YS-900 (ys900-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: YS-900 (ys900-il) Reynolds number: 200,000 Max Cl/Cd: 21.58 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ys900-il-200000-n5.txt Download as CSV file: xf-ys900-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: YS-900
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6444 0.08646 0.08313 -0.0260 1.0000 0.0156
-8.250 -0.6615 0.08452 0.08114 -0.0218 1.0000 0.0156
-8.000 -0.6804 0.08115 0.07773 -0.0177 1.0000 0.0157
-7.750 -0.6958 0.07721 0.07372 -0.0141 1.0000 0.0159
-7.500 -0.7090 0.07332 0.06975 -0.0105 1.0000 0.0162
-7.250 -0.7195 0.06964 0.06598 -0.0067 1.0000 0.0165
-7.000 -0.7265 0.06619 0.06244 -0.0032 1.0000 0.0168
-6.750 -0.7268 0.06250 0.05864 -0.0009 0.9989 0.0173
-6.500 -0.7228 0.05897 0.05497 0.0009 0.9972 0.0179
-6.250 -0.7156 0.05548 0.05129 0.0027 0.9952 0.0186
-6.000 -0.7069 0.05223 0.04783 0.0046 0.9936 0.0196
-5.750 -0.6986 0.04914 0.04451 0.0072 0.9915 0.0205
-5.500 -0.6883 0.04615 0.04126 0.0098 0.9893 0.0217
-5.250 -0.6751 0.04330 0.03811 0.0123 0.9871 0.0232
-5.000 -0.6491 0.04374 0.03791 0.0149 0.9848 0.0275
-4.750 -0.6322 0.04182 0.03557 0.0173 0.9829 0.0278
-4.500 -0.6244 0.03509 0.02867 0.0191 0.9816 0.0302
-4.250 -0.6091 0.03275 0.02611 0.0213 0.9795 0.0319
-4.000 -0.5861 0.03044 0.02345 0.0238 0.9778 0.0239
-3.750 -0.5578 0.02797 0.02056 0.0260 0.9766 0.0135
-3.500 -0.5337 0.02579 0.01804 0.0273 0.9753 0.0122
-3.250 -0.5059 0.02381 0.01573 0.0281 0.9744 0.0107
-3.000 -0.4757 0.02208 0.01372 0.0285 0.9737 0.0094
-2.750 -0.4457 0.02065 0.01209 0.0286 0.9728 0.0085
-2.500 -0.4178 0.01953 0.01083 0.0289 0.9717 0.0077
-2.250 -0.3907 0.01878 0.00972 0.0293 0.9703 0.0070
-2.000 -0.3636 0.01816 0.00903 0.0293 0.9689 0.0066
-1.750 -0.3451 0.01760 0.00839 0.0312 0.9657 0.0063
-1.500 -0.3231 0.01712 0.00777 0.0324 0.9628 0.0061
-1.250 -0.2974 0.01677 0.00720 0.0328 0.9603 0.0061
-0.750 -0.0979 0.01789 0.01161 0.0049 0.9813 0.9691
-0.500 -0.0646 0.01778 0.01144 0.0032 0.9796 0.9710
-0.250 -0.0322 0.01771 0.01135 0.0016 0.9776 0.9731
0.000 0.0000 0.01769 0.01131 0.0000 0.9753 0.9753
0.250 0.0321 0.01772 0.01135 -0.0015 0.9732 0.9776
0.500 0.0644 0.01778 0.01144 -0.0031 0.9711 0.9796
0.750 0.2386 0.01653 0.00669 -0.0317 0.0067 0.9566
1.250 0.2976 0.01676 0.00718 -0.0329 0.0061 0.9603
1.500 0.3231 0.01710 0.00774 -0.0325 0.0061 0.9628
1.750 0.3451 0.01762 0.00841 -0.0312 0.0063 0.9658
2.000 0.3638 0.01817 0.00904 -0.0294 0.0066 0.9689
2.250 0.3907 0.01881 0.00975 -0.0292 0.0069 0.9703
2.500 0.4178 0.01955 0.01084 -0.0289 0.0077 0.9717
2.750 0.4457 0.02065 0.01210 -0.0287 0.0085 0.9728
3.000 0.4758 0.02212 0.01377 -0.0285 0.0095 0.9736
3.250 0.5057 0.02374 0.01566 -0.0282 0.0105 0.9744
3.500 0.5337 0.02573 0.01798 -0.0273 0.0120 0.9753
3.750 0.5578 0.02803 0.02062 -0.0260 0.0136 0.9765
4.000 0.5862 0.03018 0.02318 -0.0240 0.0227 0.9779
4.250 0.6092 0.03277 0.02614 -0.0213 0.0320 0.9795
4.500 0.6245 0.03508 0.02865 -0.0191 0.0302 0.9816
6.500 0.7228 0.05895 0.05494 -0.0010 0.0179 0.9972
6.750 0.7269 0.06252 0.05866 0.0008 0.0173 0.9989
7.000 0.7268 0.06614 0.06240 0.0032 0.0168 1.0000
7.250 0.7199 0.06959 0.06593 0.0067 0.0165 1.0000
7.500 0.7091 0.07330 0.06973 0.0104 0.0162 1.0000
7.750 0.6955 0.07727 0.07378 0.0141 0.0159 1.0000
8.000 0.6803 0.08118 0.07776 0.0177 0.0157 1.0000
8.250 0.6600 0.08485 0.08147 0.0218 0.0156 1.0000
9.000 0.5322 0.08474 0.08176 0.0270 0.0181 1.0000
9.250 0.5217 0.08956 0.08655 0.0255 0.0181 1.0000
9.500 0.5135 0.09407 0.09104 0.0246 0.0180 1.0000
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Polar data table (+)
Polar graphs
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