LOCKHEED C-141 BL113.6 AIRFOIL (c141b-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL113.6 AIRFOIL (c141b-il) Reynolds number: 50,000 Max Cl/Cd: 29.32 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c141b-il-50000.txt Download as CSV file: xf-c141b-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4492 0.10544 0.09768 -0.0145 1.0000 0.3913
-9.000 -0.6164 0.08488 0.07758 -0.0358 1.0000 0.2027
-8.750 -0.7228 0.07624 0.06882 -0.0334 1.0000 0.1735
-8.500 -0.7144 0.07194 0.06450 -0.0320 1.0000 0.1692
-8.250 -0.7718 0.06593 0.05788 -0.0271 1.0000 0.1572
-8.000 -0.7715 0.06197 0.05373 -0.0247 1.0000 0.1562
-7.750 -0.7744 0.05823 0.04972 -0.0219 1.0000 0.1559
-7.500 -0.7755 0.05464 0.04576 -0.0190 1.0000 0.1560
-7.250 -0.7733 0.05117 0.04187 -0.0162 1.0000 0.1562
-7.000 -0.7679 0.04795 0.03814 -0.0135 1.0000 0.1568
-6.750 -0.7516 0.04522 0.03552 -0.0123 1.0000 0.1616
-6.500 -0.7388 0.04277 0.03277 -0.0102 1.0000 0.1659
-6.250 -0.7250 0.04024 0.02974 -0.0082 1.0000 0.1697
-6.000 -0.7086 0.03791 0.02707 -0.0065 1.0000 0.1757
-5.750 -0.6886 0.03606 0.02509 -0.0053 1.0000 0.1832
-5.500 -0.6685 0.03416 0.02287 -0.0040 1.0000 0.1919
-5.250 -0.6467 0.03263 0.02115 -0.0028 1.0000 0.2031
-5.000 -0.6235 0.03109 0.01960 -0.0020 1.0000 0.2164
-4.750 -0.5993 0.02968 0.01817 -0.0012 1.0000 0.2332
-4.500 -0.5748 0.02838 0.01687 -0.0003 1.0000 0.2559
-4.250 -0.5501 0.02709 0.01574 0.0005 1.0000 0.2876
-4.000 -0.5260 0.02562 0.01472 0.0013 1.0000 0.3388
-3.750 -0.5096 0.02360 0.01389 0.0038 1.0000 0.4565
-3.500 -0.5064 0.02307 0.01496 0.0132 1.0000 0.7235
-3.250 -0.4830 0.02460 0.01650 0.0201 1.0000 0.8402
-3.000 -0.3085 0.02895 0.01989 0.0012 1.0000 0.9405
-2.750 -0.1050 0.02912 0.01919 -0.0318 1.0000 1.0000
-2.500 -0.1044 0.02858 0.01856 -0.0290 1.0000 1.0000
-2.250 -0.1038 0.02810 0.01801 -0.0262 1.0000 1.0000
-2.000 -0.1033 0.02766 0.01750 -0.0231 1.0000 1.0000
-1.750 -0.1029 0.02726 0.01704 -0.0200 1.0000 1.0000
-1.500 -0.1028 0.02689 0.01662 -0.0167 1.0000 1.0000
-1.250 -0.1029 0.02656 0.01623 -0.0134 1.0000 1.0000
-1.000 -0.1030 0.02626 0.01588 -0.0099 1.0000 1.0000
-0.750 -0.1029 0.02600 0.01556 -0.0065 1.0000 1.0000
-0.500 -0.1020 0.02579 0.01530 -0.0031 1.0000 1.0000
-0.250 -0.0997 0.02565 0.01509 0.0002 1.0000 1.0000
0.000 -0.0953 0.02558 0.01496 0.0031 1.0000 1.0000
0.250 -0.0888 0.02560 0.01490 0.0057 1.0000 1.0000
0.500 -0.0806 0.02570 0.01493 0.0080 1.0000 1.0000
0.750 -0.0705 0.02587 0.01503 0.0100 1.0000 1.0000
1.000 -0.0588 0.02612 0.01522 0.0117 1.0000 1.0000
1.250 -0.0458 0.02644 0.01549 0.0131 1.0000 1.0000
1.500 -0.0318 0.02682 0.01583 0.0144 1.0000 1.0000
1.750 -0.0171 0.02726 0.01625 0.0154 1.0000 1.0000
2.000 -0.0019 0.02776 0.01673 0.0163 1.0000 1.0000
2.250 0.0137 0.02832 0.01729 0.0171 1.0000 1.0000
2.500 0.0294 0.02894 0.01791 0.0177 1.0000 1.0000
2.750 0.0452 0.02962 0.01860 0.0182 1.0000 1.0000
3.000 0.0610 0.03036 0.01937 0.0187 1.0000 1.0000
3.250 0.0766 0.03117 0.02022 0.0190 1.0000 1.0000
3.500 0.0921 0.03205 0.02115 0.0193 1.0000 1.0000
3.750 0.1612 0.03434 0.02361 0.0094 0.9750 1.0000
4.000 0.2345 0.03622 0.02570 -0.0004 0.9432 1.0000
4.250 0.2971 0.03717 0.02688 -0.0072 0.9094 1.0000
4.500 0.3561 0.03744 0.02740 -0.0123 0.8742 1.0000
4.750 0.4210 0.03694 0.02723 -0.0172 0.8377 1.0000
5.000 0.5076 0.03477 0.02553 -0.0231 0.7995 1.0000
5.250 0.5697 0.03189 0.02307 -0.0240 0.7564 1.0000
5.500 0.6627 0.02589 0.01766 -0.0252 0.6838 1.0000
5.750 0.7145 0.02437 0.01452 -0.0215 0.4255 1.0000
6.000 0.7295 0.02647 0.01566 -0.0187 0.3353 1.0000
6.250 0.7615 0.02845 0.01716 -0.0192 0.2798 1.0000
6.500 0.7973 0.03039 0.01878 -0.0204 0.2445 1.0000
6.750 0.8277 0.03227 0.02064 -0.0206 0.2209 1.0000
7.000 0.8548 0.03419 0.02259 -0.0203 0.2038 1.0000
7.250 0.8800 0.03626 0.02469 -0.0197 0.1907 1.0000
7.500 0.9035 0.03831 0.02678 -0.0189 0.1794 1.0000
7.750 0.9184 0.04058 0.02947 -0.0166 0.1721 1.0000
8.000 0.9395 0.04287 0.03178 -0.0155 0.1642 1.0000
8.250 0.9491 0.04551 0.03483 -0.0127 0.1593 1.0000
8.500 0.9556 0.04827 0.03804 -0.0094 0.1560 1.0000
8.750 0.9631 0.05100 0.04108 -0.0066 0.1521 1.0000
9.000 0.9842 0.05429 0.04422 -0.0062 0.1470 1.0000
9.250 0.9815 0.05754 0.04794 -0.0023 0.1462 1.0000
9.500 0.9760 0.06112 0.05191 0.0014 0.1460 1.0000
9.750 0.9674 0.06487 0.05600 0.0051 0.1460 1.0000
10.000 0.9565 0.06880 0.06022 0.0085 0.1461 1.0000
10.250 0.9447 0.07294 0.06458 0.0115 0.1465 1.0000
10.500 0.9307 0.07719 0.06905 0.0143 0.1475 1.0000
10.750 0.8291 0.08430 0.07650 0.0192 0.1596 1.0000
11.000 0.8212 0.08986 0.08211 0.0190 0.1616 1.0000
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Polar data table (+)
Polar graphs
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