LOCKHEED-GEORGIA SUPERCRITICAL AIRFOIL (lg10sc-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED-GEORGIA SUPERCRITICAL AIRFOIL (lg10sc-il) Reynolds number: 100,000 Max Cl/Cd: 39.07 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lg10sc-il-100000-n5.txt Download as CSV file: xf-lg10sc-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4351 0.09603 0.09115 -0.0166 1.0000 0.0301
-9.750 -0.5551 0.09957 0.09447 -0.0106 1.0000 0.0309
-9.500 -0.5529 0.09579 0.09073 -0.0114 1.0000 0.0299
-9.000 -0.5865 0.07661 0.07147 -0.0278 1.0000 0.0251
-8.750 -0.5923 0.07315 0.06800 -0.0279 1.0000 0.0248
-8.500 -0.5985 0.06945 0.06425 -0.0279 1.0000 0.0246
-8.250 -0.6028 0.06553 0.06024 -0.0278 1.0000 0.0243
-8.000 -0.6057 0.06152 0.05609 -0.0273 1.0000 0.0240
-7.750 -0.6065 0.05751 0.05190 -0.0264 1.0000 0.0237
-7.500 -0.6053 0.05355 0.04771 -0.0251 1.0000 0.0234
-7.250 -0.6021 0.04969 0.04357 -0.0234 1.0000 0.0234
-7.000 -0.5969 0.04602 0.03955 -0.0214 1.0000 0.0237
-6.750 -0.5899 0.04251 0.03559 -0.0190 1.0000 0.0242
-6.500 -0.5806 0.03933 0.03194 -0.0165 1.0000 0.0247
-6.250 -0.5683 0.03656 0.02874 -0.0142 1.0000 0.0249
-6.000 -0.5538 0.03402 0.02583 -0.0121 1.0000 0.0249
-5.750 -0.5374 0.03170 0.02313 -0.0101 1.0000 0.0250
-5.500 -0.5195 0.02959 0.02068 -0.0082 1.0000 0.0252
-5.250 -0.5005 0.02765 0.01854 -0.0067 1.0000 0.0256
-5.000 -0.4804 0.02606 0.01679 -0.0053 1.0000 0.0262
-4.750 -0.4596 0.02468 0.01526 -0.0040 1.0000 0.0270
-4.500 -0.4386 0.02356 0.01404 -0.0026 1.0000 0.0285
-4.250 -0.4171 0.02256 0.01287 -0.0013 1.0000 0.0308
-4.000 -0.3959 0.02141 0.01165 0.0000 1.0000 0.0325
-3.750 -0.3754 0.02043 0.01070 0.0014 1.0000 0.0341
-3.500 -0.3550 0.01960 0.00985 0.0027 1.0000 0.0362
-3.250 -0.3344 0.01898 0.00914 0.0041 1.0000 0.0399
-3.000 -0.3143 0.01826 0.00847 0.0053 1.0000 0.0448
-2.750 -0.2932 0.01769 0.00781 0.0065 1.0000 0.0502
-2.500 -0.2660 0.01702 0.00721 0.0063 0.9978 0.0650
-2.250 -0.2308 0.01581 0.00658 0.0043 0.9921 0.1638
-2.000 -0.2076 0.01342 0.00651 0.0049 0.9875 0.6616
-1.750 -0.1701 0.01347 0.00716 0.0058 0.9834 0.8761
-1.500 -0.0823 0.01420 0.00769 -0.0035 0.9851 0.9690
-1.250 -0.0148 0.01411 0.00737 -0.0114 0.9727 0.9757
-1.000 0.0405 0.01396 0.00703 -0.0170 0.9592 0.9815
-0.750 0.0906 0.01379 0.00673 -0.0216 0.9443 0.9872
-0.500 0.1376 0.01360 0.00643 -0.0255 0.9263 0.9929
-0.250 0.1826 0.01339 0.00613 -0.0290 0.9041 0.9981
0.000 0.2170 0.01320 0.00585 -0.0302 0.8775 1.0000
0.250 0.2440 0.01304 0.00558 -0.0298 0.8464 1.0000
0.500 0.2693 0.01292 0.00534 -0.0290 0.8112 1.0000
0.750 0.2933 0.01284 0.00511 -0.0278 0.7718 1.0000
1.000 0.3165 0.01283 0.00491 -0.0265 0.7258 1.0000
1.250 0.3395 0.01290 0.00474 -0.0252 0.6731 1.0000
1.500 0.3620 0.01306 0.00462 -0.0238 0.6151 1.0000
1.750 0.3837 0.01332 0.00456 -0.0225 0.5532 1.0000
