LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il) Reynolds number: 50,000 Max Cl/Cd: 31.51 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c141d-il-50000.txt Download as CSV file: xf-c141d-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4478 0.10695 0.09940 -0.0174 1.0000 0.3020
-8.750 -0.4516 0.10425 0.09678 -0.0165 1.0000 0.3153
-8.500 -0.4541 0.10165 0.09426 -0.0152 1.0000 0.3312
-8.250 -0.4429 0.09848 0.09111 -0.0132 1.0000 0.3512
-8.000 -0.4381 0.09580 0.08849 -0.0112 1.0000 0.3726
-7.750 -0.4489 0.09414 0.08693 -0.0086 1.0000 0.3945
-7.500 -0.4415 0.09091 0.08374 -0.0063 1.0000 0.4159
-7.250 -0.4273 0.08791 0.08075 -0.0040 1.0000 0.4423
-7.000 -0.4157 0.08497 0.07784 -0.0013 1.0000 0.4722
-6.750 -0.4130 0.08258 0.07552 0.0019 1.0000 0.5022
-6.250 -0.6078 0.06157 0.05399 -0.0239 1.0000 0.1931
-6.000 -0.5967 0.05596 0.04809 -0.0236 1.0000 0.1714
-5.750 -0.5903 0.05097 0.04240 -0.0228 1.0000 0.1571
-5.500 -0.5773 0.04723 0.03840 -0.0215 1.0000 0.1538
-5.250 -0.5629 0.04378 0.03450 -0.0202 1.0000 0.1519
-5.000 -0.5463 0.04086 0.03111 -0.0189 1.0000 0.1536
-4.750 -0.5271 0.03815 0.02787 -0.0176 1.0000 0.1557
-4.500 -0.5063 0.03575 0.02493 -0.0165 1.0000 0.1604
-4.250 -0.4842 0.03365 0.02278 -0.0156 1.0000 0.1675
-4.000 -0.4603 0.03201 0.02056 -0.0146 1.0000 0.1757
-3.750 -0.4363 0.03020 0.01880 -0.0140 1.0000 0.1862
-3.500 -0.4106 0.02870 0.01713 -0.0134 1.0000 0.1979
-3.250 -0.3845 0.02743 0.01578 -0.0127 1.0000 0.2132
-3.000 -0.3578 0.02626 0.01465 -0.0121 1.0000 0.2327
-2.750 -0.3303 0.02520 0.01362 -0.0117 1.0000 0.2605
-2.500 -0.1595 0.02258 0.01393 -0.0282 1.0000 1.0000
-2.250 -0.1586 0.02226 0.01340 -0.0246 1.0000 1.0000
-2.000 -0.1562 0.02201 0.01293 -0.0212 1.0000 1.0000
-1.750 -0.1516 0.02183 0.01255 -0.0180 1.0000 1.0000
-1.500 -0.1448 0.02172 0.01224 -0.0151 1.0000 1.0000
-1.250 -0.1359 0.02167 0.01201 -0.0125 1.0000 1.0000
-1.000 -0.1249 0.02169 0.01184 -0.0103 1.0000 1.0000
-0.750 -0.1119 0.02177 0.01174 -0.0084 1.0000 1.0000
-0.500 -0.0973 0.02191 0.01172 -0.0067 1.0000 1.0000
-0.250 -0.0815 0.02210 0.01176 -0.0054 1.0000 1.0000
0.000 -0.0648 0.02233 0.01186 -0.0041 1.0000 1.0000
0.250 -0.0474 0.02261 0.01202 -0.0031 1.0000 1.0000
0.500 -0.0295 0.02293 0.01224 -0.0022 1.0000 1.0000
0.750 -0.0112 0.02330 0.01251 -0.0014 1.0000 1.0000
1.000 0.0072 0.02370 0.01284 -0.0006 1.0000 1.0000
1.250 0.0258 0.02415 0.01323 0.0000 1.0000 1.0000
1.500 0.0445 0.02464 0.01368 0.0006 1.0000 1.0000
1.750 0.0632 0.02517 0.01418 0.0011 1.0000 1.0000
2.000 0.0818 0.02575 0.01474 0.0015 1.0000 1.0000
2.250 0.1003 0.02638 0.01537 0.0019 1.0000 1.0000
2.500 0.1186 0.02706 0.01606 0.0022 1.0000 1.0000
2.750 0.1367 0.02780 0.01682 0.0025 1.0000 1.0000
3.000 0.1545 0.02860 0.01765 0.0026 1.0000 1.0000
3.250 0.1720 0.02946 0.01857 0.0028 1.0000 1.0000
3.500 0.1890 0.03040 0.01957 0.0028 1.0000 1.0000
3.750 0.2502 0.03229 0.02163 -0.0055 0.9788 1.0000
4.000 0.3306 0.03395 0.02355 -0.0162 0.9432 1.0000
4.250 0.3941 0.03453 0.02439 -0.0227 0.9064 1.0000
4.500 0.4786 0.03361 0.02386 -0.0300 0.8585 1.0000
4.750 0.5595 0.03121 0.02191 -0.0345 0.8124 1.0000
5.000 0.6358 0.02743 0.01868 -0.0360 0.7626 1.0000
5.250 0.7029 0.02231 0.01376 -0.0320 0.6128 1.0000
5.500 0.7219 0.02418 0.01334 -0.0267 0.3674 1.0000
5.750 0.7489 0.02628 0.01477 -0.0263 0.3035 1.0000
6.000 0.7828 0.02806 0.01632 -0.0270 0.2661 1.0000
6.250 0.8172 0.02993 0.01792 -0.0279 0.2407 1.0000
6.500 0.8456 0.03171 0.01976 -0.0277 0.2217 1.0000
6.750 0.8727 0.03368 0.02177 -0.0274 0.2066 1.0000
7.000 0.8990 0.03581 0.02388 -0.0271 0.1934 1.0000
7.250 0.9176 0.03778 0.02627 -0.0253 0.1831 1.0000
7.500 0.9391 0.04031 0.02894 -0.0242 0.1745 1.0000
7.750 0.9548 0.04266 0.03169 -0.0222 0.1668 1.0000
8.000 0.9749 0.04566 0.03472 -0.0212 0.1606 1.0000
8.250 0.9806 0.04853 0.03822 -0.0180 0.1566 1.0000
8.500 0.9874 0.05167 0.04180 -0.0152 0.1531 1.0000
8.750 0.9936 0.05506 0.04553 -0.0128 0.1507 1.0000
9.000 1.0134 0.05872 0.04908 -0.0123 0.1459 1.0000
9.250 1.0081 0.06257 0.05340 -0.0090 0.1455 1.0000
9.500 1.0059 0.06695 0.05810 -0.0064 0.1458 1.0000
9.750 0.9529 0.07222 0.06414 -0.0008 0.1524 1.0000
10.000 0.9252 0.07749 0.06962 0.0017 0.1561 1.0000
10.250 0.9099 0.08266 0.07487 0.0030 0.1591 1.0000
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Polar data table (+)
Polar graphs
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