LOCKHEED-GEORGIA SUPERCRITICAL AIRFOIL (lg10sc-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED-GEORGIA SUPERCRITICAL AIRFOIL (lg10sc-il) Reynolds number: 1,000,000 Max Cl/Cd: 90.76 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lg10sc-il-1000000-n5.txt Download as CSV file: xf-lg10sc-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.6000 0.10911 0.10742 0.0035 1.0000 0.0052
-10.750 -0.6028 0.10378 0.10210 0.0010 1.0000 0.0052
-10.250 -0.9084 0.03095 0.02778 -0.0251 1.0000 0.0048
-10.000 -0.9078 0.02705 0.02346 -0.0224 1.0000 0.0049
-9.750 -0.8967 0.02482 0.02096 -0.0205 1.0000 0.0050
-9.500 -0.8828 0.02307 0.01898 -0.0187 1.0000 0.0050
-9.250 -0.8678 0.02152 0.01722 -0.0168 1.0000 0.0050
-9.000 -0.8517 0.02024 0.01576 -0.0150 1.0000 0.0051
-8.750 -0.8345 0.01915 0.01453 -0.0133 1.0000 0.0051
-8.500 -0.8169 0.01822 0.01347 -0.0115 1.0000 0.0052
-8.250 -0.7938 0.01733 0.01246 -0.0109 0.9993 0.0053
-8.000 -0.7655 0.01646 0.01146 -0.0114 0.9976 0.0054
-7.750 -0.7363 0.01565 0.01056 -0.0120 0.9960 0.0055
-7.500 -0.7063 0.01491 0.00972 -0.0127 0.9946 0.0056
-7.250 -0.6773 0.01422 0.00895 -0.0132 0.9923 0.0057
-7.000 -0.6476 0.01359 0.00824 -0.0137 0.9899 0.0059
-6.750 -0.6175 0.01300 0.00757 -0.0144 0.9875 0.0061
-6.500 -0.5870 0.01246 0.00696 -0.0151 0.9852 0.0063
-6.250 -0.5585 0.01199 0.00644 -0.0153 0.9812 0.0065
-6.000 -0.5296 0.01157 0.00597 -0.0156 0.9767 0.0067
-5.750 -0.4996 0.01114 0.00550 -0.0161 0.9730 0.0068
-5.500 -0.4731 0.01064 0.00496 -0.0159 0.9666 0.0072
-5.250 -0.4449 0.01031 0.00462 -0.0159 0.9605 0.0075
-5.000 -0.4178 0.01003 0.00430 -0.0157 0.9528 0.0078
-4.750 -0.3910 0.00975 0.00400 -0.0154 0.9442 0.0082
-4.500 -0.3648 0.00949 0.00371 -0.0149 0.9334 0.0086
-4.250 -0.3395 0.00928 0.00342 -0.0142 0.9152 0.0090
-4.000 -0.3150 0.00911 0.00313 -0.0132 0.8843 0.0095
-3.750 -0.2900 0.00895 0.00287 -0.0124 0.8528 0.0105
-3.500 -0.2634 0.00881 0.00266 -0.0120 0.8316 0.0114
-3.250 -0.2367 0.00870 0.00246 -0.0117 0.8097 0.0122
-3.000 -0.2101 0.00856 0.00224 -0.0113 0.7871 0.0137
-2.500 -0.1565 0.00842 0.00192 -0.0107 0.7327 0.0181
-2.250 -0.1297 0.00835 0.00178 -0.0104 0.7029 0.0246
-2.000 -0.1031 0.00830 0.00166 -0.0101 0.6678 0.0384
-1.750 -0.0766 0.00821 0.00155 -0.0098 0.6326 0.0628
-1.500 -0.0506 0.00808 0.00145 -0.0096 0.5935 0.1112
-1.250 -0.0250 0.00793 0.00135 -0.0093 0.5497 0.1778
-1.000 -0.0002 0.00761 0.00126 -0.0089 0.5086 0.2881
-0.750 0.0227 0.00705 0.00115 -0.0083 0.4674 0.4700
-0.500 0.0459 0.00666 0.00111 -0.0076 0.4243 0.6169
-0.250 0.0694 0.00641 0.00112 -0.0068 0.3895 0.7299
0.000 0.0944 0.00635 0.00116 -0.0061 0.3606 0.7931
0.250 0.1202 0.00639 0.00121 -0.0056 0.3332 0.8311
0.500 0.1467 0.00647 0.00126 -0.0052 0.3084 0.8555
0.750 0.1736 0.00655 0.00130 -0.0049 0.2899 0.8732
1.000 0.2007 0.00665 0.00135 -0.0046 0.2723 0.8871
1.250 0.2279 0.00677 0.00140 -0.0044 0.2563 0.8989
1.500 0.2551 0.00685 0.00146 -0.0042 0.2448 0.9100
1.750 0.2824 0.00695 0.00152 -0.0040 0.2344 0.9197
2.000 0.3096 0.00707 0.00158 -0.0038 0.2232 0.9292
2.250 0.3369 0.00717 0.00166 -0.0036 0.2143 0.9378
2.500 0.3645 0.00728 0.00173 -0.0035 0.2071 0.9456
2.750 0.3924 0.00739 0.00181 -0.0034 0.1993 0.9526
3.000 0.4203 0.00751 0.00190 -0.0034 0.1916 0.9595
