NASA/LANGLEY LS(1)-0421 AIRFOIL (ls421-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0421 AIRFOIL (ls421-il) Reynolds number: 50,000 Max Cl/Cd: 18.35 at α=10° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ls421-il-50000-n5.txt Download as CSV file: xf-ls421-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0421 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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.5024 0.11241 0.10406 -0.0736 1.0000 0.0821
-14.250 -0.5791 0.09830 0.08977 -0.0789 1.0000 0.0817
-14.000 -0.6367 0.09029 0.08161 -0.0800 1.0000 0.0812
-13.750 -0.6840 0.08478 0.07592 -0.0792 1.0000 0.0810
-13.500 -0.7240 0.08052 0.07151 -0.0774 1.0000 0.0809
-13.250 -0.7592 0.07699 0.06781 -0.0750 1.0000 0.0810
-13.000 -0.7805 0.07206 0.06251 -0.0762 0.9951 0.0818
-12.750 -0.7842 0.06857 0.05879 -0.0774 0.9904 0.0831
-12.500 -0.7723 0.06658 0.05675 -0.0781 0.9856 0.0849
-12.250 -0.7662 0.06403 0.05402 -0.0790 0.9808 0.0868
-12.000 -0.7619 0.06137 0.05108 -0.0795 0.9762 0.0888
-11.750 -0.7611 0.05889 0.04824 -0.0790 0.9704 0.0906
-11.500 -0.7378 0.05767 0.04711 -0.0797 0.9669 0.0932
-11.250 -0.7204 0.05606 0.04537 -0.0804 0.9636 0.0965
-11.000 -0.7129 0.05443 0.04343 -0.0793 0.9585 0.0996
-10.750 -0.6898 0.05350 0.04261 -0.0794 0.9545 0.1028
-10.500 -0.6683 0.05228 0.04125 -0.0798 0.9507 0.1073
-10.250 -0.6414 0.05122 0.04019 -0.0807 0.9478 0.1124
-10.000 -0.6200 0.05030 0.03914 -0.0806 0.9443 0.1182
-9.750 -0.6067 0.04963 0.03853 -0.0790 0.9395 0.1232
-9.500 -0.5903 0.04884 0.03765 -0.0783 0.9355 0.1303
-9.250 -0.5706 0.04801 0.03691 -0.0781 0.9322 0.1380
-9.000 -0.5491 0.04708 0.03599 -0.0784 0.9293 0.1481
-8.750 -0.5446 0.04646 0.03533 -0.0757 0.9239 0.1574
-8.500 -0.5420 0.04577 0.03477 -0.0730 0.9183 0.1662
-8.250 -0.5346 0.04496 0.03405 -0.0711 0.9142 0.1786
-8.000 -0.5248 0.04406 0.03325 -0.0699 0.9109 0.1945
-7.750 -0.5235 0.04330 0.03260 -0.0671 0.9063 0.2102
-7.500 -0.5294 0.04265 0.03206 -0.0631 0.9000 0.2257
-7.250 -0.5251 0.04174 0.03134 -0.0610 0.8953 0.2496
-7.000 -0.5159 0.04080 0.03061 -0.0598 0.8918 0.2823
-6.750 -0.5022 0.03995 0.03004 -0.0590 0.8891 0.3242
-6.500 -0.5077 0.03957 0.02987 -0.0545 0.8835 0.3555
-6.250 -0.4999 0.03940 0.03001 -0.0515 0.8787 0.3977
-6.000 -0.4809 0.03997 0.03090 -0.0491 0.8751 0.4431
-5.750 -0.4561 0.04109 0.03218 -0.0470 0.8724 0.4823
-5.500 -0.4270 0.04242 0.03352 -0.0456 0.8699 0.5142
-5.250 -0.4023 0.04327 0.03427 -0.0446 0.8670 0.5425
-5.000 -0.4034 0.04380 0.03476 -0.0399 0.8610 0.5621
-4.750 -0.3894 0.04455 0.03541 -0.0374 0.8567 0.5823
-4.500 -0.3700 0.04532 0.03606 -0.0358 0.8531 0.6017
-4.250 -0.3458 0.04604 0.03664 -0.0349 0.8498 0.6203
-4.000 -0.3181 0.04667 0.03712 -0.0347 0.8471 0.6387
-3.750 -0.3073 0.04781 0.03824 -0.0306 0.8425 0.6481
-3.250 -0.2826 0.04859 0.03883 -0.0261 0.8330 0.6785
-3.000 -0.2571 0.04941 0.03958 -0.0244 0.8295 0.6877
-2.750 -0.2324 0.04948 0.03951 -0.0247 0.8265 0.7024
-2.500 -0.2117 0.05008 0.04005 -0.0228 0.8228 0.7097
-2.250 -0.2106 0.04997 0.03988 -0.0202 0.8162 0.7230
-2.000 -0.1909 0.05041 0.04027 -0.0182 0.8117 0.7292
-1.750 -0.1670 0.05055 0.04032 -0.0179 0.8078 0.7390
-1.500 -0.1385 0.05059 0.04027 -0.0185 0.8045 0.7480
-1.250 -0.1291 0.05089 0.04053 -0.0157 0.7987 0.7555
-1.000 -0.1178 0.05089 0.04047 -0.0147 0.7923 0.7661
-0.750 -0.0948 0.05110 0.04063 -0.0135 0.7877 0.7720
