YS-930 (ys930-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: YS-930 (ys930-il) Reynolds number: 500,000 Max Cl/Cd: 118.95 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ys930-il-500000.txt Download as CSV file: xf-ys930-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3107 0.10582 0.10373 -0.0539 0.9942 0.0186
-11.000 -0.3065 0.10089 0.09880 -0.0568 0.9924 0.0197
-7.250 -0.3314 0.02327 0.01870 -0.1194 0.9336 0.0112
-7.000 -0.3156 0.01975 0.01473 -0.1184 0.9288 0.0104
-6.750 -0.2959 0.01747 0.01214 -0.1172 0.9244 0.0100
-6.500 -0.2733 0.01572 0.01015 -0.1165 0.9212 0.0098
-6.250 -0.2491 0.01432 0.00855 -0.1160 0.9186 0.0100
-6.000 -0.2284 0.01333 0.00741 -0.1148 0.9148 0.0107
-5.750 -0.2040 0.01274 0.00672 -0.1142 0.9116 0.0120
-5.500 -0.1829 0.01137 0.00510 -0.1132 0.9087 0.0170
-5.250 -0.1569 0.01079 0.00441 -0.1130 0.9067 0.0259
-5.000 -0.1330 0.00990 0.00370 -0.1125 0.9046 0.0775
-4.750 -0.1107 0.00933 0.00353 -0.1120 0.9021 0.1831
-4.500 -0.0840 0.00928 0.00347 -0.1119 0.9000 0.2038
-4.250 -0.0568 0.00925 0.00338 -0.1120 0.8980 0.2165
-4.000 -0.0292 0.00919 0.00326 -0.1121 0.8961 0.2270
-3.750 -0.0011 0.00918 0.00323 -0.1123 0.8945 0.2433
-3.500 0.0269 0.00911 0.00316 -0.1125 0.8931 0.2534
-3.250 0.0549 0.00903 0.00306 -0.1127 0.8918 0.2607
-3.000 0.0807 0.00900 0.00301 -0.1124 0.8900 0.2679
-2.750 0.1063 0.00892 0.00294 -0.1122 0.8879 0.2752
-2.250 0.1593 0.00881 0.00285 -0.1120 0.8843 0.2940
-2.000 0.1864 0.00873 0.00282 -0.1120 0.8826 0.3079
-1.750 0.2138 0.00865 0.00279 -0.1120 0.8812 0.3257
-1.500 0.2414 0.00856 0.00278 -0.1122 0.8798 0.3500
-1.250 0.2692 0.00847 0.00280 -0.1124 0.8785 0.3833
-1.000 0.2937 0.00839 0.00288 -0.1119 0.8766 0.4252
-0.750 0.3179 0.00828 0.00297 -0.1114 0.8743 0.4776
-0.500 0.3425 0.00814 0.00306 -0.1109 0.8721 0.5410
-0.250 0.3671 0.00796 0.00314 -0.1104 0.8700 0.6188
0.000 0.3912 0.00773 0.00323 -0.1096 0.8680 0.7105
0.250 0.4148 0.00748 0.00332 -0.1085 0.8661 0.8139
0.500 0.4535 0.00731 0.00345 -0.1105 0.8650 0.9246
0.750 0.5061 0.00730 0.00349 -0.1161 0.8636 0.9717
1.000 0.5473 0.00731 0.00354 -0.1191 0.8604 0.9907
1.250 0.5926 0.00724 0.00351 -0.1231 0.8569 1.0000
1.500 0.6199 0.00719 0.00344 -0.1228 0.8524 1.0000
1.750 0.6412 0.00720 0.00348 -0.1213 0.8458 1.0000
2.000 0.6687 0.00708 0.00334 -0.1209 0.8387 1.0000
2.250 0.6899 0.00698 0.00328 -0.1192 0.8285 1.0000
2.500 0.7135 0.00676 0.00303 -0.1177 0.8129 1.0000
2.750 0.7337 0.00661 0.00287 -0.1156 0.7951 1.0000
3.000 0.7542 0.00655 0.00285 -0.1138 0.7797 1.0000
3.250 0.7732 0.00650 0.00280 -0.1116 0.7554 1.0000
3.500 0.7777 0.00670 0.00260 -0.1060 0.6466 1.0000
3.750 0.7643 0.00803 0.00307 -0.0973 0.4827 1.0000
4.000 0.7576 0.00943 0.00368 -0.0907 0.3181 1.0000
4.250 0.7554 0.01096 0.00434 -0.0852 0.1421 1.0000
4.500 0.7609 0.01229 0.00504 -0.0812 0.0282 1.0000
4.750 0.7737 0.01332 0.00617 -0.0780 0.0134 1.0000
5.000 0.7913 0.01395 0.00687 -0.0759 0.0120 1.0000
5.250 0.8066 0.01474 0.00774 -0.0733 0.0111 1.0000
5.500 0.8214 0.01568 0.00877 -0.0707 0.0107 1.0000
5.750 0.8384 0.01686 0.01004 -0.0685 0.0106 1.0000
6.000 0.8633 0.01847 0.01176 -0.0679 0.0108 1.0000
6.250 0.8912 0.01991 0.01330 -0.0678 0.0103 1.0000
6.500 0.9107 0.02022 0.01361 -0.0666 0.0087 1.0000
6.750 0.9411 0.02215 0.01570 -0.0670 0.0086 1.0000
7.000 0.9676 0.02414 0.01788 -0.0668 0.0080 1.0000
7.250 1.0060 0.03290 0.02747 -0.0656 0.0149 1.0000
7.500 1.0184 0.03601 0.03081 -0.0633 0.0142 1.0000
7.750 1.0035 0.04526 0.04066 -0.0575 0.0131 1.0000
8.000 1.0071 0.04831 0.04397 -0.0539 0.0131 1.0000
8.250 1.0086 0.05130 0.04722 -0.0502 0.0130 1.0000
8.500 1.0075 0.05414 0.05032 -0.0463 0.0130 1.0000
8.750 1.0042 0.05679 0.05320 -0.0423 0.0129 1.0000
9.000 1.0175 0.05668 0.05330 -0.0391 0.0119 1.0000
9.250 1.0145 0.05930 0.05611 -0.0352 0.0113 1.0000
9.500 1.0028 0.06203 0.05901 -0.0305 0.0110 1.0000
9.750 0.9875 0.06510 0.06223 -0.0263 0.0108 1.0000
10.000 0.9706 0.06839 0.06568 -0.0230 0.0107 1.0000
10.250 0.9527 0.07196 0.06938 -0.0207 0.0107 1.0000
10.500 0.9324 0.07616 0.07370 -0.0193 0.0107 1.0000
10.750 0.9111 0.08091 0.07857 -0.0191 0.0109 1.0000
11.000 0.8897 0.08648 0.08424 -0.0205 0.0110 1.0000
11.250 0.8677 0.09286 0.09071 -0.0235 0.0115 1.0000
11.500 0.8468 0.10120 0.09911 -0.0289 0.0118 1.0000
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Polar data table (+)
Polar graphs
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