LOCKHEED C-141 BL0 AIRFOIL (c141a-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: LOCKHEED C-141 BL0 AIRFOIL (c141a-il) Reynolds number: 50,000 Max Cl/Cd: 29.04 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c141a-il-50000.txt Download as CSV file: xf-c141a-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-141 BL0 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 -0.6996 0.07819 0.07080 -0.0356 1.0000 0.1776
-8.750 -0.7635 0.07177 0.06411 -0.0313 1.0000 0.1645
-8.500 -0.7722 0.06784 0.06000 -0.0285 1.0000 0.1624
-8.250 -0.7786 0.06393 0.05593 -0.0257 1.0000 0.1613
-8.000 -0.7847 0.06006 0.05183 -0.0227 1.0000 0.1601
-7.750 -0.7888 0.05626 0.04773 -0.0197 1.0000 0.1590
-7.500 -0.7905 0.05274 0.04381 -0.0167 1.0000 0.1594
-7.250 -0.7893 0.04950 0.04010 -0.0137 1.0000 0.1611
-7.000 -0.7844 0.04650 0.03653 -0.0108 1.0000 0.1629
-6.750 -0.7713 0.04357 0.03339 -0.0090 1.0000 0.1660
-6.500 -0.7549 0.04149 0.03122 -0.0074 1.0000 0.1720
-6.250 -0.7403 0.03924 0.02848 -0.0054 1.0000 0.1774
-6.000 -0.7219 0.03704 0.02607 -0.0040 1.0000 0.1838
-5.750 -0.7022 0.03536 0.02415 -0.0026 1.0000 0.1929
-5.500 -0.6807 0.03357 0.02225 -0.0016 1.0000 0.2024
-5.250 -0.6585 0.03205 0.02053 -0.0005 1.0000 0.2150
-5.000 -0.6350 0.03066 0.01905 0.0004 1.0000 0.2304
-4.750 -0.6105 0.02929 0.01782 0.0012 1.0000 0.2500
-4.500 -0.5864 0.02804 0.01667 0.0020 1.0000 0.2770
-4.250 -0.5624 0.02669 0.01562 0.0030 1.0000 0.3163
-4.000 -0.5411 0.02504 0.01464 0.0043 1.0000 0.3879
-3.750 -0.5333 0.02329 0.01469 0.0100 1.0000 0.5919
-3.500 -0.5251 0.02412 0.01605 0.0192 1.0000 0.7686
-3.250 -0.4891 0.02607 0.01783 0.0236 1.0000 0.8541
-3.000 -0.3052 0.03031 0.02112 0.0020 1.0000 0.9378
-2.750 -0.1000 0.03042 0.02040 -0.0314 1.0000 1.0000
-2.500 -0.0988 0.02987 0.01978 -0.0288 1.0000 1.0000
-2.250 -0.0976 0.02937 0.01921 -0.0260 1.0000 1.0000
-2.000 -0.0965 0.02892 0.01870 -0.0231 1.0000 1.0000
-1.750 -0.0955 0.02851 0.01823 -0.0201 1.0000 1.0000
-1.500 -0.0948 0.02813 0.01780 -0.0171 1.0000 1.0000
-1.250 -0.0943 0.02779 0.01741 -0.0139 1.0000 1.0000
-1.000 -0.0941 0.02748 0.01705 -0.0106 1.0000 1.0000
-0.750 -0.0940 0.02720 0.01673 -0.0072 1.0000 1.0000
-0.500 -0.0939 0.02695 0.01644 -0.0037 1.0000 1.0000
-0.250 -0.0934 0.02675 0.01619 -0.0003 1.0000 1.0000
0.000 -0.0915 0.02660 0.01600 0.0029 1.0000 1.0000
0.250 -0.0878 0.02654 0.01587 0.0059 1.0000 1.0000
0.500 -0.0819 0.02656 0.01583 0.0085 1.0000 1.0000
0.750 -0.0742 0.02666 0.01587 0.0108 1.0000 1.0000
1.000 -0.0647 0.02685 0.01600 0.0128 1.0000 1.0000
1.250 -0.0535 0.02712 0.01622 0.0145 1.0000 1.0000
1.500 -0.0410 0.02746 0.01652 0.0160 1.0000 1.0000
1.750 -0.0274 0.02787 0.01690 0.0172 1.0000 1.0000
2.000 -0.0132 0.02834 0.01736 0.0182 1.0000 1.0000
2.250 0.0016 0.02888 0.01789 0.0191 1.0000 1.0000
2.500 0.0166 0.02948 0.01849 0.0198 1.0000 1.0000
2.750 0.0319 0.03015 0.01916 0.0204 1.0000 1.0000
3.000 0.0472 0.03088 0.01992 0.0210 1.0000 1.0000
3.250 0.0624 0.03167 0.02075 0.0214 1.0000 1.0000
3.500 0.0775 0.03254 0.02167 0.0217 1.0000 1.0000
3.750 0.1477 0.03491 0.02420 0.0115 0.9745 1.0000
4.000 0.2226 0.03688 0.02637 0.0015 0.9424 1.0000
4.250 0.2820 0.03777 0.02749 -0.0048 0.9088 1.0000
4.500 0.3412 0.03808 0.02804 -0.0100 0.8738 1.0000
4.750 0.4055 0.03763 0.02790 -0.0148 0.8374 1.0000
5.000 0.4852 0.03578 0.02646 -0.0202 0.7998 1.0000
5.250 0.5488 0.03307 0.02416 -0.0216 0.7584 1.0000
5.500 0.6429 0.02719 0.01890 -0.0234 0.6966 1.0000
5.750 0.7120 0.02452 0.01476 -0.0212 0.4334 1.0000
6.000 0.7255 0.02656 0.01582 -0.0181 0.3415 1.0000
6.250 0.7607 0.02862 0.01726 -0.0192 0.2838 1.0000
6.500 0.7958 0.03049 0.01893 -0.0203 0.2484 1.0000
6.750 0.8261 0.03229 0.02070 -0.0204 0.2248 1.0000
7.000 0.8539 0.03418 0.02257 -0.0203 0.2074 1.0000
7.250 0.8777 0.03615 0.02464 -0.0195 0.1942 1.0000
7.500 0.9020 0.03835 0.02688 -0.0189 0.1837 1.0000
7.750 0.9183 0.04031 0.02912 -0.0168 0.1749 1.0000
8.000 0.9378 0.04288 0.03179 -0.0155 0.1682 1.0000
8.250 0.9456 0.04524 0.03463 -0.0122 0.1633 1.0000
8.500 0.9601 0.04759 0.03714 -0.0102 0.1575 1.0000
8.750 0.9748 0.05084 0.04047 -0.0087 0.1537 1.0000
9.000 0.9727 0.05374 0.04388 -0.0044 0.1521 1.0000
9.250 0.9674 0.05688 0.04746 -0.0003 0.1506 1.0000
9.500 0.9590 0.06024 0.05120 0.0038 0.1496 1.0000
9.750 0.9475 0.06389 0.05517 0.0078 0.1495 1.0000
10.000 0.9329 0.06784 0.05939 0.0114 0.1504 1.0000
10.250 0.9171 0.07201 0.06375 0.0147 0.1516 1.0000
10.500 0.9019 0.07628 0.06815 0.0175 0.1528 1.0000
10.750 0.8923 0.08090 0.07286 0.0194 0.1539 1.0000
|
Polar data table (+)
Polar graphs
<< Back to LOCKHEED C-141 BL0 AIRFOIL (c141a-il)