YS-930 (ys930-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: YS-930 (ys930-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.3 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ys930-il-1000000-n5.txt Download as CSV file: xf-ys930-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4848 0.08063 0.07905 -0.0673 0.9881 0.0011
-11.000 -0.5410 0.06268 0.06105 -0.0774 0.9801 0.0009
-10.750 -0.5678 0.05061 0.04888 -0.0881 0.9571 0.0009
-10.500 -0.5577 0.03170 0.02933 -0.1221 0.9306 0.0009
-10.250 -0.5711 0.02739 0.02452 -0.1218 0.9001 0.0009
-10.000 -0.5738 0.02454 0.02129 -0.1198 0.8860 0.0009
-9.750 -0.5708 0.02196 0.01833 -0.1178 0.8765 0.0009
-9.500 -0.5609 0.01994 0.01600 -0.1162 0.8696 0.0009
-9.250 -0.5470 0.01830 0.01408 -0.1148 0.8645 0.0010
-9.000 -0.5302 0.01692 0.01247 -0.1137 0.8603 0.0011
-8.750 -0.5109 0.01586 0.01122 -0.1128 0.8564 0.0012
-8.500 -0.4890 0.01516 0.01033 -0.1122 0.8532 0.0014
-8.250 -0.4677 0.01430 0.00931 -0.1115 0.8503 0.0014
-8.000 -0.4443 0.01373 0.00863 -0.1111 0.8477 0.0015
-7.750 -0.4196 0.01334 0.00817 -0.1109 0.8451 0.0016
-7.500 -0.3960 0.01276 0.00749 -0.1105 0.8427 0.0017
-7.250 -0.3746 0.01180 0.00632 -0.1097 0.8403 0.0019
-7.000 -0.3506 0.01121 0.00560 -0.1092 0.8383 0.0021
-6.750 -0.3257 0.01071 0.00501 -0.1089 0.8365 0.0023
-6.500 -0.3002 0.01030 0.00451 -0.1087 0.8347 0.0025
-6.250 -0.2743 0.00997 0.00413 -0.1085 0.8329 0.0028
-6.000 -0.2481 0.00967 0.00374 -0.1084 0.8312 0.0034
-5.750 -0.2217 0.00942 0.00344 -0.1083 0.8295 0.0039
-5.500 -0.1957 0.00904 0.00303 -0.1081 0.8280 0.0073
-5.250 -0.1689 0.00885 0.00278 -0.1080 0.8265 0.0094
-5.000 -0.1421 0.00863 0.00253 -0.1080 0.8250 0.0129
-4.750 -0.1153 0.00840 0.00231 -0.1080 0.8236 0.0199
-4.500 -0.0889 0.00810 0.00207 -0.1079 0.8223 0.0383
-4.250 -0.0630 0.00771 0.00179 -0.1078 0.8210 0.0764
-4.000 -0.0375 0.00730 0.00156 -0.1076 0.8196 0.1285
-3.750 -0.0106 0.00710 0.00147 -0.1076 0.8184 0.1609
-3.500 0.0169 0.00700 0.00139 -0.1077 0.8172 0.1751
-3.250 0.0444 0.00690 0.00133 -0.1078 0.8160 0.1954
-3.000 0.0721 0.00681 0.00125 -0.1079 0.8149 0.2068
-2.750 0.0999 0.00676 0.00119 -0.1080 0.8138 0.2119
-2.500 0.1278 0.00671 0.00113 -0.1081 0.8126 0.2169
-2.250 0.1558 0.00668 0.00109 -0.1083 0.8115 0.2214
-2.000 0.1836 0.00662 0.00105 -0.1084 0.8105 0.2263
-1.750 0.2114 0.00657 0.00100 -0.1085 0.8095 0.2321
-1.500 0.2393 0.00653 0.00098 -0.1086 0.8082 0.2378
-1.250 0.2670 0.00648 0.00096 -0.1087 0.8068 0.2454
-1.000 0.2948 0.00643 0.00095 -0.1088 0.8054 0.2535
-0.750 0.3225 0.00638 0.00095 -0.1089 0.8040 0.2642