2.000 0.4052 0.01365 0.00457 -0.0212 0.4951 1.0000
2.250 0.4266 0.01401 0.00463 -0.0201 0.4450 1.0000
2.500 0.4481 0.01437 0.00475 -0.0190 0.4047 1.0000
2.750 0.4698 0.01473 0.00491 -0.0179 0.3730 1.0000
3.000 0.4916 0.01508 0.00509 -0.0169 0.3476 1.0000
3.250 0.5137 0.01542 0.00531 -0.0160 0.3266 1.0000
3.500 0.5358 0.01576 0.00554 -0.0150 0.3090 1.0000
3.750 0.5580 0.01611 0.00582 -0.0140 0.2938 1.0000
4.000 0.5802 0.01647 0.00610 -0.0131 0.2805 1.0000
4.250 0.6024 0.01685 0.00640 -0.0121 0.2690 1.0000
4.500 0.6249 0.01721 0.00673 -0.0112 0.2579 1.0000
4.750 0.6474 0.01759 0.00711 -0.0103 0.2478 1.0000
5.000 0.6695 0.01802 0.00747 -0.0094 0.2391 1.0000
5.250 0.6924 0.01841 0.00790 -0.0085 0.2302 1.0000
5.500 0.7148 0.01887 0.00834 -0.0077 0.2228 1.0000
5.750 0.7377 0.01929 0.00881 -0.0068 0.2146 1.0000
6.000 0.7603 0.01978 0.00928 -0.0060 0.2078 1.0000
6.250 0.7835 0.02025 0.00983 -0.0053 0.2009 1.0000
6.500 0.8060 0.02079 0.01035 -0.0045 0.1952 1.0000
6.750 0.8293 0.02129 0.01098 -0.0038 0.1884 1.0000
7.000 0.8521 0.02181 0.01153 -0.0031 0.1825 1.0000
7.250 0.8750 0.02242 0.01223 -0.0024 0.1772 1.0000
7.500 0.8980 0.02302 0.01295 -0.0017 0.1717 1.0000
7.750 0.9206 0.02362 0.01356 -0.0010 0.1669 1.0000
8.000 0.9432 0.02429 0.01441 -0.0003 0.1614 1.0000
8.250 0.9655 0.02495 0.01520 0.0004 0.1563 1.0000
8.500 0.9878 0.02565 0.01591 0.0011 0.1524 1.0000
8.750 1.0094 0.02643 0.01695 0.0019 0.1471 1.0000
9.000 1.0306 0.02710 0.01775 0.0027 0.1418 1.0000
9.250 1.0513 0.02776 0.01848 0.0035 0.1368 1.0000
9.500 1.0707 0.02842 0.01941 0.0045 0.1300 1.0000
9.750 1.0900 0.02893 0.01992 0.0054 0.1246 1.0000
10.000 1.1083 0.02976 0.02108 0.0065 0.1181 1.0000
10.250 1.1262 0.03036 0.02177 0.0076 0.1127 1.0000
10.500 1.1428 0.03125 0.02293 0.0088 0.1064 1.0000
10.750 1.1585 0.03193 0.02372 0.0100 0.1004 1.0000
11.000 1.1728 0.03292 0.02496 0.0114 0.0939 1.0000
11.250 1.1855 0.03372 0.02586 0.0129 0.0878 1.0000
11.500 1.1964 0.03497 0.02737 0.0145 0.0812 1.0000
11.750 1.2045 0.03603 0.02851 0.0163 0.0757 1.0000
12.000 1.2092 0.03758 0.03030 0.0184 0.0700 1.0000
12.250 1.2106 0.03906 0.03189 0.0206 0.0657 1.0000
12.500 1.2095 0.04106 0.03405 0.0225 0.0618 1.0000
12.750 1.2068 0.04334 0.03653 0.0239 0.0581 1.0000
13.000 1.2014 0.04594 0.03923 0.0247 0.0556 1.0000
13.250 1.1932 0.04923 0.04264 0.0248 0.0535 1.0000
13.500 1.1825 0.05331 0.04697 0.0240 0.0516 1.0000
13.750 1.1690 0.05818 0.05206 0.0221 0.0501 1.0000
14.000 1.1525 0.06404 0.05811 0.0190 0.0491 1.0000
14.250 1.1324 0.07107 0.06532 0.0148 0.0485 1.0000
14.500 1.1080 0.07933 0.07376 0.0099 0.0483 1.0000
14.750 1.0774 0.08906 0.08367 0.0043 0.0485 1.0000
15.000 1.0339 0.10168 0.09649 -0.0027 0.0494 1.0000
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Polar data table (+)
Polar graphs
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