NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.38 at α=0.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ls413-il-1000000-n5.txt Download as CSV file: xf-ls413-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-16.500 -1.0092 0.06295 0.06009 -0.0675 1.0000 0.0116
-16.250 -1.0322 0.05525 0.05220 -0.0728 1.0000 0.0116
-16.000 -1.0454 0.04977 0.04657 -0.0763 1.0000 0.0116
-15.750 -1.0535 0.04546 0.04212 -0.0787 1.0000 0.0117
-15.500 -1.0575 0.04198 0.03852 -0.0803 1.0000 0.0117
-15.250 -1.0577 0.03912 0.03555 -0.0814 1.0000 0.0118
-15.000 -1.0577 0.03645 0.03277 -0.0822 1.0000 0.0118
-14.750 -1.0546 0.03424 0.03045 -0.0825 1.0000 0.0119
-14.500 -1.0507 0.03225 0.02837 -0.0826 1.0000 0.0119
-14.250 -1.0462 0.03054 0.02657 -0.0822 1.0000 0.0120
-14.000 -1.0440 0.02903 0.02498 -0.0809 1.0000 0.0121
-13.750 -1.0370 0.02758 0.02343 -0.0804 0.9973 0.0121
-13.500 -1.0173 0.02611 0.02185 -0.0821 0.9922 0.0122
-13.250 -0.9955 0.02476 0.02039 -0.0838 0.9866 0.0123
-13.000 -0.9701 0.02360 0.01913 -0.0857 0.9823 0.0125
-12.750 -0.9471 0.02262 0.01806 -0.0866 0.9751 0.0126
-12.500 -0.9219 0.02175 0.01709 -0.0876 0.9690 0.0128
-12.250 -0.8987 0.02100 0.01626 -0.0880 0.9605 0.0129
-12.000 -0.8745 0.02035 0.01551 -0.0883 0.9532 0.0131
-11.750 -0.8506 0.01978 0.01486 -0.0884 0.9449 0.0132
-11.500 -0.8263 0.01926 0.01426 -0.0885 0.9377 0.0133
-11.250 -0.8037 0.01839 0.01328 -0.0886 0.9303 0.0135
-11.000 -0.7808 0.01749 0.01227 -0.0887 0.9239 0.0137
-10.750 -0.7563 0.01677 0.01148 -0.0889 0.9176 0.0138
-10.500 -0.7311 0.01615 0.01079 -0.0892 0.9115 0.0139
-10.250 -0.7052 0.01560 0.01018 -0.0894 0.9061 0.0141
-10.000 -0.6789 0.01510 0.00961 -0.0897 0.9000 0.0142
-9.750 -0.6523 0.01464 0.00909 -0.0900 0.8939 0.0144
-9.500 -0.6251 0.01420 0.00859 -0.0903 0.8884 0.0145
-9.250 -0.5977 0.01378 0.00812 -0.0907 0.8829 0.0147
-9.000 -0.5701 0.01338 0.00766 -0.0911 0.8779 0.0149
-8.750 -0.5421 0.01299 0.00723 -0.0915 0.8735 0.0151
-8.500 -0.5138 0.01262 0.00681 -0.0920 0.8686 0.0153
-8.250 -0.4854 0.01226 0.00641 -0.0924 0.8636 0.0155
-8.000 -0.4569 0.01194 0.00603 -0.0929 0.8590 0.0157
-7.750 -0.4279 0.01161 0.00567 -0.0934 0.8543 0.0160
-7.500 -0.3990 0.01132 0.00533 -0.0939 0.8493 0.0162
-7.250 -0.3699 0.01105 0.00502 -0.0944 0.8449 0.0164
-7.000 -0.3405 0.01077 0.00470 -0.0950 0.8411 0.0167
-6.750 -0.3109 0.01045 0.00437 -0.0956 0.8370 0.0173
-6.500 -0.2813 0.01021 0.00411 -0.0962 0.8331 0.0178
-6.250 -0.2517 0.01001 0.00388 -0.0968 0.8293 0.0184
-6.000 -0.2219 0.00981 0.00367 -0.0973 0.8259 0.0192
