LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il) Reynolds number: 100,000 Max Cl/Cd: 47.17 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c141d-il-100000.txt Download as CSV file: xf-c141d-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-141 BL610.61 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4849 0.09822 0.09289 -0.0342 1.0000 0.1232
-9.000 -0.5182 0.09448 0.08929 -0.0382 1.0000 0.1259
-8.750 -0.5555 0.09115 0.08606 -0.0393 1.0000 0.1263
-8.500 -0.5167 0.08767 0.08257 -0.0349 1.0000 0.1316
-8.250 -0.5246 0.08499 0.07997 -0.0335 1.0000 0.1349
-8.000 -0.5497 0.08207 0.07712 -0.0323 1.0000 0.1370
-7.750 -0.5838 0.07876 0.07380 -0.0322 1.0000 0.1405
-7.500 -0.6383 0.07758 0.07220 -0.0307 1.0000 0.1427
-7.250 -0.5979 0.07194 0.06701 -0.0284 1.0000 0.1473
-7.000 -0.5985 0.06934 0.06441 -0.0263 1.0000 0.1522
-6.750 -0.6216 0.06575 0.06057 -0.0254 1.0000 0.1610
-6.500 -0.6097 0.06290 0.05783 -0.0230 1.0000 0.1648
-6.250 -0.6317 0.04684 0.03966 -0.0224 1.0000 0.0857
-6.000 -0.6159 0.04310 0.03599 -0.0213 1.0000 0.0827
-5.750 -0.6035 0.03928 0.03179 -0.0195 1.0000 0.0799
-5.500 -0.5883 0.03635 0.02841 -0.0178 1.0000 0.0806
-5.250 -0.5704 0.03379 0.02537 -0.0162 1.0000 0.0822
-5.000 -0.5501 0.03138 0.02245 -0.0148 1.0000 0.0836
-4.750 -0.5282 0.02913 0.01978 -0.0138 1.0000 0.0870
-4.500 -0.5060 0.02788 0.01853 -0.0131 1.0000 0.0928
-4.250 -0.4825 0.02677 0.01695 -0.0120 1.0000 0.0987
-4.000 -0.4590 0.02524 0.01550 -0.0116 1.0000 0.1059
-3.750 -0.4349 0.02424 0.01426 -0.0109 1.0000 0.1138
-3.500 -0.4115 0.02333 0.01341 -0.0103 1.0000 0.1224
-3.250 -0.3874 0.02241 0.01247 -0.0097 1.0000 0.1310
-3.000 -0.3639 0.02185 0.01184 -0.0090 1.0000 0.1417
-2.750 -0.3402 0.02102 0.01118 -0.0084 1.0000 0.1539
-2.500 -0.3167 0.02035 0.01063 -0.0079 1.0000 0.1696
-2.250 -0.2932 0.01975 0.01016 -0.0073 1.0000 0.1931
-2.000 -0.2690 0.01893 0.00974 -0.0071 1.0000 0.2432
-1.750 -0.2536 0.01659 0.01030 -0.0021 1.0000 0.8373
-1.500 -0.1633 0.01750 0.01102 -0.0126 1.0000 1.0000
-1.250 -0.1559 0.01745 0.01083 -0.0098 1.0000 1.0000
-1.000 -0.1446 0.01751 0.01073 -0.0077 1.0000 1.0000
-0.750 -0.1302 0.01765 0.01072 -0.0061 1.0000 1.0000
-0.500 -0.1138 0.01785 0.01079 -0.0048 1.0000 1.0000
-0.250 -0.0962 0.01811 0.01093 -0.0038 1.0000 1.0000
0.000 -0.0779 0.01841 0.01113 -0.0030 1.0000 1.0000
0.250 -0.0414 0.01896 0.01156 -0.0056 0.9953 1.0000
0.500 -0.0003 0.01953 0.01205 -0.0092 0.9879 1.0000
