LOCKHEED-GEORGIA SUPERCRITICAL AIRFOIL (lg10sc-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED-GEORGIA SUPERCRITICAL AIRFOIL (lg10sc-il) Reynolds number: 50,000 Max Cl/Cd: 27.83 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lg10sc-il-50000-n5.txt Download as CSV file: xf-lg10sc-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5443 0.10735 0.10016 -0.0085 1.0000 0.0579
-9.500 -0.5441 0.10257 0.09543 -0.0105 1.0000 0.0552
-9.250 -0.5658 0.09260 0.08550 -0.0222 1.0000 0.0494
-9.000 -0.5627 0.08878 0.08172 -0.0225 1.0000 0.0485
-8.750 -0.5662 0.08451 0.07748 -0.0239 1.0000 0.0477
-8.500 -0.5734 0.08032 0.07329 -0.0247 1.0000 0.0469
-8.250 -0.5798 0.07599 0.06891 -0.0255 1.0000 0.0461
-8.000 -0.5852 0.07164 0.06447 -0.0260 1.0000 0.0452
-7.750 -0.5888 0.06734 0.05999 -0.0259 1.0000 0.0444
-7.500 -0.5905 0.06308 0.05552 -0.0254 1.0000 0.0435
-7.250 -0.5899 0.05890 0.05106 -0.0244 1.0000 0.0427
-7.000 -0.5864 0.05489 0.04670 -0.0230 1.0000 0.0420
-6.750 -0.5794 0.05130 0.04275 -0.0214 1.0000 0.0417
-6.500 -0.5692 0.04830 0.03947 -0.0198 1.0000 0.0423
-6.250 -0.5572 0.04557 0.03644 -0.0181 1.0000 0.0433
-6.000 -0.5437 0.04294 0.03347 -0.0163 1.0000 0.0445
-5.750 -0.5285 0.04036 0.03050 -0.0145 1.0000 0.0455
-5.500 -0.5113 0.03785 0.02760 -0.0128 1.0000 0.0462
-5.250 -0.4920 0.03549 0.02484 -0.0111 1.0000 0.0468
-5.000 -0.4710 0.03334 0.02232 -0.0096 1.0000 0.0476
-4.750 -0.4485 0.03151 0.02009 -0.0081 1.0000 0.0492
-4.500 -0.4267 0.02976 0.01831 -0.0070 1.0000 0.0522
-4.250 -0.4038 0.02837 0.01682 -0.0059 1.0000 0.0559
-4.000 -0.3793 0.02701 0.01527 -0.0046 1.0000 0.0591
-3.750 -0.3559 0.02575 0.01394 -0.0033 1.0000 0.0635
-3.500 -0.3339 0.02475 0.01288 -0.0021 1.0000 0.0711
-3.250 -0.3124 0.02371 0.01180 -0.0008 1.0000 0.0798
-3.000 -0.2914 0.02272 0.01079 0.0004 1.0000 0.0960
-2.750 -0.2720 0.02150 0.00981 0.0018 1.0000 0.1333
-2.500 -0.2643 0.01851 0.00908 0.0046 1.0000 0.4903
-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 0.0115 0.01884 0.00884 0.0004 0.9976 1.0000
0.000 0.0741 0.01897 0.00883 -0.0069 0.9768 1.0000
0.250 0.1323 0.01899 0.00876 -0.0132 0.9554 1.0000
0.500 0.1860 0.01890 0.00862 -0.0182 0.9325 1.0000
0.750 0.2312 0.01874 0.00845 -0.0214 0.9064 1.0000
1.000 0.2710 0.01857 0.00826 -0.0233 0.8769 1.0000
1.250 0.3060 0.01840 0.00807 -0.0240 0.8427 1.0000
1.500 0.3382 0.01825 0.00786 -0.0240 0.8042 1.0000
1.750 0.3666 0.01815 0.00767 -0.0231 0.7592 1.0000
2.000 0.3920 0.01814 0.00751 -0.0217 0.7071 1.0000
2.250 0.4155 0.01824 0.00737 -0.0199 0.6493 1.0000
2.500 0.4369 0.01850 0.00731 -0.0179 0.5888 1.0000
2.750 0.4570 0.01890 0.00739 -0.0159 0.5322 1.0000
3.000 0.4767 0.01941 0.00755 -0.0142 0.4845 1.0000
3.250 0.4967 0.01995 0.00783 -0.0126 0.4449 1.0000
3.500 0.5174 0.02051 0.00818 -0.0113 0.4138 1.0000
3.750 0.5393 0.02110 0.00861 -0.0103 0.3880 1.0000
4.000 0.5616 0.02168 0.00907 -0.0094 0.3660 1.0000
4.250 0.5845 0.02228 0.00955 -0.0086 0.3477 1.0000
4.500 0.6078 0.02289 0.01007 -0.0078 0.3313 1.0000
4.750 0.6314 0.02351 0.01068 -0.0072 0.3164 1.0000
5.000 0.6551 0.02414 0.01132 -0.0065 0.3028 1.0000
5.250 0.6788 0.02479 0.01200 -0.0058 0.2903 1.0000
5.500 0.7025 0.02549 0.01272 -0.0052 0.2793 1.0000
5.750 0.7263 0.02621 0.01341 -0.0046 0.2698 1.0000
6.000 0.7495 0.02696 0.01431 -0.0039 0.2592 1.0000
6.250 0.7730 0.02778 0.01519 -0.0033 0.2505 1.0000
6.500 0.7964 0.02862 0.01613 -0.0027 0.2424 1.0000
6.750 0.8192 0.02954 0.01720 -0.0020 0.2342 1.0000
7.000 0.8420 0.03042 0.01814 -0.0014 0.2267 1.0000
7.250 0.8641 0.03151 0.01945 -0.0007 0.2197 1.0000
7.500 0.8862 0.03255 0.02066 0.0000 0.2130 1.0000
7.750 0.9076 0.03369 0.02195 0.0007 0.2066 1.0000
8.000 0.9277 0.03488 0.02340 0.0015 0.1996 1.0000
8.250 0.9505 0.03596 0.02449 0.0021 0.1948 1.0000
8.500 0.9665 0.03769 0.02671 0.0033 0.1882 1.0000
8.750 0.9868 0.03881 0.02794 0.0041 0.1824 1.0000
9.000 1.0027 0.04051 0.02996 0.0052 0.1767 1.0000
9.250 1.0173 0.04231 0.03209 0.0063 0.1710 1.0000
9.500 1.0394 0.04321 0.03297 0.0070 0.1660 1.0000
9.750 1.0431 0.04589 0.03626 0.0088 0.1595 1.0000
10.000 1.0596 0.04709 0.03758 0.0099 0.1538 1.0000
10.250 1.0643 0.04944 0.04028 0.0116 0.1479 1.0000
10.500 1.0719 0.05111 0.04220 0.0131 0.1414 1.0000
10.750 1.0803 0.05273 0.04398 0.0145 0.1358 1.0000
11.000 1.0682 0.05627 0.04794 0.0166 0.1309 1.0000
11.250 1.0952 0.05566 0.04720 0.0175 0.1244 1.0000
11.500 1.0631 0.06081 0.05279 0.0199 0.1222 1.0000
11.750 1.0248 0.06680 0.05903 0.0207 0.1213 1.0000
12.000 0.9725 0.07640 0.06873 0.0168 0.1220 1.0000
12.250 0.8940 0.09508 0.08734 0.0045 0.1230 1.0000
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Polar data table (+)
Polar graphs
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