LA2573A (la2573a-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: LA2573A (la2573a-il) Reynolds number: 200,000 Max Cl/Cd: 64.9 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-la2573a-il-200000-n5.txt Download as CSV file: xf-la2573a-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LA2573A
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4933 0.09355 0.08823 0.0128 0.4885 0.0363
-8.750 -0.4960 0.08900 0.08368 0.0102 0.4872 0.0359
-8.500 -0.5047 0.08357 0.07827 0.0064 0.4862 0.0359
-8.250 -0.5226 0.07722 0.07191 0.0012 0.4856 0.0360
-8.000 -0.5418 0.07205 0.06668 -0.0005 0.4849 0.0358
-7.750 -0.5545 0.06652 0.06104 -0.0020 0.4840 0.0357
-7.500 -0.5629 0.06086 0.05520 -0.0027 0.4830 0.0355
-7.250 -0.5673 0.05514 0.04923 -0.0028 0.4819 0.0353
-7.000 -0.5685 0.04940 0.04315 -0.0021 0.4806 0.0352
-6.750 -0.5649 0.04418 0.03754 -0.0010 0.4790 0.0353
-6.500 -0.5578 0.03938 0.03227 0.0005 0.4772 0.0355
-6.250 -0.5480 0.03488 0.02718 0.0022 0.4754 0.0364
-6.000 -0.5344 0.03106 0.02263 0.0039 0.4735 0.0371
-5.750 -0.5131 0.02927 0.02056 0.0048 0.4713 0.0375
-5.500 -0.4896 0.02812 0.01925 0.0055 0.4693 0.0378
-5.250 -0.4654 0.02711 0.01807 0.0061 0.4675 0.0382
-5.000 -0.4408 0.02613 0.01691 0.0066 0.4657 0.0386
-4.750 -0.4156 0.02511 0.01572 0.0072 0.4640 0.0391
-4.500 -0.3898 0.02410 0.01455 0.0077 0.4621 0.0397
-4.250 -0.3636 0.02319 0.01347 0.0082 0.4600 0.0405
-4.000 -0.3369 0.02233 0.01237 0.0087 0.4578 0.0415
-3.750 -0.3101 0.02161 0.01156 0.0090 0.4556 0.0423
-3.500 -0.2831 0.02104 0.01097 0.0094 0.4536 0.0429
-3.250 -0.2560 0.02049 0.01036 0.0097 0.4518 0.0436
-3.000 -0.2288 0.01996 0.00977 0.0101 0.4502 0.0444
-2.750 -0.2016 0.01946 0.00920 0.0104 0.4486 0.0453
-2.500 -0.1745 0.01902 0.00866 0.0108 0.4470 0.0463
-2.250 -0.1475 0.01864 0.00825 0.0112 0.4453 0.0474
-2.000 -0.1204 0.01830 0.00798 0.0115 0.4435 0.0488
-1.750 -0.0933 0.01799 0.00769 0.0118 0.4415 0.0504
-1.500 -0.0662 0.01768 0.00738 0.0122 0.4396 0.0519
-1.250 -0.0395 0.01737 0.00709 0.0126 0.4378 0.0532
-1.000 -0.0127 0.01712 0.00689 0.0130 0.4361 0.0549
-0.750 0.0143 0.01692 0.00669 0.0133 0.4343 0.0573
-0.500 0.0411 0.01671 0.00650 0.0137 0.4325 0.0601
-0.250 0.0681 0.01654 0.00633 0.0141 0.4307 0.0636
0.000 0.0950 0.01638 0.00617 0.0145 0.4291 0.0676
0.250 0.1221 0.01629 0.00606 0.0148 0.4277 0.0735
0.500 0.1489 0.01621 0.00602 0.0151 0.4263 0.0831
0.750 0.1758 0.01606 0.00601 0.0154 0.4246 0.1017
1.000 0.2013 0.01575 0.00602 0.0158 0.4226 0.1668
1.500 0.2375 0.01383 0.00668 0.0213 0.4187 0.9089
1.750 0.2742 0.01413 0.00696 0.0206 0.4167 0.9395
2.000 0.3827 0.01466 0.00735 0.0060 0.4139 0.9753
2.250 0.4354 0.01472 0.00732 0.0013 0.4118 0.9853
2.500 0.4658 0.01477 0.00729 0.0008 0.4101 0.9870
2.750 0.4952 0.01487 0.00732 0.0006 0.4087 0.9885
