S1223 (s1223-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1223 (s1223-il) Reynolds number: 1,000,000 Max Cl/Cd: 120 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1223-il-1000000-n5.txt Download as CSV file: xf-s1223-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 0.2171 0.08935 0.08587 -0.1305 0.6425 0.0098
-8.250 0.2211 0.08676 0.08312 -0.1311 0.6075 0.0099
-8.000 0.2287 0.08476 0.08101 -0.1311 0.5785 0.0099
-7.750 0.2358 0.08273 0.07889 -0.1313 0.5578 0.0099
-7.500 0.2427 0.08069 0.07679 -0.1315 0.5408 0.0099
-7.250 0.2489 0.07865 0.07470 -0.1315 0.5275 0.0099
-7.000 0.2549 0.07668 0.07271 -0.1312 0.5166 0.0099
-6.750 0.2605 0.07482 0.07082 -0.1307 0.5062 0.0099
-5.750 0.3867 0.01674 0.01177 -0.2348 0.4926 0.0088
-5.500 0.4539 0.01482 0.00938 -0.2456 0.4791 0.0092
-5.250 0.5022 0.01397 0.00822 -0.2508 0.4670 0.0096
-5.000 0.5450 0.01341 0.00744 -0.2544 0.4566 0.0098
-4.750 0.5837 0.01307 0.00691 -0.2570 0.4472 0.0099
-4.500 0.6249 0.01263 0.00634 -0.2601 0.4397 0.0103
-4.250 0.6595 0.01249 0.00609 -0.2615 0.4319 0.0106
-4.000 0.6931 0.01237 0.00589 -0.2627 0.4258 0.0109
-3.750 0.7271 0.01224 0.00568 -0.2639 0.4195 0.0113
-3.500 0.7611 0.01214 0.00547 -0.2651 0.4128 0.0118
-3.250 0.7940 0.01207 0.00531 -0.2661 0.4077 0.0124
-3.000 0.8275 0.01197 0.00514 -0.2672 0.4025 0.0130
-2.750 0.8593 0.01195 0.00507 -0.2679 0.3968 0.0136
-2.500 0.8911 0.01195 0.00500 -0.2686 0.3910 0.0142
-2.250 0.9234 0.01190 0.00489 -0.2694 0.3866 0.0150
-2.000 0.9549 0.01190 0.00482 -0.2700 0.3820 0.0156
-1.750 0.9880 0.01186 0.00473 -0.2710 0.3774 0.0164
-1.500 1.0189 0.01189 0.00471 -0.2715 0.3729 0.0173
-1.250 1.0493 0.01191 0.00469 -0.2719 0.3702 0.0185
-1.000 1.0805 0.01191 0.00466 -0.2724 0.3670 0.0195
-0.750 1.1112 0.01194 0.00465 -0.2729 0.3633 0.0206
-0.500 1.1409 0.01201 0.00467 -0.2731 0.3593 0.0218
0.000 1.2001 0.01215 0.00475 -0.2735 0.3532 0.0260
0.250 1.2301 0.01219 0.00481 -0.2737 0.3510 0.0342
0.500 1.2637 0.01217 0.00490 -0.2749 0.3484 0.0967
0.750 1.2971 0.01217 0.00506 -0.2761 0.3454 0.1844
1.000 1.3255 0.01229 0.00520 -0.2761 0.3425 0.2112
1.250 1.3534 0.01243 0.00535 -0.2760 0.3397 0.2312
1.500 1.3808 0.01257 0.00549 -0.2757 0.3373 0.2423
1.750 1.4082 0.01268 0.00561 -0.2755 0.3361 0.2549
2.000 1.4357 0.01280 0.00576 -0.2752 0.3347 0.2681
2.250 1.4625 0.01294 0.00589 -0.2748 0.3329 0.2754
2.500 1.4895 0.01308 0.00605 -0.2745 0.3310 0.2855
2.750 1.5159 0.01323 0.00621 -0.2741 0.3289 0.2951
3.000 1.5425 0.01340 0.00639 -0.2737 0.3268 0.3075
3.250 1.5687 0.01358 0.00658 -0.2733 0.3248 0.3209
3.500 1.5949 0.01376 0.00678 -0.2728 0.3228 0.3373
3.750 1.6208 0.01397 0.00701 -0.2723 0.3206 0.3543
4.000 1.6470 0.01413 0.00721 -0.2719 0.3196 0.3724
