YS-930 (ys930-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: YS-930 (ys930-il) Reynolds number: 100,000 Max Cl/Cd: 47.09 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ys930-il-100000-n5.txt Download as CSV file: xf-ys930-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: YS-930
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4627 0.09498 0.09040 -0.0437 1.0000 0.0165
-9.250 -0.4768 0.09173 0.08724 -0.0424 1.0000 0.0164
-9.000 -0.4904 0.08900 0.08461 -0.0409 1.0000 0.0162
-8.750 -0.4953 0.08376 0.07941 -0.0439 0.9973 0.0161
-8.500 -0.4967 0.07706 0.07273 -0.0497 0.9922 0.0158
-8.250 -0.5029 0.06965 0.06534 -0.0570 0.9851 0.0155
-8.000 -0.5085 0.06060 0.05616 -0.0681 0.9765 0.0152
-7.750 -0.5085 0.05318 0.04838 -0.0760 0.9700 0.0150
-7.500 -0.5101 0.04832 0.04314 -0.0778 0.9634 0.0149
-7.250 -0.5008 0.04338 0.03768 -0.0802 0.9590 0.0149
-7.000 -0.4886 0.03933 0.03308 -0.0809 0.9550 0.0150
-6.750 -0.4762 0.03602 0.02924 -0.0802 0.9510 0.0152
-6.500 -0.4571 0.03319 0.02591 -0.0800 0.9483 0.0155
-6.250 -0.4346 0.03068 0.02293 -0.0799 0.9464 0.0161
-6.000 -0.4093 0.02865 0.02051 -0.0800 0.9448 0.0170
-5.750 -0.3922 0.02672 0.01830 -0.0789 0.9418 0.0203
-5.500 -0.3723 0.02558 0.01700 -0.0780 0.9389 0.0237
-5.250 -0.3499 0.02427 0.01544 -0.0771 0.9367 0.0270
-5.000 -0.3262 0.02298 0.01396 -0.0769 0.9348 0.0340
-4.750 -0.2994 0.02188 0.01265 -0.0771 0.9332 0.0446
-4.500 -0.2718 0.02052 0.01132 -0.0775 0.9318 0.0777
-4.250 -0.2502 0.01990 0.01119 -0.0771 0.9294 0.1997
-4.000 -0.2290 0.02003 0.01122 -0.0762 0.9266 0.2402
-3.750 -0.2049 0.02018 0.01128 -0.0758 0.9239 0.2735
-3.500 -0.1779 0.02009 0.01096 -0.0759 0.9220 0.2875
-3.250 -0.1498 0.01995 0.01069 -0.0762 0.9204 0.2975
-3.000 -0.1201 0.01981 0.01041 -0.0768 0.9189 0.3072
-2.750 -0.0949 0.01973 0.01024 -0.0765 0.9167 0.3167
-2.500 -0.0750 0.01969 0.01017 -0.0753 0.9136 0.3257
-2.250 -0.0502 0.01962 0.01006 -0.0749 0.9110 0.3364
-2.000 -0.0232 0.01956 0.00992 -0.0751 0.9088 0.3497
-1.750 0.0055 0.01949 0.00986 -0.0755 0.9070 0.3670
-1.500 0.0359 0.01942 0.00982 -0.0763 0.9055 0.3887
-1.250 0.0574 0.01943 0.00990 -0.0754 0.9023 0.4129
-1.000 0.0790 0.01942 0.01000 -0.0744 0.8988 0.4451
-0.750 0.1055 0.01935 0.01006 -0.0744 0.8962 0.4937
-0.500 0.1337 0.01920 0.01017 -0.0747 0.8941 0.5647
-0.250 0.1621 0.01895 0.01032 -0.0747 0.8924 0.6699
0.000 0.2155 0.01852 0.01053 -0.0796 0.8923 0.9486
