NASA LRN 1015 (NASA TM 102840) (lrn1015-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA LRN 1015 (NASA TM 102840) (lrn1015-il) Reynolds number: 500,000 Max Cl/Cd: 112.89 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lrn1015-il-500000-n5.txt Download as CSV file: xf-lrn1015-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA LRN 1015 (NASA TM 102840)
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 -0.0847 0.08550 0.08170 -0.1066 0.7381 0.0104
-10.500 -0.0841 0.08170 0.07793 -0.1083 0.7368 0.0101
-10.250 -0.0880 0.07704 0.07329 -0.1104 0.7354 0.0103
-10.000 -0.0923 0.07247 0.06875 -0.1126 0.7340 0.0102
-9.750 -0.1010 0.06714 0.06345 -0.1155 0.7325 0.0098
-9.500 -0.1165 0.06021 0.05655 -0.1205 0.7309 0.0099
-9.250 -0.1519 0.05202 0.04828 -0.1258 0.7289 0.0098
-9.000 -0.1847 0.04742 0.04358 -0.1239 0.7269 0.0096
-8.750 -0.2008 0.04317 0.03917 -0.1222 0.7250 0.0096
-8.500 -0.2117 0.03873 0.03450 -0.1200 0.7232 0.0097
-8.250 -0.2165 0.03443 0.02990 -0.1177 0.7215 0.0098
-8.000 -0.2168 0.03017 0.02527 -0.1153 0.7199 0.0099
-7.750 -0.2111 0.02645 0.02113 -0.1130 0.7184 0.0102
-7.500 -0.2008 0.02302 0.01720 -0.1109 0.7169 0.0107
-7.250 -0.1837 0.02075 0.01451 -0.1095 0.7155 0.0110
-7.000 -0.1628 0.01917 0.01259 -0.1085 0.7141 0.0112
-6.750 -0.1401 0.01805 0.01130 -0.1079 0.7128 0.0114
-6.500 -0.1161 0.01728 0.01045 -0.1075 0.7115 0.0116
-6.250 -0.0914 0.01670 0.00981 -0.1071 0.7101 0.0118
-6.000 -0.0663 0.01613 0.00919 -0.1067 0.7086 0.0121
-5.750 -0.0411 0.01556 0.00854 -0.1063 0.7070 0.0125
-5.500 -0.0158 0.01500 0.00791 -0.1059 0.7053 0.0128
-5.250 0.0095 0.01446 0.00730 -0.1055 0.7037 0.0132
-5.000 0.0349 0.01397 0.00674 -0.1051 0.7022 0.0135
-4.750 0.0610 0.01362 0.00632 -0.1048 0.7009 0.0140
-4.500 0.0862 0.01317 0.00587 -0.1045 0.6996 0.0146
-4.250 0.1124 0.01287 0.00555 -0.1043 0.6983 0.0152
-4.000 0.1386 0.01255 0.00519 -0.1040 0.6970 0.0158
-3.750 0.1645 0.01225 0.00488 -0.1037 0.6953 0.0164
-3.500 0.1907 0.01199 0.00460 -0.1035 0.6936 0.0170
-3.250 0.2168 0.01170 0.00431 -0.1032 0.6920 0.0178
-3.000 0.2435 0.01148 0.00411 -0.1031 0.6903 0.0188
-2.750 0.2705 0.01130 0.00391 -0.1030 0.6886 0.0201
-2.500 0.2975 0.01111 0.00372 -0.1029 0.6869 0.0222
-2.250 0.3250 0.01096 0.00355 -0.1028 0.6854 0.0247
-2.000 0.3524 0.01080 0.00339 -0.1028 0.6840 0.0282
-1.750 0.3800 0.01066 0.00325 -0.1028 0.6825 0.0357
-1.500 0.4060 0.01030 0.00312 -0.1027 0.6809 0.1055
-1.250 0.4283 0.00953 0.00303 -0.1023 0.6790 0.3141
-1.000 0.4476 0.00856 0.00299 -0.1013 0.6770 0.5906
-0.750 0.4696 0.00828 0.00319 -0.0999 0.6749 0.7334
-0.500 0.4957 0.00833 0.00331 -0.0993 0.6729 0.7743
-0.250 0.5228 0.00839 0.00337 -0.0990 0.6710 0.7959
0.000 0.5507 0.00841 0.00337 -0.0990 0.6691 0.8036
0.250 0.5792 0.00844 0.00335 -0.0991 0.6673 0.8102
0.500 0.6073 0.00849 0.00337 -0.0992 0.6652 0.8163
0.750 0.6343 0.00852 0.00343 -0.0990 0.6625 0.8212
1.000 0.6617 0.00855 0.00346 -0.0989 0.6593 0.8265
1.250 0.6895 0.00855 0.00342 -0.0989 0.6554 0.8315
1.500 0.7174 0.00851 0.00334 -0.0989 0.6510 0.8353
1.750 0.7434 0.00852 0.00339 -0.0986 0.6449 0.8393
2.000 0.7706 0.00852 0.00337 -0.0985 0.6397 0.8434
2.250 0.7982 0.00854 0.00335 -0.0985 0.6354 0.8473
2.500 0.8247 0.00857 0.00342 -0.0983 0.6296 0.8506
2.750 0.8510 0.00858 0.00342 -0.0980 0.6233 0.8540
3.000 0.8773 0.00862 0.00347 -0.0978 0.6171 0.8577
