.00510 -0.2692 0.4146 0.0218
-1.250 1.0443 0.01180 0.00493 -0.2707 0.4086 0.0232
-1.000 1.0771 0.01176 0.00487 -0.2716 0.4039 0.0252
-0.750 1.1089 0.01178 0.00482 -0.2723 0.3985 0.0268
-0.500 1.1410 0.01184 0.00479 -0.2731 0.3923 0.0289
-0.250 1.1720 0.01185 0.00479 -0.2735 0.3890 0.0316
0.000 1.2030 0.01188 0.00481 -0.2740 0.3854 0.0384
0.250 1.2438 0.01171 0.00495 -0.2770 0.3813 0.1927
0.500 1.2720 0.01186 0.00509 -0.2769 0.3771 0.2184
1.000 1.3277 0.01212 0.00536 -0.2765 0.3708 0.2532
1.250 1.3557 0.01223 0.00549 -0.2764 0.3684 0.2701
1.500 1.3832 0.01236 0.00562 -0.2762 0.3658 0.2819
1.750 1.4104 0.01251 0.00576 -0.2759 0.3631 0.2952
2.000 1.4378 0.01267 0.00594 -0.2756 0.3603 0.3114
2.250 1.4647 0.01289 0.00614 -0.2753 0.3568 0.3258
2.500 1.4918 0.01306 0.00632 -0.2750 0.3545 0.3430
2.750 1.5193 0.01317 0.00649 -0.2748 0.3529 0.3631
3.000 1.5466 0.01330 0.00666 -0.2746 0.3512 0.3864
3.500 1.6009 0.01361 0.00706 -0.2741 0.3474 0.4445
3.750 1.6278 0.01379 0.00730 -0.2738 0.3453 0.4781
4.000 1.6544 0.01399 0.00755 -0.2735 0.3431 0.5149
4.250 1.6808 0.01425 0.00784 -0.2731 0.3401 0.5571
4.500 1.7073 0.01453 0.00818 -0.2728 0.3374 0.6064
4.750 1.7353 0.01465 0.00844 -0.2728 0.3363 0.6683
5.000 1.7636 0.01477 0.00871 -0.2728 0.3347 0.7527
5.250 1.7831 0.01469 0.00890 -0.2709 0.3328 1.0000
5.500 1.8080 0.01490 0.00911 -0.2703 0.3307 1.0000
5.750 1.8325 0.01513 0.00934 -0.2695 0.3283 1.0000
6.000 1.8564 0.01541 0.00959 -0.2687 0.3254 1.0000
6.250 1.8795 0.01578 0.00993 -0.2677 0.3219 1.0000
6.500 1.9033 0.01607 0.01023 -0.2668 0.3197 1.0000
6.750 1.9278 0.01626 0.01046 -0.2661 0.3184 1.0000
7.000 1.9519 0.01647 0.01070 -0.2654 0.3167 1.0000
7.250 1.9757 0.01669 0.01095 -0.2645 0.3143 1.0000
7.500 1.9988 0.01695 0.01122 -0.2636 0.3114 1.0000
7.750 2.0210 0.01727 0.01153 -0.2624 0.3083 1.0000
8.000 2.0420 0.01770 0.01194 -0.2611 0.3047 1.0000
8.250 2.0648 0.01797 0.01225 -0.2601 0.3021 1.0000
8.500 2.0883 0.01815 0.01248 -0.2593 0.2989 1.0000
8.750 2.1108 0.01843 0.01277 -0.2583 0.2947 1.0000
9.000 2.1319 0.01880 0.01314 -0.2571 0.2908 1.0000
9.250 2.1521 0.01925 0.01359 -0.2557 0.2869 1.0000
9.500 2.1743 0.01952 0.01392 -0.2546 0.2844 1.0000
9.750 2.1956 0.01985 0.01429 -0.2535 0.2809 1.0000
10.000 2.2157 0.02026 0.01472 -0.2521 0.2767 1.0000
10.250 2.2343 0.02080 0.01525 -0.2505 0.2718 1.0000
10.500 2.2555 0.02114 0.01565 -0.2493 0.2675 1.0000
10.750 2.2741 0.02165 0.01616 -0.2478 0.2613 1.0000
11.000 2.2915 0.02225 0.01676 -0.2460 0.2555 1.0000
11.250 2.3097 0.02279 0.01733 -0.2444 0.2489 1.0000
11.500 2.3251 0.02354 0.01806 -0.2424 0.2411 1.0000
11.750 2.3408 0.02426 0.01879 -0.2404 0.2329 1.0000
12.000 2.3544 0.02515 0.01967 -0.2381 0.2239 1.0000
12.250 2.3653 0.02625 0.02074 -0.2355 0.2131 1.0000
12.500 2.3751 0.02745 0.02190 -0.2328 0.2008 1.0000
12.750 2.3832 0.02877 0.02319 -0.2298 0.1892 1.0000
13.000 2.3902 0.03021 0.02461 -0.2268 0.1785 1.0000
13.250 2.3946 0.03185 0.02623 -0.2235 0.1684 1.0000
13.500 2.3974 0.03366 0.02803 -0.2202 0.1588 1.0000
13.750 2.4021 0.03535 0.02974 -0.2172 0.1504 1.0000
14.000 2.4033 0.03739 0.03178 -0.2140 0.1423 1.0000
14.250 2.4030 0.03963 0.03404 -0.2108 0.1345 1.0000
14.500 2.4036 0.04186 0.03630 -0.2079 0.1280 1.0000
14.750 2.3985 0.04474 0.03919 -0.2047 0.1206 1.0000
15.000 2.3954 0.04753 0.04202 -0.2020 0.1136 1.0000
15.250 2.3861 0.05116 0.04568 -0.1992 0.1064 1.0000
15.500 2.3777 0.05487 0.04944 -0.1968 0.1005 1.0000
15.750 2.3681 0.05893 0.05356 -0.1948 0.0961 1.0000
16.000 2.3598 0.06302 0.05775 -0.1933 0.0925 1.0000
16.250 2.3438 0.06842 0.06323 -0.1921 0.0883 1.0000
16.500 2.3291 0.07393 0.06885 -0.1915 0.0852 1.0000
16.750 2.3126 0.07996 0.07499 -0.1913 0.0821 1.0000
17.000 2.2895 0.08728 0.08244 -0.1917 0.0791 1.0000
17.250 2.2657 0.09493 0.09023 -0.1926 0.0770 1.0000
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Polar data table (+)
Polar graphs
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