LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il) Reynolds number: 100,000 Max Cl/Cd: 47.66 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c141c-il-100000.txt Download as CSV file: xf-c141c-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-141 BL426.57 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 -0.5126 0.09284 0.08761 -0.0342 1.0000 0.1461
-9.000 -0.5308 0.08918 0.08405 -0.0358 1.0000 0.1514
-8.750 -0.5900 0.08558 0.08061 -0.0375 1.0000 0.1534
-8.500 -0.6522 0.08352 0.07845 -0.0354 1.0000 0.1543
-8.250 -0.5902 0.07877 0.07388 -0.0331 1.0000 0.1592
-8.000 -0.6003 0.07603 0.07117 -0.0310 1.0000 0.1632
-7.750 -0.6723 0.07393 0.06879 -0.0288 1.0000 0.1701
-7.500 -0.6415 0.06941 0.06450 -0.0270 1.0000 0.1733
-7.250 -0.6998 0.05235 0.04600 -0.0259 1.0000 0.0968
-7.000 -0.7012 0.04581 0.03857 -0.0221 1.0000 0.0812
-6.750 -0.6919 0.04214 0.03464 -0.0200 1.0000 0.0805
-6.500 -0.6815 0.03942 0.03142 -0.0176 1.0000 0.0812
-6.250 -0.6685 0.03659 0.02813 -0.0154 1.0000 0.0821
-6.000 -0.6520 0.03346 0.02469 -0.0140 1.0000 0.0829
-5.750 -0.6330 0.03119 0.02220 -0.0128 1.0000 0.0847
-5.500 -0.6129 0.02983 0.02075 -0.0117 1.0000 0.0887
-5.250 -0.5917 0.02836 0.01891 -0.0104 1.0000 0.0929
-5.000 -0.5685 0.02668 0.01688 -0.0094 1.0000 0.0964
-4.750 -0.5459 0.02548 0.01570 -0.0088 1.0000 0.1029
-4.500 -0.5222 0.02453 0.01447 -0.0078 1.0000 0.1091
-4.250 -0.4987 0.02327 0.01333 -0.0073 1.0000 0.1171
-4.000 -0.4752 0.02234 0.01232 -0.0065 1.0000 0.1267
-3.750 -0.4522 0.02161 0.01156 -0.0057 1.0000 0.1387
-3.500 -0.4294 0.02080 0.01086 -0.0050 1.0000 0.1545
-3.250 -0.4072 0.01990 0.01022 -0.0042 1.0000 0.1763
-3.000 -0.3848 0.01905 0.00963 -0.0035 1.0000 0.2151
-2.750 -0.3630 0.01704 0.00903 -0.0032 1.0000 0.4128
-2.500 -0.3514 0.01604 0.00966 0.0023 1.0000 0.7807
-2.250 -0.3307 0.01644 0.01022 0.0060 1.0000 0.8884
-2.000 -0.2662 0.01739 0.01095 0.0004 1.0000 0.9648
-1.750 -0.1454 0.01838 0.01152 -0.0173 1.0000 1.0000
-1.500 -0.1483 0.01810 0.01118 -0.0132 1.0000 1.0000
-1.250 -0.1481 0.01792 0.01090 -0.0095 1.0000 1.0000
-1.000 -0.1437 0.01783 0.01072 -0.0064 1.0000 1.0000
-0.750 -0.1358 0.01784 0.01062 -0.0038 1.0000 1.0000
-0.500 -0.1245 0.01794 0.01061 -0.0017 1.0000 1.0000
-0.250 -0.1105 0.01812 0.01069 -0.0002 1.0000 1.0000
0.000 -0.0947 0.01836 0.01085 0.0011 1.0000 1.0000
0.250 -0.0616 0.01883 0.01124 -0.0010 0.9958 1.0000
0.500 -0.0203 0.01939 0.01172 -0.0047 0.9883 1.0000
0.750 0.0211 0.01998 0.01225 -0.0083 0.9809 1.0000
