YS-930 (ys930-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: YS-930 (ys930-il) Reynolds number: 500,000 Max Cl/Cd: 108.25 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ys930-il-500000-n5.txt Download as CSV file: xf-ys930-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4353 0.09323 0.09101 -0.0564 0.9937 0.0021
-10.500 -0.4531 0.08257 0.08040 -0.0623 0.9899 0.0020
-9.500 -0.4845 0.04108 0.03853 -0.1039 0.9462 0.0017
-9.000 -0.4708 0.02839 0.02474 -0.1180 0.9185 0.0017
-8.750 -0.4732 0.02340 0.01906 -0.1170 0.9057 0.0018
-8.500 -0.4643 0.02051 0.01571 -0.1155 0.8976 0.0020
-8.250 -0.4458 0.01908 0.01402 -0.1149 0.8924 0.0022
-8.000 -0.4241 0.01832 0.01312 -0.1145 0.8881 0.0024
-7.750 -0.4032 0.01732 0.01193 -0.1138 0.8839 0.0027
-7.500 -0.3815 0.01635 0.01077 -0.1132 0.8803 0.0029
-7.250 -0.3597 0.01538 0.00961 -0.1125 0.8772 0.0032
-7.000 -0.3374 0.01457 0.00865 -0.1118 0.8740 0.0035
-6.750 -0.3124 0.01420 0.00820 -0.1116 0.8712 0.0041
-6.500 -0.2897 0.01338 0.00718 -0.1110 0.8685 0.0046
-6.250 -0.2670 0.01247 0.00610 -0.1104 0.8662 0.0054
-6.000 -0.2425 0.01187 0.00538 -0.1100 0.8641 0.0061
-5.750 -0.2175 0.01137 0.00477 -0.1096 0.8619 0.0082
-5.500 -0.1924 0.01088 0.00415 -0.1092 0.8597 0.0119
-5.250 -0.1664 0.01057 0.00381 -0.1090 0.8575 0.0168
-5.000 -0.1404 0.01021 0.00342 -0.1088 0.8555 0.0262
-4.750 -0.1146 0.00979 0.00304 -0.1087 0.8537 0.0523
-4.500 -0.0901 0.00917 0.00262 -0.1085 0.8522 0.1186
-4.250 -0.0639 0.00891 0.00249 -0.1084 0.8507 0.1636
-4.000 -0.0369 0.00880 0.00238 -0.1084 0.8491 0.1817
-3.750 -0.0101 0.00868 0.00233 -0.1084 0.8475 0.2072
-3.500 0.0171 0.00859 0.00224 -0.1084 0.8459 0.2194
-3.250 0.0445 0.00853 0.00214 -0.1085 0.8445 0.2261
-3.000 0.0718 0.00844 0.00202 -0.1085 0.8430 0.2317
-2.750 0.0994 0.00839 0.00193 -0.1086 0.8415 0.2370
-2.500 0.1271 0.00831 0.00185 -0.1086 0.8402 0.2432
-2.250 0.1550 0.00827 0.00179 -0.1088 0.8391 0.2498
-2.000 0.1825 0.00821 0.00175 -0.1089 0.8379 0.2569
-1.500 0.2365 0.00810 0.00169 -0.1088 0.8348 0.2755
-1.250 0.2636 0.00805 0.00168 -0.1088 0.8332 0.2873
-1.000 0.2908 0.00799 0.00168 -0.1088 0.8316 0.3028
-0.750 0.3181 0.00793 0.00169 -0.1088 0.8301 0.3208
-0.500 0.3454 0.00787 0.00170 -0.1088 0.8286 0.3419
-0.250 0.3729 0.00780 0.00173 -0.1089 0.8272 0.3662
0.000 0.4005 0.00773 0.00176 -0.1090 0.8257 0.3954
0.250 0.4269 0.00765 0.00182 -0.1089 0.8236 0.4292
0.500 0.4527 0.00756 0.00190 -0.1086 0.8211 0.4687
0.750 0.4788 0.00745 0.00197 -0.1083 0.8184 0.5139
1.000 0.5050 0.00732 0.00202 -0.1081 0.8151 0.5666
1.250 0.5314 0.00716 0.00206 -0.1078 0.8116 0.6275
1.500 0.5543 0.00698 0.00215 -0.1068 0.8063 0.6972
1.750 0.5775 0.00673 0.00223 -0.1056 0.8007 0.7821
2.000 0.6003 0.00648 0.00232 -0.1042 0.7938 0.8841
2.250 0.6522 0.00637 0.00235 -0.1093 0.7827 0.9640
2.500 0.6829 0.00633 0.00230 -0.1098 0.7600 0.9868
2.750 0.7047 0.00651 0.00211 -0.1083 0.6545 1.0000
3.000 0.7021 0.00741 0.00242 -0.1018 0.5368 1.0000
3.250 0.7004 0.00846 0.00287 -0.0959 0.4111 1.0000
3.500 0.7033 0.00952 0.00337 -0.0911 0.2819 1.0000
3.750 0.7080 0.01065 0.00387 -0.0869 0.1465 1.0000
4.000 0.7215 0.01140 0.00428 -0.0843 0.0727 1.0000
4.250 0.7392 0.01193 0.00465 -0.0825 0.0372 1.0000
4.500 0.7582 0.01238 0.00504 -0.0808 0.0200 1.0000
4.750 0.7775 0.01285 0.00548 -0.0792 0.0108 1.0000
5.000 0.7970 0.01329 0.00600 -0.0776 0.0082 1.0000
5.250 0.8160 0.01372 0.00643 -0.0759 0.0058 1.0000
5.500 0.8338 0.01426 0.00700 -0.0741 0.0041 1.0000
5.750 0.8516 0.01481 0.00762 -0.0722 0.0036 1.0000
6.000 0.8691 0.01541 0.00835 -0.0702 0.0033 1.0000
6.250 0.8872 0.01599 0.00899 -0.0685 0.0027 1.0000
6.500 0.9053 0.01661 0.00965 -0.0668 0.0023 1.0000
6.750 0.9224 0.01740 0.01052 -0.0650 0.0021 1.0000
7.000 0.9362 0.01937 0.01269 -0.0625 0.0018 1.0000
7.250 0.9574 0.02065 0.01410 -0.0614 0.0017 1.0000
7.500 0.9816 0.02227 0.01591 -0.0609 0.0017 1.0000
7.750 1.0087 0.02447 0.01840 -0.0609 0.0016 1.0000
8.000 1.0314 0.02706 0.02133 -0.0601 0.0016 1.0000
8.250 1.0483 0.03013 0.02480 -0.0582 0.0016 1.0000
8.500 1.0584 0.03365 0.02873 -0.0553 0.0016 1.0000
8.750 1.0613 0.03760 0.03311 -0.0514 0.0017 1.0000
9.000 1.0588 0.04154 0.03740 -0.0469 0.0017 1.0000
9.250 1.0472 0.04572 0.04192 -0.0413 0.0017 1.0000
9.500 1.0343 0.04901 0.04545 -0.0361 0.0017 1.0000
9.750 1.0146 0.05297 0.04965 -0.0308 0.0018 1.0000
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Polar data table (+)
Polar graphs
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