LOCKHEED C-141 BL113.6 AIRFOIL (c141b-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL113.6 AIRFOIL (c141b-il) Reynolds number: 50,000 Max Cl/Cd: 28.26 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c141b-il-50000-n5.txt Download as CSV file: xf-c141b-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-141 BL113.6 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5732 0.09877 0.09069 -0.0493 1.0000 0.0707
-11.250 -0.5978 0.08987 0.08183 -0.0542 1.0000 0.0702
-11.000 -0.6327 0.08163 0.07360 -0.0584 1.0000 0.0693
-10.750 -0.6701 0.07547 0.06741 -0.0596 1.0000 0.0685
-10.500 -0.7063 0.07113 0.06301 -0.0576 1.0000 0.0679
-10.250 -0.7399 0.06803 0.05983 -0.0532 1.0000 0.0676
-10.000 -0.7648 0.06495 0.05661 -0.0490 1.0000 0.0677
-9.750 -0.7841 0.06199 0.05347 -0.0449 1.0000 0.0683
-9.500 -0.7991 0.05904 0.05029 -0.0409 1.0000 0.0690
-9.250 -0.8104 0.05606 0.04701 -0.0370 1.0000 0.0699
-9.000 -0.8178 0.05304 0.04363 -0.0332 1.0000 0.0710
-8.750 -0.8223 0.05005 0.04018 -0.0295 1.0000 0.0724
-8.500 -0.8203 0.04751 0.03730 -0.0264 1.0000 0.0743
-8.250 -0.8097 0.04592 0.03565 -0.0244 1.0000 0.0767
-8.000 -0.7998 0.04406 0.03358 -0.0221 1.0000 0.0792
-7.750 -0.7892 0.04195 0.03111 -0.0198 1.0000 0.0820
-7.500 -0.7773 0.03991 0.02859 -0.0175 1.0000 0.0855
-7.250 -0.7612 0.03852 0.02723 -0.0160 1.0000 0.0889
-7.000 -0.7444 0.03705 0.02556 -0.0144 1.0000 0.0928
-6.750 -0.7267 0.03558 0.02366 -0.0127 1.0000 0.0979
-6.500 -0.7079 0.03436 0.02254 -0.0116 1.0000 0.1024
-6.250 -0.6881 0.03322 0.02124 -0.0102 1.0000 0.1084
-6.000 -0.6678 0.03212 0.02005 -0.0090 1.0000 0.1148
-5.750 -0.6473 0.03119 0.01905 -0.0078 1.0000 0.1222
-5.500 -0.6267 0.03027 0.01811 -0.0067 1.0000 0.1307
-5.250 -0.6059 0.02948 0.01716 -0.0054 1.0000 0.1411
-5.000 -0.5864 0.02865 0.01642 -0.0042 1.0000 0.1526
-4.750 -0.5668 0.02787 0.01566 -0.0029 1.0000 0.1668
-4.500 -0.5475 0.02710 0.01493 -0.0017 1.0000 0.1857
-4.250 -0.5286 0.02627 0.01423 -0.0005 1.0000 0.2102
-4.000 -0.5101 0.02537 0.01357 0.0006 1.0000 0.2473
-3.750 -0.4934 0.02435 0.01298 0.0020 1.0000 0.3099
-3.500 -0.4796 0.02321 0.01265 0.0042 1.0000 0.4287
-3.250 -0.4657 0.02264 0.01286 0.0077 1.0000 0.5796
-3.000 -0.4490 0.02262 0.01312 0.0109 1.0000 0.6798
-2.750 -0.4310 0.02275 0.01333 0.0138 1.0000 0.7472
-2.500 -0.4090 0.02304 0.01363 0.0162 1.0000 0.8006
-2.250 -0.3816 0.02346 0.01400 0.0174 1.0000 0.8481
-2.000 -0.3465 0.02402 0.01444 0.0169 1.0000 0.8918
-1.750 -0.2873 0.02495 0.01517 0.0118 1.0000 0.9331
-1.500 -0.2061 0.02588 0.01582 0.0017 1.0000 0.9673
-1.250 -0.1471 0.02618 0.01593 -0.0053 1.0000 0.9865
-1.000 -0.1030 0.02626 0.01588 -0.0099 1.0000 1.0000
-0.750 -0.0978 0.02604 0.01560 -0.0074 0.9989 1.0000
-0.500 -0.0662 0.02610 0.01556 -0.0097 0.9916 1.0000
-0.250 -0.0350 0.02622 0.01559 -0.0118 0.9841 1.0000
