LOCKHEED-GEORGIA SUPERCRITICAL AIRFOIL (lg10sc-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED-GEORGIA SUPERCRITICAL AIRFOIL (lg10sc-il) Reynolds number: 500,000 Max Cl/Cd: 73.54 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lg10sc-il-500000.txt Download as CSV file: xf-lg10sc-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6187 0.05865 0.05584 -0.0288 1.0000 0.0199
-8.000 -0.6314 0.05258 0.04952 -0.0272 1.0000 0.0201
-7.750 -0.6271 0.04920 0.04614 -0.0261 1.0000 0.0205
-7.500 -0.6195 0.04710 0.04400 -0.0246 1.0000 0.0208
-7.250 -0.6111 0.04526 0.04210 -0.0229 1.0000 0.0212
-7.000 -0.6034 0.04318 0.03993 -0.0208 1.0000 0.0217
-6.750 -0.5961 0.04084 0.03744 -0.0183 1.0000 0.0226
-6.500 -0.5871 0.03932 0.03538 -0.0139 1.0000 0.0250
-6.250 -0.5916 0.03413 0.02980 -0.0098 1.0000 0.0257
-6.000 -0.5795 0.03191 0.02760 -0.0079 1.0000 0.0262
-5.750 -0.5670 0.03030 0.02592 -0.0058 1.0000 0.0267
-5.500 -0.5531 0.02878 0.02431 -0.0038 0.9999 0.0275
-5.250 -0.5268 0.01936 0.01345 -0.0006 0.9981 0.0162
-5.000 -0.4923 0.01791 0.01177 -0.0017 0.9962 0.0159
-4.750 -0.4591 0.01602 0.00971 -0.0028 0.9947 0.0161
-4.500 -0.4260 0.01481 0.00846 -0.0040 0.9923 0.0167
-4.250 -0.3913 0.01396 0.00758 -0.0054 0.9894 0.0174
-4.000 -0.3551 0.01322 0.00681 -0.0072 0.9869 0.0183
-3.750 -0.3163 0.01278 0.00632 -0.0095 0.9848 0.0198
-3.500 -0.2810 0.01169 0.00523 -0.0111 0.9792 0.0214
-3.250 -0.2346 0.01101 0.00454 -0.0148 0.9744 0.0239
-3.000 -0.1996 0.01038 0.00389 -0.0162 0.9671 0.0270
-2.750 -0.1662 0.00997 0.00349 -0.0172 0.9609 0.0329
-2.500 -0.1376 0.00941 0.00303 -0.0172 0.9521 0.0566
-2.250 -0.1139 0.00810 0.00261 -0.0168 0.9432 0.2798
-2.000 -0.0959 0.00684 0.00234 -0.0151 0.9306 0.5443
-1.750 -0.0755 0.00621 0.00224 -0.0133 0.9177 0.6891
-1.500 -0.0530 0.00589 0.00220 -0.0116 0.9041 0.7770
-1.250 -0.0304 0.00574 0.00222 -0.0097 0.8892 0.8428
-1.000 -0.0065 0.00572 0.00223 -0.0081 0.8730 0.8801
-0.750 0.0168 0.00577 0.00227 -0.0063 0.8552 0.9111
-0.500 0.0408 0.00591 0.00236 -0.0045 0.8349 0.9358
-0.250 0.0685 0.00606 0.00241 -0.0038 0.8116 0.9501
0.000 0.0976 0.00620 0.00242 -0.0036 0.7851 0.9599
0.250 0.1323 0.00636 0.00242 -0.0048 0.7512 0.9651
0.500 0.1623 0.00654 0.00241 -0.0050 0.7145 0.9723
0.750 0.2006 0.00676 0.00240 -0.0071 0.6662 0.9745
1.000 0.2373 0.00705 0.00241 -0.0090 0.6061 0.9774
1.250 0.2714 0.00738 0.00244 -0.0105 0.5410 0.9815
1.500 0.3049 0.00775 0.00249 -0.0119 0.4722 0.9854
2.000 0.3769 0.00843 0.00263 -0.0159 0.3614 0.9907
2.250 0.4117 0.00870 0.00271 -0.0177 0.3262 0.9941
2.500 0.4484 0.00893 0.00278 -0.0198 0.2983 0.9962
2.750 0.4848 0.00912 0.00287 -0.0219 0.2776 0.9986
3.000 0.5161 0.00929 0.00295 -0.0229 0.2618 1.0000
3.250 0.5401 0.00942 0.00302 -0.0223 0.2493 1.0000
3.500 0.5635 0.00958 0.00312 -0.0216 0.2382 1.0000
