S4022 (s4022-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4022 (s4022-il) Reynolds number: 50,000 Max Cl/Cd: 39.11 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4022-il-50000-n5.txt Download as CSV file: xf-s4022-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4022
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3560 0.11339 0.10693 -0.0354 1.0000 0.1248
-8.250 -0.3816 0.11286 0.10659 -0.0353 1.0000 0.1276
-8.000 -0.4003 0.11158 0.10545 -0.0344 1.0000 0.1280
-7.500 -0.3970 0.10017 0.09404 -0.0341 1.0000 0.0693
-7.000 -0.4416 0.09237 0.08647 -0.0387 1.0000 0.0585
-6.750 -0.4407 0.09005 0.08421 -0.0357 1.0000 0.0576
-6.500 -0.4426 0.08725 0.08147 -0.0346 1.0000 0.0564
-6.250 -0.4338 0.08243 0.07664 -0.0391 0.9966 0.0546
-6.000 -0.4156 0.07553 0.06966 -0.0481 0.9900 0.0523
-5.750 -0.3932 0.06747 0.06134 -0.0591 0.9835 0.0498
-5.500 -0.3643 0.05793 0.05108 -0.0716 0.9768 0.0467
-5.250 -0.3267 0.05230 0.04465 -0.0793 0.9724 0.0455
-5.000 -0.2967 0.04811 0.04000 -0.0833 0.9674 0.0454
-4.750 -0.2604 0.04425 0.03555 -0.0877 0.9634 0.0454
-4.500 -0.2215 0.04105 0.03172 -0.0917 0.9601 0.0456
-4.250 -0.1909 0.03842 0.02880 -0.0939 0.9552 0.0473
-4.000 -0.1565 0.03677 0.02690 -0.0964 0.9507 0.0516
-3.750 -0.1188 0.03507 0.02477 -0.0987 0.9471 0.0547
-3.500 -0.0897 0.03365 0.02302 -0.0990 0.9412 0.0564
-3.250 -0.0563 0.03253 0.02157 -0.0998 0.9366 0.0584
-3.000 -0.0254 0.03145 0.02045 -0.1006 0.9318 0.0618
-2.750 0.0045 0.03066 0.01948 -0.1013 0.9257 0.0670
-2.500 0.0433 0.02981 0.01850 -0.1038 0.9215 0.0786
-2.250 0.0781 0.02878 0.01765 -0.1062 0.9156 0.1189
-2.000 0.1131 0.02694 0.01797 -0.1087 0.9116 0.5381
-1.750 0.1310 0.02735 0.01860 -0.1049 0.9050 0.6758
-1.500 0.1478 0.02752 0.01869 -0.1018 0.8969 0.7235
-1.250 0.1699 0.02759 0.01861 -0.1000 0.8901 0.7620
-1.000 0.1901 0.02758 0.01847 -0.0980 0.8824 0.7934
-0.750 0.2108 0.02753 0.01830 -0.0963 0.8750 0.8229
-0.500 0.2338 0.02741 0.01803 -0.0951 0.8678 0.8523
-0.250 0.2544 0.02732 0.01784 -0.0937 0.8597 0.8827
0.000 0.2854 0.02712 0.01753 -0.0944 0.8532 0.9210
0.250 0.3187 0.02706 0.01733 -0.0963 0.8439 1.0000
0.500 0.3625 0.02721 0.01725 -0.1001 0.8386 1.0000
0.750 0.3941 0.02757 0.01743 -0.1019 0.8297 1.0000
1.000 0.4364 0.02769 0.01736 -0.1051 0.8244 1.0000
1.250 0.4653 0.02809 0.01763 -0.1063 0.8149 1.0000
1.500 0.5070 0.02814 0.01755 -0.1090 0.8098 1.0000
1.750 0.5335 0.02858 0.01791 -0.1096 0.7996 1.0000
2.000 0.5720 0.02864 0.01789 -0.1117 0.7940 1.0000
2.250 0.5999 0.02900 0.01820 -0.1122 0.7843 1.0000
2.500 0.6289 0.02933 0.01851 -0.1128 0.7753 1.0000
2.750 0.6657 0.02934 0.01849 -0.1144 0.7688 1.0000
3.000 0.6909 0.02977 0.01891 -0.1144 0.7584 1.0000
3.250 0.7320 0.02956 0.01875 -0.1163 0.7532 1.0000
3.500 0.7550 0.03004 0.01926 -0.1159 0.7418 1.0000
