LOCKHEED-GEORGIA SUPERCRITICAL AIRFOIL (lg10sc-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED-GEORGIA SUPERCRITICAL AIRFOIL (lg10sc-il) Reynolds number: 50,000 Max Cl/Cd: 25.9 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lg10sc-il-50000.txt Download as CSV file: xf-lg10sc-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED-GEORGIA SUPERCRITICAL AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5559 0.13671 0.12960 0.0101 1.0000 0.2062
-10.500 -0.5353 0.13126 0.12415 0.0114 1.0000 0.2141
-10.250 -0.5573 0.13038 0.12337 0.0082 1.0000 0.2220
-10.000 -0.5306 0.12467 0.11764 0.0102 1.0000 0.2334
-9.750 -0.5268 0.12095 0.11398 0.0099 1.0000 0.2424
-9.500 -0.5502 0.11991 0.11306 0.0073 1.0000 0.2526
-9.250 -0.5324 0.11532 0.10848 0.0087 1.0000 0.2669
-9.000 -0.5201 0.11126 0.10443 0.0096 1.0000 0.2806
-8.750 -0.5151 0.10784 0.10106 0.0101 1.0000 0.2956
-8.500 -0.5186 0.10510 0.09839 0.0103 1.0000 0.3126
-8.250 -0.5133 0.10156 0.09492 0.0112 1.0000 0.3309
-8.000 -0.4959 0.09804 0.09141 0.0133 1.0000 0.3560
-7.750 -0.4891 0.09475 0.08818 0.0148 1.0000 0.3794
-7.500 -0.5003 0.09310 0.08663 0.0165 1.0000 0.4056
-7.250 -0.4690 0.08848 0.08197 0.0184 1.0000 0.4314
-7.000 -0.4588 0.08524 0.07878 0.0202 1.0000 0.4579
-5.750 -0.5460 0.05027 0.04203 -0.0163 1.0000 0.1460
-5.500 -0.5308 0.04587 0.03723 -0.0149 1.0000 0.1334
-5.250 -0.5124 0.04252 0.03362 -0.0134 1.0000 0.1264
-5.000 -0.4941 0.03976 0.02989 -0.0110 1.0000 0.1166
-4.750 -0.4735 0.03666 0.02662 -0.0096 1.0000 0.1143
-4.500 -0.4518 0.03410 0.02374 -0.0081 1.0000 0.1129
-4.250 -0.4291 0.03203 0.02124 -0.0065 1.0000 0.1147
-4.000 -0.4052 0.03009 0.01894 -0.0051 1.0000 0.1177
-3.750 -0.3794 0.02799 0.01682 -0.0041 1.0000 0.1218
-3.500 -0.3524 0.02640 0.01509 -0.0030 1.0000 0.1291
-3.250 -0.0995 0.02076 0.01235 -0.0284 1.0000 1.0000
-3.000 -0.0863 0.02025 0.01158 -0.0271 1.0000 1.0000
-2.750 -0.0737 0.01982 0.01094 -0.0256 1.0000 1.0000
-2.500 -0.0622 0.01946 0.01041 -0.0238 1.0000 1.0000
-2.250 -0.0521 0.01917 0.00998 -0.0216 1.0000 1.0000
-2.000 -0.0432 0.01895 0.00962 -0.0191 1.0000 1.0000
-1.750 -0.0354 0.01878 0.00934 -0.0164 1.0000 1.0000
-1.500 -0.0283 0.01866 0.00912 -0.0134 1.0000 1.0000
-1.250 -0.0220 0.01860 0.00897 -0.0103 1.0000 1.0000
-1.000 -0.0161 0.01858 0.00886 -0.0072 1.0000 1.0000
-0.750 -0.0099 0.01862 0.00879 -0.0040 1.0000 1.0000
-0.500 -0.0031 0.01870 0.00879 -0.0010 1.0000 1.0000
-0.250 0.0045 0.01884 0.00884 0.0017 1.0000 1.0000
0.000 0.0129 0.01903 0.00896 0.0043 1.0000 1.0000
0.250 0.0226 0.01928 0.00914 0.0065 1.0000 1.0000
0.500 0.0336 0.01961 0.00939 0.0084 1.0000 1.0000
0.750 0.0455 0.02001 0.00975 0.0099 1.0000 1.0000
1.000 0.0578 0.02050 0.01021 0.0111 1.0000 1.0000
1.250 0.0703 0.02112 0.01081 0.0120 1.0000 1.0000
1.500 0.1421 0.02209 0.01183 0.0018 0.9763 1.0000
1.750 0.2444 0.02247 0.01238 -0.0125 0.9341 1.0000
2.000 0.3572 0.02170 0.01189 -0.0266 0.8851 1.0000
2.250 0.4273 0.02052 0.01088 -0.0309 0.8244 1.0000
2.500 0.4643 0.01981 0.01006 -0.0290 0.7523 1.0000
2.750 0.4886 0.01974 0.00965 -0.0255 0.6792 1.0000
3.000 0.5094 0.02015 0.00966 -0.0226 0.6160 1.0000
3.250 0.5316 0.02080 0.00996 -0.0206 0.5662 1.0000
3.500 0.5544 0.02154 0.01041 -0.0191 0.5273 1.0000
3.750 0.5773 0.02235 0.01106 -0.0178 0.4957 1.0000
4.000 0.6006 0.02319 0.01171 -0.0167 0.4696 1.0000
4.250 0.6231 0.02412 0.01262 -0.0157 0.4464 1.0000
4.500 0.6462 0.02507 0.01349 -0.0147 0.4267 1.0000
4.750 0.6693 0.02607 0.01446 -0.0138 0.4093 1.0000
5.000 0.6921 0.02717 0.01558 -0.0129 0.3940 1.0000
5.250 0.7143 0.02833 0.01680 -0.0120 0.3794 1.0000
5.500 0.7359 0.02959 0.01816 -0.0111 0.3659 1.0000
5.750 0.7572 0.03105 0.01980 -0.0103 0.3548 1.0000
6.000 0.7794 0.03244 0.02123 -0.0095 0.3443 1.0000
6.250 0.7999 0.03391 0.02285 -0.0085 0.3334 1.0000
6.500 0.8175 0.03585 0.02509 -0.0076 0.3245 1.0000
6.750 0.8397 0.03746 0.02678 -0.0068 0.3167 1.0000
7.000 0.8523 0.03992 0.02967 -0.0057 0.3087 1.0000
7.250 0.8762 0.04139 0.03107 -0.0049 0.3004 1.0000
7.500 0.8810 0.04483 0.03509 -0.0037 0.2950 1.0000
7.750 0.8926 0.04769 0.03826 -0.0028 0.2894 1.0000
8.000 0.9064 0.05037 0.04109 -0.0019 0.2835 1.0000
8.250 0.8987 0.05518 0.04634 -0.0010 0.2794 1.0000
8.500 0.8890 0.06043 0.05188 -0.0008 0.2771 1.0000
8.750 0.8605 0.06804 0.05970 -0.0019 0.2796 1.0000
9.000 0.8384 0.07537 0.06711 -0.0039 0.2830 1.0000
9.250 0.8291 0.08151 0.07330 -0.0054 0.2855 1.0000
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Polar data table (+)
Polar graphs
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