0.250 0.2357 0.01879 0.01072 -0.0785 0.8879 1.0000
0.500 0.2592 0.01901 0.01087 -0.0780 0.8838 1.0000
0.750 0.2891 0.01919 0.01099 -0.0787 0.8810 1.0000
1.000 0.3223 0.01935 0.01112 -0.0799 0.8788 1.0000
1.250 0.3378 0.01967 0.01142 -0.0779 0.8726 1.0000
1.500 0.3659 0.01986 0.01165 -0.0782 0.8688 1.0000
1.750 0.3995 0.01999 0.01180 -0.0794 0.8662 1.0000
2.000 0.4183 0.02029 0.01213 -0.0780 0.8598 1.0000
2.250 0.4474 0.02044 0.01234 -0.0783 0.8553 1.0000
2.500 0.4834 0.02049 0.01247 -0.0799 0.8525 1.0000
2.750 0.5003 0.02079 0.01291 -0.0780 0.8443 1.0000
3.000 0.5355 0.02079 0.01304 -0.0793 0.8404 1.0000
3.250 0.5575 0.02098 0.01335 -0.0782 0.8325 1.0000
3.500 0.5940 0.02082 0.01338 -0.0795 0.8273 1.0000
3.750 0.6187 0.02082 0.01355 -0.0787 0.8179 1.0000
4.000 0.6698 0.01999 0.01310 -0.0818 0.8121 1.0000
4.250 0.6928 0.01941 0.01273 -0.0796 0.7933 1.0000
4.500 0.7242 0.01719 0.01067 -0.0766 0.7446 1.0000
4.750 0.7633 0.01621 0.00803 -0.0743 0.3911 1.0000
5.000 0.7559 0.01888 0.00902 -0.0688 0.1262 1.0000
5.250 0.7660 0.02068 0.01022 -0.0658 0.0469 1.0000
5.500 0.7807 0.02184 0.01137 -0.0634 0.0321 1.0000
5.750 0.7933 0.02317 0.01282 -0.0606 0.0274 1.0000
6.000 0.8078 0.02447 0.01428 -0.0580 0.0244 1.0000
6.250 0.8248 0.02579 0.01563 -0.0563 0.0202 1.0000
6.500 0.8486 0.02780 0.01784 -0.0557 0.0171 1.0000
6.750 0.8820 0.03010 0.02034 -0.0563 0.0159 1.0000
7.000 0.9171 0.03291 0.02346 -0.0569 0.0149 1.0000
7.250 0.9461 0.03587 0.02682 -0.0566 0.0144 1.0000
7.500 0.9684 0.03905 0.03044 -0.0552 0.0141 1.0000
7.750 0.9845 0.04234 0.03420 -0.0529 0.0138 1.0000
8.000 0.9955 0.04534 0.03761 -0.0502 0.0132 1.0000
8.250 1.0029 0.04799 0.04060 -0.0474 0.0123 1.0000
8.500 1.0079 0.05033 0.04319 -0.0446 0.0115 1.0000
8.750 1.0079 0.05248 0.04550 -0.0418 0.0104 1.0000
9.000 1.0047 0.05559 0.04890 -0.0383 0.0102 1.0000
9.250 0.9885 0.05956 0.05312 -0.0339 0.0097 1.0000
9.500 0.9816 0.06210 0.05591 -0.0302 0.0098 1.0000
9.750 0.9610 0.06621 0.06026 -0.0263 0.0096 1.0000
10.000 0.9471 0.06948 0.06374 -0.0235 0.0096 1.0000
10.250 0.9343 0.07275 0.06720 -0.0214 0.0096 1.0000
10.500 0.9149 0.07707 0.07171 -0.0201 0.0096 1.0000
10.750 0.9029 0.08072 0.07553 -0.0197 0.0097 1.0000
11.000 0.8876 0.08529 0.08025 -0.0202 0.0098 1.0000
11.250 0.8728 0.09048 0.08559 -0.0219 0.0099 1.0000
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Polar data table (+)
Polar graphs
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