3.750 0.7813 0.03039 0.01964 -0.1158 0.7315 1.0000
4.000 0.8216 0.03013 0.01945 -0.1175 0.7254 1.0000
4.250 0.8447 0.03055 0.01998 -0.1169 0.7136 1.0000
4.500 0.8706 0.03085 0.02037 -0.1167 0.7026 1.0000
4.750 0.9056 0.03073 0.02034 -0.1174 0.6939 1.0000
5.000 0.9377 0.03069 0.02042 -0.1178 0.6837 1.0000
5.250 0.9626 0.03094 0.02085 -0.1172 0.6713 1.0000
5.500 0.9893 0.03109 0.02113 -0.1168 0.6588 1.0000
5.750 1.0173 0.03114 0.02132 -0.1164 0.6460 1.0000
6.000 1.0461 0.03112 0.02145 -0.1161 0.6327 1.0000
6.250 1.0745 0.03107 0.02156 -0.1156 0.6184 1.0000
6.500 1.1029 0.03098 0.02170 -0.1151 0.6028 1.0000
6.750 1.1325 0.03078 0.02166 -0.1146 0.5859 1.0000
7.000 1.1585 0.03073 0.02175 -0.1135 0.5670 1.0000
7.250 1.1776 0.03097 0.02213 -0.1117 0.5459 1.0000
7.500 1.1997 0.03105 0.02232 -0.1100 0.5231 1.0000
7.750 1.2202 0.03120 0.02261 -0.1082 0.4978 1.0000
8.000 1.2340 0.03169 0.02318 -0.1056 0.4705 1.0000
8.250 1.2471 0.03226 0.02379 -0.1030 0.4412 1.0000
8.500 1.2564 0.03310 0.02466 -0.1001 0.4105 1.0000
8.750 1.2636 0.03412 0.02569 -0.0972 0.3784 1.0000
9.000 1.2692 0.03534 0.02686 -0.0942 0.3453 1.0000
9.250 1.2732 0.03680 0.02823 -0.0913 0.3128 1.0000
9.500 1.2750 0.03855 0.02992 -0.0886 0.2804 1.0000
9.750 1.2761 0.04052 0.03186 -0.0860 0.2507 1.0000
10.000 1.2766 0.04270 0.03395 -0.0836 0.2238 1.0000
10.250 1.2767 0.04507 0.03622 -0.0815 0.2009 1.0000
10.500 1.2782 0.04750 0.03866 -0.0797 0.1801 1.0000
10.750 1.2785 0.05011 0.04122 -0.0780 0.1624 1.0000
11.000 1.2794 0.05278 0.04385 -0.0765 0.1469 1.0000
11.250 1.2822 0.05545 0.04655 -0.0751 0.1331 1.0000
11.500 1.2836 0.05827 0.04941 -0.0740 0.1201 1.0000
11.750 1.2845 0.06122 0.05246 -0.0729 0.1080 1.0000
12.000 1.2856 0.06429 0.05566 -0.0720 0.0966 1.0000
12.250 1.2833 0.06772 0.05922 -0.0715 0.0858 1.0000
12.500 1.2801 0.07135 0.06295 -0.0712 0.0765 1.0000
12.750 1.2750 0.07517 0.06672 -0.0712 0.0690 1.0000
13.000 1.2732 0.07905 0.07090 -0.0712 0.0611 1.0000
13.250 1.2707 0.08298 0.07496 -0.0713 0.0555 1.0000
13.500 1.2705 0.08697 0.07924 -0.0714 0.0502 1.0000
13.750 1.2682 0.09093 0.08321 -0.0719 0.0466 1.0000
14.000 1.2663 0.09546 0.08805 -0.0724 0.0432 1.0000
14.250 1.2619 0.10036 0.09327 -0.0736 0.0406 1.0000
14.500 1.2568 0.10532 0.09845 -0.0751 0.0386 1.0000
14.750 1.2525 0.11018 0.10346 -0.0767 0.0371 1.0000
15.000 1.2494 0.11496 0.10836 -0.0783 0.0359 1.0000
15.250 1.2428 0.12070 0.11426 -0.0806 0.0352 1.0000
15.500 1.2302 0.12795 0.12180 -0.0845 0.0349 1.0000
15.750 1.2161 0.13588 0.12999 -0.0891 0.0348 1.0000
16.000 1.2006 0.14458 0.13891 -0.0946 0.0348 1.0000
16.250 1.1848 0.15402 0.14852 -0.1008 0.0350 1.0000
16.500 1.1690 0.16416 0.15879 -0.1075 0.0352 1.0000
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Polar data table (+)
Polar graphs
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