3.750 0.5869 0.00972 0.00321 -0.0208 0.2287 1.0000
4.000 0.6102 0.00987 0.00333 -0.0201 0.2203 1.0000
4.250 0.6332 0.01005 0.00346 -0.0192 0.2120 1.0000
4.500 0.6564 0.01019 0.00361 -0.0184 0.2045 1.0000
4.750 0.6791 0.01040 0.00376 -0.0175 0.1968 1.0000
5.000 0.7023 0.01056 0.00394 -0.0166 0.1905 1.0000
5.250 0.7251 0.01076 0.00412 -0.0157 0.1841 1.0000
5.500 0.7478 0.01099 0.00434 -0.0148 0.1782 1.0000
5.750 0.7711 0.01116 0.00452 -0.0139 0.1722 1.0000
6.000 0.7932 0.01149 0.00478 -0.0129 0.1658 1.0000
6.250 0.8169 0.01164 0.00500 -0.0122 0.1613 1.0000
6.500 0.8401 0.01188 0.00524 -0.0113 0.1562 1.0000
6.750 0.8624 0.01223 0.00557 -0.0104 0.1511 1.0000
7.000 0.8862 0.01242 0.00583 -0.0096 0.1470 1.0000
7.250 0.9096 0.01267 0.00607 -0.0089 0.1418 1.0000
7.500 0.9325 0.01299 0.00639 -0.0081 0.1363 1.0000
7.750 0.9569 0.01319 0.00664 -0.0075 0.1317 1.0000
8.000 0.9801 0.01352 0.00696 -0.0068 0.1269 1.0000
8.250 1.0038 0.01383 0.00731 -0.0062 0.1224 1.0000
8.500 1.0284 0.01405 0.00758 -0.0057 0.1179 1.0000
8.750 1.0515 0.01443 0.00795 -0.0051 0.1128 1.0000
9.000 1.0758 0.01471 0.00831 -0.0046 0.1087 1.0000
9.250 1.1002 0.01496 0.00861 -0.0041 0.1040 1.0000
9.500 1.1225 0.01545 0.00908 -0.0034 0.0987 1.0000
9.750 1.1476 0.01565 0.00939 -0.0031 0.0945 1.0000
10.000 1.1708 0.01602 0.00976 -0.0026 0.0886 1.0000
10.250 1.1945 0.01636 0.01017 -0.0021 0.0829 1.0000
10.500 1.2166 0.01685 0.01064 -0.0015 0.0751 1.0000
10.750 1.2394 0.01727 0.01109 -0.0009 0.0663 1.0000
11.000 1.2598 0.01794 0.01174 -0.0001 0.0556 1.0000
11.250 1.2782 0.01882 0.01258 0.0010 0.0458 1.0000
11.500 1.2960 0.01970 0.01348 0.0022 0.0393 1.0000
11.750 1.3127 0.02064 0.01449 0.0035 0.0349 1.0000
12.000 1.3269 0.02174 0.01563 0.0050 0.0315 1.0000
12.250 1.3406 0.02281 0.01681 0.0066 0.0290 1.0000
12.500 1.3550 0.02374 0.01784 0.0081 0.0270 1.0000
12.750 1.3635 0.02500 0.01917 0.0103 0.0252 1.0000
13.000 1.3642 0.02651 0.02079 0.0135 0.0238 1.0000
13.250 1.3737 0.02753 0.02194 0.0154 0.0227 1.0000
13.500 1.3802 0.02881 0.02334 0.0173 0.0217 1.0000
13.750 1.3842 0.03034 0.02496 0.0190 0.0207 1.0000
14.000 1.3826 0.03243 0.02715 0.0207 0.0198 1.0000
14.250 1.3719 0.03556 0.03041 0.0219 0.0191 1.0000
14.500 1.3699 0.03827 0.03328 0.0222 0.0186 1.0000
14.750 1.3689 0.04116 0.03633 0.0218 0.0181 1.0000
15.000 1.3638 0.04488 0.04021 0.0206 0.0177 1.0000
15.250 1.3552 0.04945 0.04494 0.0185 0.0173 1.0000
15.500 1.3436 0.05495 0.05060 0.0156 0.0170 1.0000
15.750 1.3278 0.06144 0.05725 0.0119 0.0169 1.0000
16.000 1.3088 0.06862 0.06459 0.0079 0.0168 1.0000
16.250 1.2874 0.07614 0.07226 0.0040 0.0167 1.0000
16.500 1.2651 0.08366 0.07991 0.0003 0.0167 1.0000
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Polar data table (+)
Polar graphs
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