-0.500 0.3502 0.00634 0.00095 -0.1090 0.8024 0.2770
0.000 0.4056 0.00625 0.00096 -0.1091 0.7983 0.3066
0.250 0.4326 0.00618 0.00098 -0.1090 0.7952 0.3250
0.500 0.4594 0.00611 0.00100 -0.1089 0.7911 0.3458
0.750 0.4863 0.00604 0.00101 -0.1088 0.7867 0.3705
1.000 0.5129 0.00597 0.00104 -0.1086 0.7818 0.3984
1.250 0.5392 0.00588 0.00106 -0.1083 0.7756 0.4305
1.500 0.5654 0.00580 0.00109 -0.1081 0.7692 0.4663
1.750 0.5910 0.00571 0.00114 -0.1076 0.7598 0.5064
2.000 0.6158 0.00562 0.00118 -0.1070 0.7462 0.5502
2.250 0.6356 0.00561 0.00118 -0.1053 0.6931 0.6006
2.500 0.6326 0.00670 0.00157 -0.0988 0.5146 0.6426
2.750 0.6411 0.00742 0.00195 -0.0951 0.3953 0.7010
3.000 0.6531 0.00792 0.00228 -0.0921 0.3025 0.7762
3.250 0.6626 0.00832 0.00262 -0.0884 0.2129 0.8769
3.500 0.6994 0.00908 0.00314 -0.0910 0.1106 0.9960
3.750 0.7164 0.00978 0.00350 -0.0891 0.0377 1.0000
4.000 0.7364 0.01013 0.00376 -0.0877 0.0186 1.0000
4.250 0.7570 0.01047 0.00403 -0.0863 0.0071 1.0000
4.500 0.7783 0.01078 0.00431 -0.0850 0.0035 1.0000
4.750 0.7998 0.01107 0.00462 -0.0838 0.0028 1.0000
5.000 0.8210 0.01140 0.00497 -0.0825 0.0022 1.0000
5.250 0.8405 0.01187 0.00550 -0.0809 0.0018 1.0000
5.500 0.8613 0.01223 0.00594 -0.0796 0.0017 1.0000
5.750 0.8823 0.01254 0.00628 -0.0784 0.0016 1.0000
6.000 0.9013 0.01299 0.00678 -0.0767 0.0014 1.0000
6.250 0.9192 0.01353 0.00739 -0.0748 0.0012 1.0000
6.500 0.9358 0.01422 0.00816 -0.0726 0.0011 1.0000
6.750 0.9522 0.01499 0.00904 -0.0705 0.0011 1.0000
7.000 0.9695 0.01578 0.00992 -0.0686 0.0011 1.0000
7.250 0.9868 0.01689 0.01116 -0.0667 0.0010 1.0000
7.500 1.0063 0.01790 0.01229 -0.0653 0.0010 1.0000
7.750 1.0294 0.01971 0.01431 -0.0645 0.0010 1.0000
8.000 1.0563 0.02246 0.01738 -0.0645 0.0010 1.0000
8.250 1.0767 0.02564 0.02097 -0.0631 0.0010 1.0000
8.500 1.0863 0.03136 0.02728 -0.0595 0.0011 1.0000
8.750 1.0856 0.03722 0.03363 -0.0545 0.0012 1.0000
9.000 1.0800 0.04249 0.03927 -0.0492 0.0013 1.0000
9.250 1.0725 0.04693 0.04400 -0.0442 0.0013 1.0000
9.500 1.0590 0.05098 0.04828 -0.0387 0.0013 1.0000
9.750 1.0451 0.05405 0.05152 -0.0334 0.0014 1.0000
10.000 1.0253 0.05769 0.05533 -0.0283 0.0014 1.0000
10.250 1.0085 0.06106 0.05885 -0.0245 0.0014 1.0000
10.500 0.9847 0.06533 0.06327 -0.0212 0.0014 1.0000
10.750 0.9646 0.06950 0.06757 -0.0193 0.0014 1.0000
11.000 0.9457 0.07394 0.07213 -0.0186 0.0014 1.0000
11.250 0.9245 0.07923 0.07752 -0.0191 0.0014 1.0000
11.500 0.9021 0.08562 0.08402 -0.0213 0.0014 1.0000
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Polar data table (+)
Polar graphs
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