1.000 0.0614 0.02051 0.01275 -0.0116 0.9727 1.0000
1.250 0.0973 0.02096 0.01318 -0.0140 0.9633 1.0000
1.500 0.1416 0.02153 0.01374 -0.0180 0.9557 1.0000
1.750 0.1775 0.02187 0.01410 -0.0202 0.9446 1.0000
2.000 0.2150 0.02219 0.01445 -0.0226 0.9330 1.0000
2.250 0.2567 0.02248 0.01479 -0.0256 0.9221 1.0000
2.500 0.3077 0.02265 0.01504 -0.0301 0.9124 1.0000
2.750 0.3600 0.02239 0.01489 -0.0342 0.8974 1.0000
3.000 0.4117 0.02180 0.01442 -0.0377 0.8797 1.0000
3.250 0.4808 0.02079 0.01362 -0.0440 0.8663 1.0000
3.500 0.5378 0.01968 0.01270 -0.0478 0.8510 1.0000
3.750 0.5724 0.01885 0.01203 -0.0475 0.8314 1.0000
4.000 0.6148 0.01766 0.01100 -0.0482 0.8103 1.0000
4.250 0.6503 0.01659 0.01007 -0.0475 0.7830 1.0000
4.500 0.6844 0.01561 0.00919 -0.0464 0.7430 1.0000
4.750 0.7124 0.01504 0.00853 -0.0444 0.6723 1.0000
5.000 0.7316 0.01535 0.00802 -0.0408 0.5006 1.0000
5.250 0.7274 0.01711 0.00853 -0.0346 0.3198 1.0000
5.500 0.7315 0.01871 0.00939 -0.0304 0.2373 1.0000
5.750 0.7431 0.01999 0.01030 -0.0275 0.1952 1.0000
6.000 0.7586 0.02119 0.01126 -0.0253 0.1683 1.0000
6.250 0.7773 0.02234 0.01225 -0.0237 0.1484 1.0000
6.500 0.7982 0.02353 0.01334 -0.0225 0.1328 1.0000
6.750 0.8217 0.02482 0.01460 -0.0217 0.1204 1.0000
7.000 0.8460 0.02623 0.01600 -0.0211 0.1100 1.0000
7.250 0.8736 0.02807 0.01766 -0.0213 0.1014 1.0000
7.500 0.8952 0.02924 0.01914 -0.0199 0.0945 1.0000
7.750 0.9207 0.03107 0.02091 -0.0198 0.0888 1.0000
8.000 0.9423 0.03312 0.02331 -0.0185 0.0848 1.0000
8.250 0.9617 0.03479 0.02524 -0.0170 0.0804 1.0000
8.500 0.9823 0.03674 0.02730 -0.0160 0.0772 1.0000
8.750 1.0019 0.04031 0.03103 -0.0153 0.0752 1.0000
9.000 1.0125 0.04303 0.03423 -0.0125 0.0744 1.0000
9.250 1.0192 0.04577 0.03747 -0.0094 0.0734 1.0000
9.500 1.0223 0.04881 0.04099 -0.0061 0.0724 1.0000
9.750 1.0223 0.05224 0.04484 -0.0027 0.0719 1.0000
10.000 1.0197 0.05614 0.04909 0.0005 0.0724 1.0000
10.250 1.0153 0.06025 0.05349 0.0034 0.0732 1.0000
10.500 1.0120 0.06472 0.05817 0.0058 0.0741 1.0000
10.750 0.9336 0.05998 0.05383 0.0157 0.0753 1.0000
11.000 0.8354 0.06440 0.05891 0.0246 0.0791 1.0000
11.250 0.7739 0.07262 0.06736 0.0248 0.0826 1.0000
11.500 0.7394 0.08006 0.07489 0.0232 0.0851 1.0000
11.750 0.7230 0.08634 0.08119 0.0219 0.0866 1.0000
12.000 0.6000 0.12204 0.11697 0.0004 0.1597 1.0000
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Polar data table (+)
Polar graphs
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