-5.750 -0.1919 0.00963 0.00348 -0.0979 0.8224 0.0199
-5.500 -0.1619 0.00943 0.00327 -0.0986 0.8187 0.0211
-5.250 -0.1319 0.00925 0.00309 -0.0992 0.8152 0.0224
-5.000 -0.1019 0.00911 0.00293 -0.0997 0.8118 0.0239
-4.750 -0.0716 0.00894 0.00277 -0.1004 0.8087 0.0258
-4.500 -0.0413 0.00879 0.00263 -0.1010 0.8052 0.0282
-4.250 -0.0110 0.00865 0.00250 -0.1016 0.8013 0.0311
-4.000 0.0191 0.00853 0.00238 -0.1022 0.7976 0.0344
-3.750 0.0494 0.00840 0.00226 -0.1028 0.7942 0.0392
-3.500 0.0800 0.00825 0.00216 -0.1035 0.7908 0.0468
-3.250 0.1107 0.00808 0.00205 -0.1043 0.7871 0.0624
-3.000 0.1419 0.00783 0.00193 -0.1052 0.7835 0.0999
-2.750 0.1737 0.00750 0.00180 -0.1064 0.7798 0.1662
-2.500 0.2067 0.00702 0.00168 -0.1081 0.7758 0.2721
-2.250 0.2394 0.00663 0.00157 -0.1096 0.7701 0.3615
-1.750 0.3050 0.00590 0.00146 -0.1124 0.7563 0.5688
-1.500 0.3353 0.00586 0.00149 -0.1130 0.7490 0.6123
-1.250 0.3654 0.00587 0.00153 -0.1134 0.7417 0.6347
-1.000 0.3950 0.00591 0.00154 -0.1137 0.7327 0.6441
-0.750 0.4246 0.00594 0.00154 -0.1141 0.7224 0.6478
-0.500 0.4541 0.00599 0.00156 -0.1144 0.7124 0.6516
0.000 0.5119 0.00617 0.00159 -0.1147 0.6731 0.6603
0.250 0.5399 0.00636 0.00162 -0.1147 0.6390 0.6635
0.500 0.5675 0.00657 0.00169 -0.1147 0.5977 0.6668
0.750 0.5943 0.00690 0.00182 -0.1146 0.5499 0.6714
1.000 0.6202 0.00734 0.00200 -0.1143 0.4905 0.6765
1.250 0.6453 0.00788 0.00222 -0.1140 0.4196 0.6807
1.500 0.6715 0.00827 0.00242 -0.1138 0.3716 0.6846
1.750 0.6972 0.00870 0.00262 -0.1136 0.3180 0.6880
2.000 0.7232 0.00909 0.00282 -0.1134 0.2768 0.6906
2.250 0.7499 0.00940 0.00299 -0.1133 0.2470 0.6930
2.500 0.7763 0.00972 0.00317 -0.1132 0.2170 0.6952
2.750 0.8024 0.01006 0.00337 -0.1130 0.1864 0.6976
3.000 0.8290 0.01034 0.00357 -0.1128 0.1666 0.7001
3.250 0.8559 0.01058 0.00375 -0.1127 0.1535 0.7027
3.500 0.8827 0.01082 0.00394 -0.1126 0.1408 0.7054
3.750 0.9093 0.01107 0.00414 -0.1125 0.1275 0.7082
4.000 0.9359 0.01131 0.00433 -0.1123 0.1170 0.7108
4.250 0.9623 0.01156 0.00453 -0.1122 0.1081 0.7133
4.500 0.9885 0.01181 0.00476 -0.1120 0.1000 0.7160
4.750 1.0149 0.01204 0.00498 -0.1118 0.0943 0.7189
5.000 1.0410 0.01228 0.00521 -0.1115 0.0888 0.7218
5.250 1.0668 0.01255 0.00545 -0.1112 0.0834 0.7246
5.500 1.0929 0.01277 0.00568 -0.1110 0.0802 0.7274
5.750 1.1184 0.01304 0.00593 -0.1107 0.0760 0.7301
6.000 1.1436 0.01332 0.00621 -0.1103 0.0717 0.7331
6.250 1.1691 0.01355 0.00646 -0.1100 0.0692 0.7364
6.500 1.1938 0.01385 0.00675 -0.1095 0.0652 0.7397
6.750 1.2181 0.01417 0.00705 -0.1090 0.0612 0.7429