4.250 1.6734 0.01428 0.00741 -0.2715 0.3184 0.3921
4.500 1.6996 0.01444 0.00762 -0.2711 0.3169 0.4137
4.750 1.7258 0.01461 0.00785 -0.2706 0.3152 0.4379
5.000 1.7517 0.01480 0.00808 -0.2702 0.3132 0.4647
5.250 1.7776 0.01500 0.00834 -0.2698 0.3107 0.4960
5.500 1.8035 0.01523 0.00861 -0.2694 0.3080 0.5356
5.750 1.8290 0.01549 0.00893 -0.2689 0.3048 0.5757
6.000 1.8549 0.01570 0.00921 -0.2685 0.3024 0.6192
6.250 1.8815 0.01587 0.00949 -0.2682 0.3002 0.6717
6.500 1.9083 0.01607 0.00981 -0.2680 0.2978 0.7400
6.750 1.9284 0.01607 0.01008 -0.2663 0.2956 0.9917
7.250 1.9746 0.01667 0.01067 -0.2644 0.2893 1.0000
7.500 1.9973 0.01697 0.01099 -0.2634 0.2859 1.0000
7.750 2.0203 0.01725 0.01128 -0.2624 0.2825 1.0000
8.000 2.0427 0.01756 0.01160 -0.2614 0.2785 1.0000
8.250 2.0640 0.01797 0.01198 -0.2602 0.2728 1.0000
8.500 2.0859 0.01832 0.01233 -0.2591 0.2667 1.0000
8.750 2.1062 0.01881 0.01278 -0.2577 0.2576 1.0000
9.000 2.1271 0.01923 0.01320 -0.2564 0.2510 1.0000
9.250 2.1463 0.01977 0.01371 -0.2549 0.2434 1.0000
9.500 2.1659 0.02026 0.01420 -0.2534 0.2373 1.0000
9.750 2.1841 0.02086 0.01478 -0.2517 0.2296 1.0000
10.000 2.2023 0.02145 0.01537 -0.2500 0.2224 1.0000
10.250 2.2185 0.02221 0.01609 -0.2480 0.2130 1.0000
10.500 2.2334 0.02305 0.01689 -0.2458 0.2015 1.0000
10.750 2.2462 0.02406 0.01785 -0.2434 0.1887 1.0000
11.000 2.2598 0.02498 0.01875 -0.2410 0.1797 1.0000
11.250 2.2706 0.02612 0.01985 -0.2383 0.1691 1.0000
11.500 2.2814 0.02725 0.02097 -0.2356 0.1598 1.0000
11.750 2.2920 0.02838 0.02209 -0.2330 0.1517 1.0000
12.000 2.3007 0.02969 0.02339 -0.2301 0.1438 1.0000
12.250 2.3093 0.03099 0.02469 -0.2273 0.1362 1.0000
12.500 2.3160 0.03246 0.02617 -0.2243 0.1290 1.0000
12.750 2.3212 0.03407 0.02779 -0.2213 0.1217 1.0000
13.000 2.3268 0.03568 0.02942 -0.2184 0.1155 1.0000
13.250 2.3294 0.03761 0.03136 -0.2153 0.1090 1.0000
13.500 2.3343 0.03937 0.03317 -0.2126 0.1043 1.0000
13.750 2.3353 0.04156 0.03539 -0.2097 0.0987 1.0000
14.000 2.3371 0.04374 0.03762 -0.2070 0.0946 1.0000
14.250 2.3378 0.04611 0.04003 -0.2045 0.0905 1.0000
14.500 2.3344 0.04901 0.04298 -0.2019 0.0864 1.0000
14.750 2.3336 0.05175 0.04580 -0.1997 0.0832 1.0000
15.000 2.3287 0.05510 0.04921 -0.1976 0.0796 1.0000
15.250 2.3188 0.05923 0.05342 -0.1957 0.0751 1.0000
15.500 2.3082 0.06370 0.05797 -0.1941 0.0710 1.0000
15.750 2.2984 0.06830 0.06266 -0.1931 0.0689 1.0000
16.000 2.2864 0.07347 0.06794 -0.1925 0.0669 1.0000
16.250 2.2719 0.07925 0.07384 -0.1923 0.0642 1.0000
16.500 2.2570 0.08529 0.08001 -0.1925 0.0628 1.0000
16.750 2.2372 0.09231 0.08716 -0.1933 0.0611 1.0000
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Polar data table (+)
Polar graphs
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