LOCKHEED C-141 BL761.11 AIRFOIL (c141e-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL761.11 AIRFOIL (c141e-il) Reynolds number: 100,000 Max Cl/Cd: 45.71 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c141e-il-100000-n5.txt Download as CSV file: xf-c141e-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-141 BL761.11 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 -0.5088 0.09380 0.08808 -0.0407 1.0000 0.0422
-9.750 -0.5185 0.08904 0.08338 -0.0422 1.0000 0.0420
-9.500 -0.5328 0.08383 0.07824 -0.0442 1.0000 0.0418
-9.250 -0.5559 0.07796 0.07244 -0.0470 1.0000 0.0415
-9.000 -0.5862 0.07343 0.06794 -0.0463 1.0000 0.0411
-8.750 -0.6106 0.06871 0.06317 -0.0450 1.0000 0.0410
-8.500 -0.6305 0.06416 0.05851 -0.0432 1.0000 0.0411
-8.250 -0.6461 0.05961 0.05377 -0.0411 1.0000 0.0415
-8.000 -0.6584 0.05486 0.04875 -0.0388 1.0000 0.0420
-7.750 -0.6676 0.04982 0.04331 -0.0362 1.0000 0.0426
-7.500 -0.6715 0.04497 0.03795 -0.0337 1.0000 0.0431
-7.250 -0.6699 0.04049 0.03285 -0.0312 1.0000 0.0436
-7.000 -0.6586 0.03821 0.03032 -0.0294 1.0000 0.0443
-6.750 -0.6432 0.03716 0.02922 -0.0280 1.0000 0.0454
-6.500 -0.6278 0.03576 0.02765 -0.0266 1.0000 0.0468
-6.250 -0.6123 0.03365 0.02516 -0.0251 1.0000 0.0484
-6.000 -0.5949 0.03128 0.02229 -0.0237 1.0000 0.0498
-5.750 -0.5669 0.02929 0.01988 -0.0243 0.9978 0.0513
-5.500 -0.5365 0.02846 0.01901 -0.0255 0.9951 0.0534
-5.250 -0.5065 0.02735 0.01769 -0.0263 0.9925 0.0560
-5.000 -0.4762 0.02598 0.01595 -0.0269 0.9898 0.0583
-4.750 -0.4452 0.02503 0.01495 -0.0279 0.9870 0.0606
-4.500 -0.4129 0.02440 0.01427 -0.0292 0.9845 0.0641
-4.250 -0.3826 0.02360 0.01326 -0.0298 0.9814 0.0677
-4.000 -0.3526 0.02284 0.01254 -0.0305 0.9780 0.0708
-3.750 -0.3208 0.02233 0.01202 -0.0316 0.9749 0.0759
-3.500 -0.2874 0.02173 0.01136 -0.0329 0.9724 0.0811
-3.250 -0.2594 0.02126 0.01095 -0.0332 0.9680 0.0869
-3.000 -0.2293 0.02079 0.01046 -0.0339 0.9640 0.0940
-2.750 -0.1967 0.02039 0.01011 -0.0351 0.9606 0.1031
-2.500 -0.1643 0.01999 0.00977 -0.0363 0.9575 0.1133
-2.250 -0.1381 0.01965 0.00946 -0.0362 0.9518 0.1251
-2.000 -0.1064 0.01930 0.00918 -0.0372 0.9478 0.1418
-1.750 -0.0722 0.01890 0.00893 -0.0387 0.9447 0.1700
-1.500 -0.0465 0.01826 0.00874 -0.0388 0.9392 0.2512
-1.250 -0.0248 0.01666 0.00891 -0.0377 0.9355 0.6627
-1.000 0.0034 0.01646 0.00927 -0.0360 0.9322 0.8386
-0.750 0.0555 0.01669 0.00957 -0.0399 0.9315 0.9451
-0.500 0.1267 0.01693 0.00972 -0.0487 0.9326 0.9955
-0.250 0.1684 0.01695 0.00964 -0.0519 0.9294 1.0000
0.000 0.1884 0.01696 0.00958 -0.0506 0.9201 1.0000
0.250 0.2227 0.01695 0.00951 -0.0521 0.9152 1.0000
0.500 0.2458 0.01698 0.00949 -0.0514 0.9068 1.0000
0.750 0.2781 0.01697 0.00945 -0.0524 0.9009 1.0000