3.250 0.4496 0.00764 0.00199 -0.0037 0.1837 0.9648
3.500 0.4781 0.00776 0.00208 -0.0039 0.1780 0.9705
3.750 0.5082 0.00789 0.00218 -0.0044 0.1721 0.9744
4.000 0.5390 0.00804 0.00230 -0.0051 0.1653 0.9779
4.250 0.5689 0.00818 0.00241 -0.0056 0.1594 0.9820
4.500 0.5991 0.00834 0.00253 -0.0062 0.1532 0.9853
4.750 0.6314 0.00848 0.00267 -0.0073 0.1489 0.9873
5.000 0.6635 0.00864 0.00280 -0.0083 0.1437 0.9893
5.250 0.6948 0.00882 0.00295 -0.0092 0.1376 0.9913
5.500 0.7258 0.00897 0.00311 -0.0100 0.1333 0.9935
5.750 0.7570 0.00915 0.00327 -0.0109 0.1285 0.9950
6.000 0.7888 0.00934 0.00344 -0.0119 0.1239 0.9963
6.250 0.8204 0.00950 0.00362 -0.0129 0.1207 0.9977
6.500 0.8515 0.00971 0.00381 -0.0138 0.1160 0.9991
6.750 0.8801 0.00993 0.00401 -0.0142 0.1103 1.0000
7.000 0.9034 0.01011 0.00420 -0.0133 0.1057 1.0000
7.250 0.9265 0.01034 0.00440 -0.0125 0.1006 1.0000
7.500 0.9502 0.01054 0.00461 -0.0118 0.0973 1.0000
7.750 0.9739 0.01075 0.00484 -0.0111 0.0928 1.0000
8.000 0.9971 0.01103 0.00509 -0.0103 0.0869 1.0000
8.250 1.0211 0.01125 0.00532 -0.0097 0.0835 1.0000
8.500 1.0449 0.01152 0.00559 -0.0091 0.0786 1.0000
8.750 1.0689 0.01181 0.00588 -0.0085 0.0743 1.0000
9.000 1.0930 0.01210 0.00618 -0.0080 0.0691 1.0000
9.250 1.1167 0.01246 0.00651 -0.0074 0.0630 1.0000
9.500 1.1400 0.01287 0.00690 -0.0068 0.0556 1.0000
9.750 1.1627 0.01335 0.00735 -0.0062 0.0466 1.0000
10.000 1.1846 0.01393 0.00787 -0.0055 0.0374 1.0000
10.250 1.2071 0.01444 0.00838 -0.0048 0.0323 1.0000
10.500 1.2297 0.01494 0.00889 -0.0042 0.0285 1.0000
10.750 1.2516 0.01548 0.00945 -0.0035 0.0251 1.0000
11.000 1.2740 0.01596 0.00997 -0.0029 0.0229 1.0000
11.250 1.2959 0.01649 0.01052 -0.0022 0.0207 1.0000
11.500 1.3171 0.01707 0.01113 -0.0015 0.0186 1.0000
11.750 1.3384 0.01760 0.01170 -0.0007 0.0171 1.0000
12.000 1.3585 0.01823 0.01237 0.0001 0.0154 1.0000
12.250 1.3788 0.01881 0.01300 0.0009 0.0143 1.0000
12.500 1.3985 0.01942 0.01366 0.0018 0.0133 1.0000
12.750 1.4170 0.02010 0.01439 0.0028 0.0123 1.0000
13.000 1.4343 0.02085 0.01519 0.0040 0.0114 1.0000
13.250 1.4521 0.02150 0.01592 0.0051 0.0110 1.0000
13.500 1.4684 0.02222 0.01672 0.0063 0.0104 1.0000
13.750 1.4825 0.02301 0.01757 0.0079 0.0098 1.0000
14.000 1.4927 0.02388 0.01851 0.0100 0.0093 1.0000
14.250 1.5009 0.02489 0.01959 0.0122 0.0087 1.0000
14.500 1.5105 0.02584 0.02063 0.0141 0.0084 1.0000
14.750 1.5189 0.02692 0.02180 0.0158 0.0081 1.0000
15.000 1.5256 0.02817 0.02314 0.0174 0.0077 1.0000
15.250 1.5306 0.02964 0.02470 0.0189 0.0074 1.0000
15.500 1.5337 0.03138 0.02653 0.0201 0.0071 1.0000
15.750 1.5345 0.03345 0.02871 0.0210 0.0068 1.0000
16.000 1.5327 0.03599 0.03136 0.0215 0.0066 1.0000
16.250 1.5290 0.03898 0.03447 0.0213 0.0064 1.0000
16.500 1.5245 0.04241 0.03803 0.0205 0.0063 1.0000
16.750 1.5159 0.04669 0.04246 0.0188 0.0062 1.0000
17.000 1.5017 0.05226 0.04819 0.0160 0.0061 1.0000
17.250 1.4787 0.05978 0.05590 0.0118 0.0061 1.0000
17.500 1.4413 0.07023 0.06656 0.0059 0.0062 1.0000
17.750 1.3819 0.08432 0.08089 -0.0013 0.0064 1.0000
18.000 1.3263 0.09746 0.09423 -0.0076 0.0067 1.0000
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Polar data table (+)
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