3.250 0.9036 0.00866 0.00352 -0.0976 0.6103 0.8615
3.500 0.9297 0.00872 0.00356 -0.0974 0.6034 0.8652
3.750 0.9547 0.00877 0.00363 -0.0969 0.5944 0.8685
4.000 0.9794 0.00884 0.00371 -0.0964 0.5844 0.8722
4.250 1.0031 0.00895 0.00378 -0.0957 0.5717 0.8762
4.500 1.0259 0.00909 0.00388 -0.0949 0.5563 0.8802
4.750 1.0465 0.00927 0.00402 -0.0936 0.5380 0.8841
5.000 1.0644 0.00953 0.00421 -0.0919 0.5166 0.8888
5.250 1.0787 0.00990 0.00447 -0.0895 0.4896 0.8943
5.500 1.0881 0.01037 0.00482 -0.0863 0.4605 0.9006
5.750 1.0921 0.01089 0.00524 -0.0820 0.4318 0.9099
6.000 1.0896 0.01148 0.00574 -0.0766 0.4039 0.9236
6.250 1.0936 0.01227 0.00643 -0.0730 0.3735 0.9484
6.750 1.1069 0.01437 0.00830 -0.0685 0.3201 1.0000
7.000 1.1130 0.01542 0.00927 -0.0662 0.3009 1.0000
7.250 1.1205 0.01646 0.01023 -0.0641 0.2833 1.0000
7.500 1.1300 0.01742 0.01112 -0.0623 0.2689 1.0000
7.750 1.1385 0.01844 0.01207 -0.0604 0.2530 1.0000
8.000 1.1477 0.01945 0.01301 -0.0586 0.2380 1.0000
8.250 1.1580 0.02041 0.01392 -0.0570 0.2253 1.0000
8.500 1.1686 0.02137 0.01483 -0.0555 0.2142 1.0000
8.750 1.1802 0.02229 0.01572 -0.0541 0.2032 1.0000
9.000 1.1921 0.02321 0.01661 -0.0528 0.1934 1.0000
9.250 1.2026 0.02422 0.01758 -0.0514 0.1837 1.0000
9.500 1.2148 0.02515 0.01849 -0.0502 0.1744 1.0000
9.750 1.2260 0.02615 0.01946 -0.0489 0.1654 1.0000
10.000 1.2373 0.02716 0.02046 -0.0477 0.1575 1.0000
10.250 1.2499 0.02810 0.02140 -0.0466 0.1510 1.0000
10.500 1.2615 0.02912 0.02242 -0.0455 0.1441 1.0000
10.750 1.2734 0.03016 0.02345 -0.0445 0.1382 1.0000
11.000 1.2858 0.03119 0.02449 -0.0436 0.1321 1.0000
11.250 1.2970 0.03233 0.02563 -0.0426 0.1265 1.0000
11.500 1.3096 0.03339 0.02672 -0.0418 0.1215 1.0000
11.750 1.3206 0.03459 0.02791 -0.0409 0.1158 1.0000
12.000 1.3323 0.03575 0.02910 -0.0401 0.1111 1.0000
12.250 1.3436 0.03698 0.03034 -0.0393 0.1063 1.0000
12.500 1.3540 0.03829 0.03166 -0.0384 0.1020 1.0000
12.750 1.3658 0.03951 0.03292 -0.0378 0.0987 1.0000
13.000 1.3771 0.04079 0.03425 -0.0371 0.0956 1.0000
13.250 1.3873 0.04218 0.03566 -0.0364 0.0921 1.0000
13.500 1.3962 0.04372 0.03722 -0.0357 0.0886 1.0000
13.750 1.4073 0.04507 0.03863 -0.0352 0.0860 1.0000
14.000 1.4176 0.04652 0.04013 -0.0346 0.0834 1.0000
14.250 1.4250 0.04824 0.04186 -0.0340 0.0796 1.0000
14.500 1.4337 0.04988 0.04354 -0.0335 0.0764 1.0000
14.750 1.4429 0.05150 0.04521 -0.0331 0.0733 1.0000
15.000 1.4501 0.05333 0.04707 -0.0326 0.0703 1.0000
15.250 1.4564 0.05529 0.04905 -0.0322 0.0675 1.0000
15.500 1.4647 0.05707 0.05092 -0.0319 0.0662 1.0000
15.750 1.4733 0.05884 0.05277 -0.0317 0.0643 1.0000
16.000 1.4800 0.06084 0.05483 -0.0314 0.0622 1.0000
16.250 1.4854 0.06302 0.05704 -0.0313 0.0599 1.0000
16.500 1.4902 0.06530 0.05939 -0.0311 0.0585 1.0000
16.750 1.4962 0.06746 0.06162 -0.0311 0.0563 1.0000
17.000 1.5020 0.06968 0.06392 -0.0311 0.0541 1.0000
17.250 1.5065 0.07208 0.06639 -0.0312 0.0523 1.0000
17.500 1.5090 0.07478 0.06915 -0.0314 0.0505 1.0000
17.750 1.5113 0.07753 0.07197 -0.0317 0.0487 1.0000
18.000 1.5156 0.08008 0.07462 -0.0320 0.0470 1.0000
18.250 1.5178 0.08293 0.07753 -0.0324 0.0444 1.0000
18.500 1.5165 0.08627 0.08092 -0.0330 0.0418 1.0000
18.750 1.5173 0.08940 0.08414 -0.0337 0.0395 1.0000
19.000 1.5159 0.09287 0.08767 -0.0345 0.0363 1.0000
19.250 1.5129 0.09661 0.09147 -0.0354 0.0331 1.0000
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