YS-915 (ys915-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: YS-915 (ys915-il) Reynolds number: 100,000 Max Cl/Cd: 29.42 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ys915-il-100000.txt Download as CSV file: xf-ys915-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: YS-915
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5395 0.10164 0.09708 -0.0361 1.0000 0.1107
-9.000 -0.5603 0.09878 0.09432 -0.0367 1.0000 0.1111
-8.750 -0.5875 0.09586 0.09150 -0.0375 1.0000 0.1113
-8.500 -0.6032 0.09278 0.08848 -0.0367 1.0000 0.1112
-8.250 -0.6182 0.08947 0.08520 -0.0358 1.0000 0.1111
-5.250 -0.6111 0.03808 0.03029 -0.0228 1.0000 0.0602
-5.000 -0.5893 0.03319 0.02514 -0.0215 1.0000 0.0510
-4.750 -0.5651 0.03113 0.02245 -0.0193 1.0000 0.0456
-4.500 -0.5422 0.02831 0.01931 -0.0179 1.0000 0.0437
-4.250 -0.5184 0.02621 0.01693 -0.0165 1.0000 0.0426
-4.000 -0.4945 0.02437 0.01489 -0.0150 1.0000 0.0426
-3.750 -0.4719 0.02294 0.01337 -0.0135 1.0000 0.0440
-3.500 -0.4506 0.02169 0.01205 -0.0119 1.0000 0.0475
-3.250 -0.4311 0.02035 0.01070 -0.0104 1.0000 0.0611
-3.000 -0.4132 0.01724 0.00895 -0.0089 1.0000 0.2855
-2.750 -0.4033 0.01670 0.00932 -0.0046 1.0000 0.5553
-2.500 -0.3902 0.01668 0.00954 -0.0009 1.0000 0.6341
-2.250 -0.3701 0.01648 0.00934 0.0009 1.0000 0.6708
-2.000 -0.3476 0.01623 0.00907 0.0019 1.0000 0.7025
-1.750 -0.3254 0.01599 0.00888 0.0030 1.0000 0.7433
-1.500 -0.2993 0.01572 0.00880 0.0037 1.0000 0.8127
-1.250 -0.2043 0.01594 0.00891 -0.0107 1.0000 1.0000
-1.000 -0.1847 0.01594 0.00861 -0.0102 1.0000 1.0000
-0.750 -0.1643 0.01604 0.00849 -0.0095 1.0000 1.0000
-0.500 -0.1438 0.01617 0.00845 -0.0088 1.0000 1.0000
-0.250 -0.1232 0.01634 0.00846 -0.0080 1.0000 1.0000
0.000 -0.1026 0.01653 0.00849 -0.0072 1.0000 1.0000
0.250 -0.0819 0.01674 0.00859 -0.0065 1.0000 1.0000
0.500 -0.0613 0.01698 0.00874 -0.0058 1.0000 1.0000
0.750 -0.0407 0.01724 0.00893 -0.0050 1.0000 1.0000
1.000 -0.0202 0.01752 0.00917 -0.0043 1.0000 1.0000
1.250 0.0002 0.01783 0.00944 -0.0037 1.0000 1.0000
1.500 0.0205 0.01816 0.00976 -0.0030 1.0000 1.0000
1.750 0.0405 0.01852 0.01011 -0.0023 1.0000 1.0000
2.000 0.0605 0.01891 0.01051 -0.0017 1.0000 1.0000
2.250 0.0802 0.01933 0.01095 -0.0011 1.0000 1.0000
2.500 0.0997 0.01978 0.01145 -0.0005 1.0000 1.0000
2.750 0.1189 0.02027 0.01199 0.0001 1.0000 1.0000
3.000 0.1673 0.02141 0.01332 -0.0052 0.9883 1.0000
3.250 0.2158 0.02245 0.01453 -0.0104 0.9747 1.0000
3.500 0.2631 0.02330 0.01559 -0.0150 0.9603 1.0000
3.750 0.3137 0.02405 0.01661 -0.0200 0.9450 1.0000
4.000 0.3615 0.02439 0.01734 -0.0240 0.9252 1.0000
4.250 0.5822 0.01979 0.00976 -0.0425 0.0643 1.0000
4.500 0.5997 0.02163 0.01150 -0.0402 0.0534 1.0000
4.750 0.6323 0.02367 0.01370 -0.0401 0.0491 1.0000
5.000 0.6671 0.02658 0.01659 -0.0412 0.0414 1.0000
5.250 0.6985 0.02895 0.01928 -0.0408 0.0406 1.0000
5.500 0.7300 0.03317 0.02375 -0.0409 0.0423 1.0000
5.750 0.7537 0.03442 0.02578 -0.0375 0.0486 1.0000
6.000 0.7783 0.03853 0.03054 -0.0346 0.0626 1.0000
7.750 0.8493 0.06858 0.06327 -0.0141 0.1320 1.0000
8.750 0.8244 0.08191 0.07704 -0.0043 0.1056 1.0000
9.000 0.7934 0.08383 0.07913 -0.0009 0.1046 1.0000
9.250 0.7679 0.08693 0.08231 0.0004 0.1037 1.0000
9.500 0.7436 0.09127 0.08668 -0.0008 0.1025 1.0000
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Polar data table (+)
Polar graphs
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