-0.500 -0.0656 0.05115 0.04062 -0.0141 0.7839 0.7798
-0.250 -0.0515 0.05127 0.04068 -0.0131 0.7780 0.7879
0.000 -0.0400 0.05146 0.04086 -0.0108 0.7708 0.7936
0.250 -0.0143 0.05149 0.04085 -0.0111 0.7657 0.8003
0.500 0.0188 0.05145 0.04074 -0.0130 0.7620 0.8068
0.750 0.0234 0.05173 0.04103 -0.0100 0.7531 0.8116
1.000 0.0453 0.05183 0.04110 -0.0098 0.7468 0.8168
1.250 0.0782 0.05179 0.04102 -0.0113 0.7423 0.8222
1.500 0.0914 0.05208 0.04131 -0.0104 0.7339 0.8269
1.750 0.1117 0.05218 0.04141 -0.0097 0.7265 0.8310
2.000 0.1447 0.05208 0.04128 -0.0108 0.7217 0.8352
2.500 0.1849 0.05256 0.04176 -0.0110 0.7047 0.8437
2.750 0.2203 0.05227 0.04147 -0.0120 0.7004 0.8469
3.000 0.2256 0.05281 0.04206 -0.0100 0.6878 0.8507
3.250 0.2610 0.05259 0.04183 -0.0114 0.6822 0.8538
3.500 0.2743 0.05308 0.04236 -0.0107 0.6704 0.8577
3.750 0.3092 0.05292 0.04222 -0.0123 0.6637 0.8612
4.000 0.3236 0.05323 0.04258 -0.0111 0.6523 0.8644
4.250 0.3546 0.05295 0.04233 -0.0118 0.6447 0.8672
4.500 0.3712 0.05332 0.04275 -0.0113 0.6327 0.8704
4.750 0.4054 0.05290 0.04237 -0.0122 0.6251 0.8738
5.000 0.4223 0.05341 0.04293 -0.0120 0.6117 0.8774
5.250 0.4581 0.05258 0.04216 -0.0126 0.6049 0.8805
5.500 0.4712 0.05305 0.04270 -0.0116 0.5901 0.8837
6.000 0.5278 0.05224 0.04201 -0.0120 0.5683 0.8898
6.250 0.5473 0.05249 0.04233 -0.0117 0.5533 0.8934
6.500 0.5869 0.05081 0.04071 -0.0119 0.5468 0.8969
6.750 0.6020 0.05106 0.04104 -0.0108 0.5305 0.9008
7.250 0.6523 0.05032 0.04045 -0.0104 0.5030 0.9081
7.750 0.7054 0.04913 0.03937 -0.0095 0.4738 0.9152
8.000 0.7306 0.04874 0.03901 -0.0091 0.4571 0.9195
8.250 0.7594 0.04817 0.03843 -0.0089 0.4400 0.9242
8.500 0.7860 0.04753 0.03777 -0.0083 0.4218 0.9290
8.750 0.8117 0.04719 0.03736 -0.0078 0.4024 0.9341
9.250 0.8552 0.04748 0.03748 -0.0068 0.3622 0.9441
9.500 0.8738 0.04803 0.03793 -0.0063 0.3431 0.9495
9.750 0.8911 0.04872 0.03853 -0.0058 0.3254 0.9553
10.000 0.9078 0.04946 0.03916 -0.0054 0.3092 0.9625
10.250 0.9227 0.05043 0.04009 -0.0050 0.2939 0.9710
10.500 0.9339 0.05157 0.04125 -0.0046 0.2799 0.9845
10.750 0.9481 0.05254 0.04218 -0.0044 0.2676 1.0000
11.000 0.9686 0.05370 0.04324 -0.0050 0.2560 1.0000
11.250 0.9839 0.05545 0.04507 -0.0055 0.2447 1.0000
11.500 1.0052 0.05662 0.04614 -0.0062 0.2352 1.0000
11.750 1.0205 0.05844 0.04807 -0.0068 0.2258 1.0000
12.000 1.0419 0.05966 0.04922 -0.0074 0.2178 1.0000
12.250 1.0553 0.06170 0.05140 -0.0080 0.2098 1.0000
12.500 1.0817 0.06250 0.05204 -0.0087 0.2030 1.0000
12.750 1.0887 0.06521 0.05502 -0.0092 0.1963 1.0000
13.000 1.1073 0.06674 0.05655 -0.0099 0.1902 1.0000
13.250 1.1242 0.06853 0.05838 -0.0105 0.1848 1.0000
13.500 1.1290 0.07147 0.06154 -0.0110 0.1795 1.0000
13.750 1.1464 0.07309 0.06315 -0.0115 0.1746 1.0000
14.000 1.1589 0.07533 0.06546 -0.0121 0.1703 1.0000
14.250 1.1533 0.07946 0.06988 -0.0127 0.1662 1.0000
14.500 1.1583 0.08242 0.07295 -0.0134 0.1621 1.0000
14.750 1.1887 0.08261 0.07300 -0.0139 0.1582 1.0000
15.000 1.1628 0.08921 0.08000 -0.0151 0.1554 1.0000
15.250 1.1340 0.09667 0.08782 -0.0171 0.1525 1.0000
15.500 1.1108 0.10385 0.09524 -0.0196 0.1495 1.0000
15.750 1.1311 0.10482 0.09618 -0.0201 0.1464 1.0000
16.000 1.1001 0.11368 0.10528 -0.0239 0.1439 1.0000
16.500 0.9394 0.15630 0.14849 -0.0473 0.1333 1.0000
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Polar data table (+)
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