YS-915 (ys915-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: YS-915 (ys915-il) Reynolds number: 100,000 Max Cl/Cd: 34.01 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ys915-il-100000-n5.txt Download as CSV file: xf-ys915-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5153 0.09354 0.08875 -0.0392 1.0000 0.0117
-9.250 -0.5268 0.08933 0.08462 -0.0394 1.0000 0.0114
-9.000 -0.5383 0.08525 0.08061 -0.0397 1.0000 0.0112
-8.750 -0.5525 0.08063 0.07605 -0.0405 1.0000 0.0111
-8.500 -0.5688 0.07564 0.07110 -0.0421 1.0000 0.0107
-8.250 -0.5927 0.07178 0.06726 -0.0426 1.0000 0.0108
-8.000 -0.6162 0.06893 0.06436 -0.0405 1.0000 0.0106
-7.750 -0.6334 0.06534 0.06067 -0.0390 1.0000 0.0105
-7.500 -0.6469 0.06136 0.05651 -0.0373 1.0000 0.0101
-7.250 -0.6556 0.05744 0.05237 -0.0353 1.0000 0.0099
-7.000 -0.6589 0.05370 0.04834 -0.0333 1.0000 0.0096
-6.750 -0.6517 0.05005 0.04431 -0.0324 0.9987 0.0092
-6.500 -0.6394 0.04620 0.04003 -0.0323 0.9963 0.0091
-6.250 -0.6235 0.04335 0.03677 -0.0318 0.9945 0.0089
-6.000 -0.6086 0.03992 0.03287 -0.0310 0.9927 0.0088
-5.750 -0.5918 0.03678 0.02926 -0.0301 0.9907 0.0088
-5.500 -0.5729 0.03407 0.02610 -0.0291 0.9891 0.0088
-5.250 -0.5524 0.03142 0.02300 -0.0281 0.9876 0.0089
-5.000 -0.5307 0.02859 0.01977 -0.0273 0.9863 0.0094
-4.750 -0.5076 0.02690 0.01786 -0.0270 0.9849 0.0114
-4.500 -0.4823 0.02596 0.01669 -0.0268 0.9835 0.0157
-4.250 -0.4565 0.02459 0.01512 -0.0262 0.9823 0.0173
-4.000 -0.4336 0.02313 0.01341 -0.0250 0.9808 0.0187
-3.750 -0.4139 0.02165 0.01172 -0.0236 0.9789 0.0218
-3.250 -0.3698 0.01865 0.00926 -0.0221 0.9751 0.1631
-3.000 -0.3509 0.01759 0.00939 -0.0211 0.9731 0.4400
-2.750 -0.3274 0.01746 0.00948 -0.0203 0.9710 0.5225
-2.500 -0.2979 0.01743 0.00928 -0.0208 0.9693 0.5450
-2.250 -0.2728 0.01731 0.00907 -0.0204 0.9670 0.5650
-2.000 -0.2471 0.01721 0.00889 -0.0201 0.9644 0.5873
-1.750 -0.2198 0.01714 0.00869 -0.0202 0.9619 0.6145
-1.500 -0.1912 0.01711 0.00867 -0.0206 0.9596 0.6478
-1.250 -0.1616 0.01708 0.00871 -0.0210 0.9576 0.6896
-1.000 -0.1314 0.01705 0.00882 -0.0215 0.9557 0.7457
-0.750 -0.0986 0.01694 0.00893 -0.0225 0.9537 0.8262
-0.500 -0.0225 0.01713 0.00915 -0.0329 0.9561 0.9480
-0.250 0.0154 0.01736 0.00927 -0.0357 0.9541 1.0000
0.000 0.0389 0.01747 0.00929 -0.0353 0.9497 1.0000
0.250 0.0680 0.01766 0.00940 -0.0361 0.9462 1.0000
0.500 0.1007 0.01790 0.00959 -0.0376 0.9435 1.0000
0.750 0.1212 0.01800 0.00968 -0.0365 0.9378 1.0000
1.000 0.1506 0.01819 0.00986 -0.0372 0.9336 1.0000
1.250 0.1849 0.01843 0.01012 -0.0390 0.9305 1.0000
1.500 0.2057 0.01856 0.01026 -0.0379 0.9238 1.0000
1.750 0.2380 0.01875 0.01052 -0.0391 0.9195 1.0000
2.000 0.2657 0.01892 0.01076 -0.0394 0.9137 1.0000
2.250 0.2953 0.01907 0.01112 -0.0400 0.9076 1.0000
2.500 0.3282 0.01921 0.01139 -0.0412 0.9021 1.0000
2.750 0.3574 0.01929 0.01163 -0.0415 0.8942 1.0000
3.000 0.3874 0.01933 0.01184 -0.0420 0.8857 1.0000
3.250 0.4303 0.01920 0.01199 -0.0446 0.8785 1.0000
3.500 0.4679 0.01872 0.01180 -0.0457 0.8637 1.0000
3.750 0.5558 0.01634 0.00684 -0.0494 0.1862 1.0000
4.000 0.5686 0.01819 0.00789 -0.0468 0.0538 1.0000
4.250 0.5848 0.01927 0.00893 -0.0445 0.0345 1.0000
4.500 0.6009 0.02035 0.01017 -0.0420 0.0285 1.0000
4.750 0.6154 0.02199 0.01185 -0.0394 0.0244 1.0000
5.000 0.6371 0.02291 0.01291 -0.0381 0.0181 1.0000
5.250 0.6620 0.02469 0.01480 -0.0372 0.0162 1.0000
5.500 0.6910 0.02695 0.01722 -0.0371 0.0152 1.0000
5.750 0.7195 0.02970 0.02025 -0.0369 0.0146 1.0000
6.000 0.7436 0.03291 0.02399 -0.0357 0.0142 1.0000
6.250 0.7625 0.03582 0.02731 -0.0337 0.0141 1.0000
6.500 0.7771 0.03898 0.03089 -0.0312 0.0141 1.0000
6.750 0.7889 0.04200 0.03431 -0.0283 0.0141 1.0000
7.000 0.7989 0.04491 0.03760 -0.0251 0.0143 1.0000
7.250 0.8078 0.04766 0.04072 -0.0219 0.0146 1.0000
7.500 0.8133 0.05088 0.04433 -0.0183 0.0150 1.0000
7.750 0.8147 0.05424 0.04800 -0.0148 0.0150 1.0000
8.000 0.8112 0.05771 0.05170 -0.0115 0.0146 1.0000
8.250 0.8057 0.06120 0.05541 -0.0082 0.0144 1.0000
8.500 0.7921 0.06542 0.05982 -0.0048 0.0140 1.0000
8.750 0.7789 0.06885 0.06341 -0.0013 0.0139 1.0000
9.000 0.7728 0.07097 0.06567 0.0018 0.0141 1.0000
9.250 0.7517 0.07518 0.07000 0.0042 0.0139 1.0000
9.500 0.7496 0.07722 0.07220 0.0057 0.0144 1.0000
9.750 0.7235 0.08554 0.08077 0.0038 0.0196 1.0000
10.000 0.7099 0.09121 0.08647 0.0009 0.0194 1.0000
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Polar data table (+)
Polar graphs
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