7.250 1.2668 0.01474 0.00765 -0.1079 0.0560 0.7488
7.500 1.2901 0.01509 0.00799 -0.1072 0.0528 0.7521
7.750 1.3138 0.01539 0.00833 -0.1066 0.0509 0.7555
8.000 1.3370 0.01571 0.00867 -0.1059 0.0488 0.7590
8.500 1.3809 0.01648 0.00945 -0.1041 0.0438 0.7658
8.750 1.4029 0.01682 0.00983 -0.1032 0.0423 0.7698
9.000 1.4237 0.01720 0.01024 -0.1021 0.0402 0.7741
9.250 1.4431 0.01765 0.01069 -0.1007 0.0379 0.7780
9.500 1.4621 0.01807 0.01115 -0.0993 0.0363 0.7821
9.750 1.4785 0.01848 0.01161 -0.0974 0.0349 0.7865
10.000 1.4955 0.01896 0.01211 -0.0956 0.0334 0.7909
10.250 1.5122 0.01951 0.01268 -0.0939 0.0317 0.7949
10.500 1.5291 0.02005 0.01328 -0.0923 0.0305 0.7992
10.750 1.5463 0.02059 0.01387 -0.0908 0.0294 0.8039
11.000 1.5628 0.02118 0.01450 -0.0892 0.0283 0.8085
11.250 1.5784 0.02185 0.01519 -0.0876 0.0269 0.8129
11.500 1.5933 0.02257 0.01596 -0.0859 0.0256 0.8179
11.750 1.6091 0.02323 0.01668 -0.0843 0.0247 0.8231
12.000 1.6240 0.02395 0.01747 -0.0828 0.0237 0.8282
12.250 1.6382 0.02475 0.01831 -0.0812 0.0227 0.8344
12.500 1.6513 0.02563 0.01924 -0.0795 0.0218 0.8409
12.750 1.6643 0.02652 0.02020 -0.0778 0.0211 0.8480
13.000 1.6779 0.02739 0.02115 -0.0763 0.0206 0.8561
13.250 1.6905 0.02832 0.02217 -0.0747 0.0201 0.8648
13.500 1.7024 0.02932 0.02324 -0.0731 0.0195 0.8745
13.750 1.7133 0.03039 0.02439 -0.0715 0.0189 0.8862
14.000 1.7230 0.03154 0.02563 -0.0698 0.0183 0.9018
14.250 1.7269 0.03261 0.02686 -0.0670 0.0177 1.0000
14.500 1.7367 0.03390 0.02821 -0.0656 0.0173 1.0000
14.750 1.7463 0.03522 0.02961 -0.0642 0.0169 1.0000
15.000 1.7550 0.03665 0.03110 -0.0629 0.0166 1.0000
15.250 1.7630 0.03816 0.03269 -0.0616 0.0163 1.0000
15.500 1.7698 0.03979 0.03439 -0.0603 0.0159 1.0000
15.750 1.7755 0.04155 0.03621 -0.0590 0.0156 1.0000
16.000 1.7805 0.04343 0.03817 -0.0578 0.0153 1.0000
16.250 1.7843 0.04547 0.04028 -0.0567 0.0150 1.0000
16.500 1.7870 0.04768 0.04257 -0.0556 0.0146 1.0000
16.750 1.7881 0.05012 0.04509 -0.0546 0.0143 1.0000
17.000 1.7895 0.05262 0.04769 -0.0539 0.0141 1.0000
17.250 1.7913 0.05514 0.05030 -0.0533 0.0139 1.0000
17.500 1.7921 0.05786 0.05312 -0.0529 0.0137 1.0000
17.750 1.7913 0.06084 0.05620 -0.0526 0.0134 1.0000
18.000 1.7889 0.06408 0.05954 -0.0524 0.0131 1.0000
18.250 1.7851 0.06764 0.06320 -0.0526 0.0129 1.0000
18.500 1.7794 0.07158 0.06725 -0.0530 0.0127 1.0000
18.750 1.7721 0.07586 0.07164 -0.0536 0.0124 1.0000
19.000 1.7623 0.08063 0.07653 -0.0547 0.0122 1.0000
19.250 1.7500 0.08592 0.08194 -0.0561 0.0120 1.0000
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