3.000 0.5249 0.01502 0.00748 0.0001 0.4068 0.9904
3.250 0.5540 0.01516 0.00767 -0.0002 0.4045 0.9920
3.500 0.5822 0.01530 0.00783 -0.0004 0.4020 0.9934
3.750 0.6127 0.01540 0.00795 -0.0010 0.3997 0.9948
4.000 0.6428 0.01551 0.00806 -0.0015 0.3977 0.9963
4.250 0.6720 0.01560 0.00814 -0.0018 0.3957 0.9977
4.500 0.7010 0.01567 0.00818 -0.0020 0.3938 0.9990
4.750 0.7296 0.01576 0.00824 -0.0022 0.3922 1.0000
5.000 0.7538 0.01593 0.00840 -0.0015 0.3905 1.0000
5.250 0.7776 0.01620 0.00880 -0.0010 0.3877 1.0000
5.500 0.8012 0.01643 0.00911 -0.0003 0.3848 1.0000
5.750 0.8249 0.01661 0.00934 0.0003 0.3822 1.0000
6.000 0.8485 0.01673 0.00949 0.0011 0.3798 1.0000
6.250 0.8722 0.01682 0.00958 0.0019 0.3777 1.0000
6.500 0.8958 0.01690 0.00964 0.0028 0.3759 1.0000
6.750 0.9190 0.01706 0.00984 0.0036 0.3736 1.0000
7.000 0.9409 0.01742 0.01035 0.0043 0.3699 1.0000
7.250 0.9632 0.01762 0.01065 0.0052 0.3665 1.0000
7.500 0.9859 0.01773 0.01080 0.0061 0.3636 1.0000
7.750 1.0089 0.01774 0.01082 0.0070 0.3610 1.0000
8.000 1.0321 0.01774 0.01080 0.0080 0.3586 1.0000
8.250 1.0522 0.01811 0.01137 0.0090 0.3528 1.0000
8.500 1.0755 0.01781 0.01107 0.0100 0.3458 1.0000
8.750 1.0972 0.01775 0.01107 0.0110 0.3355 1.0000
9.000 1.1197 0.01764 0.01096 0.0120 0.3259 1.0000
9.250 1.1412 0.01778 0.01114 0.0129 0.3169 1.0000
9.500 1.1623 0.01801 0.01144 0.0138 0.3078 1.0000
9.750 1.1832 0.01823 0.01165 0.0147 0.2981 1.0000
10.000 1.2032 0.01857 0.01200 0.0156 0.2865 1.0000
10.250 1.2221 0.01902 0.01246 0.0166 0.2730 1.0000
10.500 1.2392 0.01962 0.01303 0.0175 0.2573 1.0000
10.750 1.2535 0.02046 0.01384 0.0185 0.2390 1.0000
11.000 1.2628 0.02166 0.01497 0.0196 0.2187 1.0000
11.250 1.2647 0.02337 0.01662 0.0209 0.1996 1.0000
11.500 1.2540 0.02594 0.01920 0.0219 0.1857 1.0000
11.750 1.2332 0.03014 0.02344 0.0211 0.1756 1.0000
12.000 1.2153 0.03437 0.02767 0.0204 0.1650 1.0000
12.250 1.1971 0.03857 0.03185 0.0198 0.1543 1.0000
12.500 1.1812 0.04254 0.03579 0.0193 0.1443 1.0000
12.750 1.1658 0.04650 0.03971 0.0187 0.1341 1.0000
13.250 1.1412 0.05398 0.04713 0.0175 0.1144 1.0000
13.500 1.1332 0.05753 0.05065 0.0168 0.1053 1.0000
13.750 1.1262 0.06113 0.05423 0.0160 0.0970 1.0000
14.000 1.1210 0.06461 0.05769 0.0151 0.0898 1.0000
14.250 1.1163 0.06813 0.06119 0.0142 0.0836 1.0000
14.500 1.1143 0.07137 0.06444 0.0134 0.0781 1.0000
14.750 1.1118 0.07475 0.06781 0.0124 0.0739 1.0000
15.000 1.1108 0.07799 0.07107 0.0115 0.0694 1.0000
15.250 1.1095 0.08131 0.07440 0.0106 0.0662 1.0000
15.500 1.1100 0.08445 0.07758 0.0096 0.0630 1.0000
15.750 1.1090 0.08782 0.08095 0.0086 0.0602 1.0000
16.000 1.1106 0.09088 0.08406 0.0076 0.0580 1.0000
16.250 1.1118 0.09403 0.08724 0.0066 0.0557 1.0000
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Polar data table (+)
Polar graphs
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