0.000 -0.0063 0.02631 0.01561 -0.0133 0.9758 1.0000
0.250 0.0232 0.02647 0.01571 -0.0148 0.9679 1.0000
0.500 0.0526 0.02665 0.01584 -0.0163 0.9597 1.0000
0.750 0.0791 0.02681 0.01597 -0.0170 0.9506 1.0000
1.000 0.1122 0.02708 0.01621 -0.0190 0.9432 1.0000
1.250 0.1357 0.02723 0.01636 -0.0190 0.9328 1.0000
1.500 0.1669 0.02749 0.01662 -0.0204 0.9245 1.0000
1.750 0.1946 0.02770 0.01685 -0.0211 0.9145 1.0000
2.000 0.2203 0.02791 0.01709 -0.0213 0.9040 1.0000
2.250 0.2576 0.02814 0.01738 -0.0236 0.8959 1.0000
2.500 0.2809 0.02830 0.01759 -0.0232 0.8832 1.0000
2.750 0.3084 0.02842 0.01779 -0.0234 0.8705 1.0000
3.000 0.3408 0.02844 0.01791 -0.0242 0.8573 1.0000
3.250 0.3757 0.02826 0.01785 -0.0252 0.8414 1.0000
3.500 0.4110 0.02783 0.01755 -0.0257 0.8220 1.0000
3.750 0.4523 0.02708 0.01696 -0.0269 0.8016 1.0000
4.000 0.4808 0.02646 0.01649 -0.0258 0.7785 1.0000
4.250 0.5129 0.02565 0.01583 -0.0250 0.7543 1.0000
4.500 0.5376 0.02502 0.01534 -0.0230 0.7256 1.0000
4.750 0.5696 0.02423 0.01468 -0.0219 0.6900 1.0000
5.000 0.6029 0.02353 0.01402 -0.0211 0.6389 1.0000
5.250 0.6387 0.02303 0.01333 -0.0205 0.5512 1.0000
5.500 0.6622 0.02343 0.01301 -0.0183 0.4273 1.0000
5.750 0.6680 0.02454 0.01345 -0.0143 0.3395 1.0000
6.000 0.6741 0.02572 0.01418 -0.0108 0.2808 1.0000
6.250 0.6831 0.02688 0.01501 -0.0079 0.2401 1.0000
6.500 0.6950 0.02799 0.01590 -0.0055 0.2108 1.0000
6.750 0.7104 0.02904 0.01682 -0.0036 0.1868 1.0000
7.000 0.7282 0.03011 0.01780 -0.0022 0.1681 1.0000
7.250 0.7492 0.03118 0.01884 -0.0013 0.1524 1.0000
7.500 0.7737 0.03229 0.01996 -0.0009 0.1388 1.0000
7.750 0.7998 0.03348 0.02114 -0.0007 0.1276 1.0000
8.000 0.8247 0.03469 0.02231 -0.0005 0.1182 1.0000
8.250 0.8521 0.03604 0.02385 -0.0004 0.1094 1.0000
8.500 0.8770 0.03746 0.02520 -0.0003 0.1028 1.0000
8.750 0.9013 0.03906 0.02712 0.0002 0.0964 1.0000
9.000 0.9230 0.04055 0.02856 0.0007 0.0915 1.0000
9.250 0.9426 0.04251 0.03085 0.0017 0.0868 1.0000
9.500 0.9598 0.04443 0.03302 0.0030 0.0829 1.0000
9.750 0.9767 0.04611 0.03473 0.0041 0.0796 1.0000
10.000 0.9871 0.04845 0.03740 0.0061 0.0767 1.0000
10.250 0.9932 0.05105 0.04041 0.0085 0.0743 1.0000
10.500 0.9976 0.05349 0.04314 0.0110 0.0722 1.0000
10.750 1.0023 0.05565 0.04548 0.0133 0.0702 1.0000
11.000 1.0102 0.05763 0.04749 0.0150 0.0683 1.0000
11.250 1.0017 0.06045 0.05058 0.0185 0.0672 1.0000
11.750 0.9646 0.06733 0.05815 0.0255 0.0661 1.0000
12.000 0.9422 0.07139 0.06248 0.0278 0.0658 1.0000
12.250 0.9165 0.07608 0.06742 0.0290 0.0658 1.0000
12.500 0.8874 0.08166 0.07322 0.0287 0.0659 1.0000
12.750 0.8554 0.08850 0.08022 0.0265 0.0662 1.0000
13.000 0.8216 0.09699 0.08884 0.0223 0.0666 1.0000
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Polar data table (+)
Polar graphs
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