S1223 (s1223-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1223 (s1223-il) Reynolds number: 100,000 Max Cl/Cd: 54.48 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1223-il-100000.txt Download as CSV file: xf-s1223-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-5.500 -0.0105 0.10503 0.10101 -0.0547 0.9320 0.0686
-5.250 0.0047 0.10263 0.09863 -0.0592 0.9191 0.0714
-5.000 0.0103 0.10225 0.09828 -0.0688 0.9014 0.0727
-4.750 0.0386 0.09558 0.09163 -0.0648 0.8932 0.0746
-4.500 0.0702 0.09134 0.08739 -0.0687 0.8858 0.0781
-4.250 0.0884 0.08839 0.08445 -0.0731 0.8701 0.0821
-4.000 0.1103 0.08464 0.08072 -0.0818 0.8534 0.0847
-3.750 0.1289 0.08072 0.07681 -0.0783 0.8397 0.0874
-3.500 0.1542 0.07715 0.07323 -0.0813 0.8248 0.0922
-3.250 0.1897 0.07260 0.06865 -0.0923 0.8082 0.0983
-3.000 0.2240 0.06862 0.06461 -0.0931 0.7962 0.1062
-2.750 0.2714 0.06377 0.05965 -0.1031 0.7789 0.1151
-2.500 0.3355 0.05889 0.05459 -0.1188 0.7554 0.1284
-2.250 0.4065 0.05411 0.04954 -0.1332 0.7308 0.1442
-2.000 0.4772 0.04983 0.04493 -0.1458 0.7064 0.1612
-1.750 0.8569 0.02451 0.01681 -0.2451 0.6665 0.0825
-1.500 0.9316 0.02289 0.01425 -0.2551 0.6427 0.0838
-1.250 0.9834 0.02207 0.01313 -0.2602 0.6248 0.0909
-1.000 1.0275 0.02169 0.01241 -0.2632 0.6098 0.0976
-0.750 1.0711 0.02145 0.01216 -0.2664 0.5966 0.1168
-0.500 1.1236 0.02167 0.01264 -0.2712 0.5853 0.2859
-0.250 1.1483 0.02246 0.01342 -0.2701 0.5751 0.3449
0.000 1.1729 0.02337 0.01430 -0.2688 0.5671 0.4004
0.250 1.1995 0.02372 0.01464 -0.2684 0.5583 0.4252
0.500 1.2338 0.02405 0.01477 -0.2696 0.5509 0.4444
0.750 1.2672 0.02443 0.01503 -0.2707 0.5445 0.4607
1.000 1.2977 0.02476 0.01533 -0.2713 0.5378 0.4771
1.250 1.3313 0.02513 0.01556 -0.2724 0.5317 0.4949
1.500 1.3650 0.02561 0.01592 -0.2736 0.5263 0.5155
1.750 1.3918 0.02601 0.01641 -0.2734 0.5204 0.5383
2.000 1.4219 0.02644 0.01685 -0.2739 0.5153 0.5662
2.250 1.4531 0.02690 0.01726 -0.2745 0.5109 0.6019
2.500 1.4823 0.02744 0.01782 -0.2746 0.5068 0.6465
2.750 1.5037 0.02784 0.01847 -0.2732 0.5020 0.7026
3.000 1.5223 0.02811 0.01899 -0.2711 0.4976 0.7898
3.250 1.5379 0.02823 0.01917 -0.2686 0.4939 1.0000
3.500 1.5728 0.02903 0.01973 -0.2703 0.4902 1.0000
3.750 1.6028 0.02996 0.02055 -0.2709 0.4867 1.0000
4.000 1.6248 0.03079 0.02150 -0.2700 0.4825 1.0000
4.250 1.6490 0.03161 0.02235 -0.2694 0.4781 1.0000
4.500 1.6752 0.03240 0.02311 -0.2692 0.4743 1.0000
4.750 1.7032 0.03323 0.02387 -0.2693 0.4711 1.0000
5.000 1.7335 0.03427 0.02481 -0.2700 0.4681 1.0000
5.250 1.7484 0.03535 0.02614 -0.2678 0.4642 1.0000
5.500 1.7673 0.03642 0.02733 -0.2663 0.4601 1.0000
5.750 1.7899 0.03739 0.02836 -0.2655 0.4564 1.0000
6.000 1.8152 0.03826 0.02925 -0.2652 0.4529 1.0000
6.250 1.8443 0.03914 0.03005 -0.2655 0.4496 1.0000
6.500 1.8582 0.04061 0.03172 -0.2633 0.4459 1.0000
6.750 1.8685 0.04213 0.03348 -0.2605 0.4416 1.0000
7.000 1.8860 0.04332 0.03480 -0.2589 0.4375 1.0000
7.250 1.9110 0.04411 0.03559 -0.2585 0.4337 1.0000
7.500 1.9414 0.04485 0.03626 -0.2590 0.4304 1.0000
7.750 1.9463 0.04684 0.03852 -0.2555 0.4263 1.0000
8.000 1.9457 0.04896 0.04095 -0.2511 0.4215 1.0000
8.250 1.9623 0.05011 0.04219 -0.2494 0.4171 1.0000
8.500 1.9937 0.05041 0.04244 -0.2499 0.4132 1.0000
8.750 2.0220 0.05130 0.04331 -0.2501 0.4095 1.0000
9.000 1.9896 0.05513 0.04764 -0.2412 0.4042 1.0000
9.250 1.9883 0.05721 0.04993 -0.2370 0.3993 1.0000
9.500 2.0272 0.05688 0.04954 -0.2384 0.3952 1.0000
9.750 2.0814 0.05612 0.04859 -0.2422 0.3914 1.0000
10.000 1.9821 0.06371 0.05687 -0.2247 0.3865 1.0000
10.500 1.9679 0.06835 0.06181 -0.2157 0.3771 1.0000
10.750 2.0778 0.06333 0.05652 -0.2255 0.3721 1.0000
11.500 1.8149 0.09405 0.08820 -0.1970 0.3552 1.0000
11.750 1.4189 0.16839 0.16288 -0.2248 0.3114 1.0000
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Polar data table (+)
Polar graphs
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