0.750 0.0403 0.02011 0.01256 -0.0125 0.9802 1.0000
1.000 0.0829 0.02072 0.01311 -0.0162 0.9729 1.0000
1.250 0.1179 0.02115 0.01351 -0.0184 0.9632 1.0000
1.500 0.1564 0.02163 0.01398 -0.0211 0.9541 1.0000
1.750 0.2017 0.02211 0.01446 -0.0250 0.9454 1.0000
2.000 0.2390 0.02237 0.01475 -0.0273 0.9329 1.0000
2.250 0.2810 0.02254 0.01495 -0.0301 0.9195 1.0000
2.500 0.3325 0.02236 0.01485 -0.0341 0.9035 1.0000
2.750 0.3844 0.02196 0.01453 -0.0378 0.8877 1.0000
3.000 0.4544 0.02072 0.01344 -0.0438 0.8696 1.0000
3.250 0.5194 0.01934 0.01223 -0.0487 0.8530 1.0000
3.500 0.5672 0.01825 0.01130 -0.0506 0.8367 1.0000
3.750 0.6117 0.01713 0.01033 -0.0518 0.8174 1.0000
4.000 0.6408 0.01636 0.00967 -0.0503 0.7899 1.0000
4.250 0.6744 0.01550 0.00888 -0.0493 0.7520 1.0000
4.500 0.7033 0.01491 0.00820 -0.0474 0.6810 1.0000
4.750 0.7211 0.01545 0.00761 -0.0433 0.4598 1.0000
5.000 0.7166 0.01746 0.00831 -0.0372 0.2917 1.0000
5.250 0.7265 0.01885 0.00916 -0.0340 0.2338 1.0000
5.500 0.7425 0.01998 0.00999 -0.0319 0.2055 1.0000
5.750 0.7622 0.02099 0.01084 -0.0304 0.1858 1.0000
6.000 0.7839 0.02200 0.01175 -0.0292 0.1703 1.0000
6.250 0.8072 0.02309 0.01273 -0.0285 0.1575 1.0000
6.500 0.8324 0.02435 0.01380 -0.0282 0.1459 1.0000
6.750 0.8552 0.02526 0.01485 -0.0271 0.1357 1.0000
7.000 0.8807 0.02664 0.01624 -0.0268 0.1266 1.0000
7.250 0.9059 0.02800 0.01751 -0.0265 0.1183 1.0000
7.500 0.9291 0.02947 0.01922 -0.0255 0.1108 1.0000
7.750 0.9539 0.03111 0.02078 -0.0253 0.1042 1.0000
8.000 0.9736 0.03283 0.02287 -0.0237 0.0985 1.0000
8.250 0.9951 0.03442 0.02456 -0.0227 0.0934 1.0000
8.500 1.0148 0.03687 0.02715 -0.0218 0.0891 1.0000
8.750 1.0279 0.03889 0.02967 -0.0192 0.0856 1.0000
9.000 1.0423 0.04125 0.03236 -0.0172 0.0829 1.0000
9.250 1.0621 0.04325 0.03434 -0.0165 0.0798 1.0000
9.500 1.0708 0.04663 0.03801 -0.0143 0.0776 1.0000
9.750 1.0710 0.04964 0.04157 -0.0105 0.0765 1.0000
10.000 1.0696 0.05330 0.04567 -0.0071 0.0762 1.0000
10.250 1.0652 0.05722 0.04997 -0.0037 0.0763 1.0000
10.500 1.0581 0.06130 0.05437 -0.0005 0.0766 1.0000
10.750 1.0486 0.06545 0.05878 0.0025 0.0770 1.0000
11.000 1.0380 0.06968 0.06322 0.0053 0.0775 1.0000
11.250 1.0276 0.07407 0.06774 0.0077 0.0779 1.0000
11.500 0.8344 0.11516 0.10985 -0.0045 0.1614 1.0000
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Polar data table (+)
Polar graphs
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