1.000 0.3072 0.01697 0.00944 -0.0527 0.8940 1.0000
1.250 0.3395 0.01686 0.00933 -0.0535 0.8857 1.0000
1.500 0.3733 0.01656 0.00904 -0.0542 0.8739 1.0000
1.750 0.4122 0.01596 0.00844 -0.0553 0.8581 1.0000
2.000 0.4458 0.01552 0.00801 -0.0556 0.8423 1.0000
2.250 0.4765 0.01529 0.00781 -0.0556 0.8296 1.0000
2.500 0.5078 0.01506 0.00761 -0.0557 0.8164 1.0000
2.750 0.5327 0.01488 0.00745 -0.0545 0.7952 1.0000
3.000 0.5625 0.01457 0.00713 -0.0540 0.7658 1.0000
3.250 0.5918 0.01433 0.00684 -0.0533 0.7270 1.0000
3.500 0.6221 0.01422 0.00661 -0.0530 0.6803 1.0000
3.750 0.6507 0.01429 0.00645 -0.0524 0.6146 1.0000
4.000 0.6724 0.01471 0.00641 -0.0505 0.5185 1.0000
4.250 0.6855 0.01554 0.00662 -0.0475 0.4095 1.0000
4.500 0.6977 0.01647 0.00704 -0.0446 0.3253 1.0000
4.750 0.7129 0.01727 0.00751 -0.0424 0.2681 1.0000
5.000 0.7296 0.01801 0.00800 -0.0405 0.2266 1.0000
5.250 0.7471 0.01872 0.00851 -0.0387 0.1928 1.0000
5.500 0.7655 0.01938 0.00904 -0.0371 0.1639 1.0000
5.750 0.7843 0.02004 0.00956 -0.0356 0.1410 1.0000
6.000 0.8033 0.02070 0.01012 -0.0341 0.1235 1.0000
6.250 0.8221 0.02138 0.01073 -0.0326 0.1106 1.0000
6.500 0.8405 0.02213 0.01141 -0.0311 0.1005 1.0000
6.750 0.8589 0.02290 0.01215 -0.0296 0.0920 1.0000
7.000 0.8778 0.02369 0.01297 -0.0282 0.0845 1.0000
7.500 0.9148 0.02547 0.01479 -0.0253 0.0735 1.0000
7.750 0.9333 0.02636 0.01567 -0.0239 0.0690 1.0000
8.000 0.9526 0.02735 0.01671 -0.0226 0.0651 1.0000
8.250 0.9723 0.02834 0.01778 -0.0215 0.0617 1.0000
8.500 0.9914 0.02938 0.01882 -0.0203 0.0593 1.0000
8.750 1.0116 0.03058 0.02009 -0.0193 0.0569 1.0000
9.000 1.0317 0.03173 0.02140 -0.0183 0.0543 1.0000
9.250 1.0503 0.03282 0.02258 -0.0171 0.0522 1.0000
9.500 1.0691 0.03405 0.02380 -0.0161 0.0507 1.0000
9.750 1.0886 0.03563 0.02554 -0.0151 0.0493 1.0000
10.000 1.1062 0.03729 0.02749 -0.0139 0.0478 1.0000
10.250 1.1214 0.03884 0.02925 -0.0124 0.0462 1.0000
10.500 1.1352 0.04023 0.03077 -0.0108 0.0449 1.0000
10.750 1.1486 0.04160 0.03221 -0.0092 0.0438 1.0000
11.000 1.1608 0.04340 0.03413 -0.0076 0.0430 1.0000
11.250 1.1645 0.04579 0.03691 -0.0048 0.0424 1.0000
11.500 1.1643 0.04833 0.03981 -0.0018 0.0417 1.0000
11.750 1.1604 0.05096 0.04277 0.0013 0.0411 1.0000
12.000 1.1535 0.05370 0.04582 0.0044 0.0405 1.0000
12.250 1.1442 0.05659 0.04898 0.0071 0.0400 1.0000
12.500 1.1330 0.05967 0.05232 0.0093 0.0396 1.0000
12.750 1.1196 0.06307 0.05596 0.0111 0.0392 1.0000
13.000 1.1035 0.06697 0.06009 0.0121 0.0389 1.0000
13.250 1.0823 0.07178 0.06514 0.0121 0.0387 1.0000
13.500 1.0481 0.07892 0.07259 0.0101 0.0388 1.0000
13.750 0.9629 0.09743 0.09158 -0.0014 0.0402 1.0000
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Polar data table (+)
Polar graphs
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