NACA 64(3)-218 (naca643218-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64(3)-218 (naca643218-il) Reynolds number: 50,000 Max Cl/Cd: 17.96 at α=10.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca643218-il-50000-n5.txt Download as CSV file: xf-naca643218-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(3)-218
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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.6252 0.10218 0.09421 -0.0472 1.0000 0.0710
-14.000 -0.7244 0.08355 0.07511 -0.0585 1.0000 0.0681
-13.750 -0.7449 0.07796 0.06933 -0.0608 1.0000 0.0683
-13.500 -0.7548 0.07382 0.06504 -0.0621 1.0000 0.0691
-13.250 -0.7636 0.06995 0.06102 -0.0630 1.0000 0.0700
-13.000 -0.7702 0.06635 0.05724 -0.0635 1.0000 0.0708
-12.750 -0.7746 0.06304 0.05374 -0.0638 1.0000 0.0720
-12.500 -0.7760 0.05994 0.05042 -0.0638 1.0000 0.0731
-12.250 -0.7747 0.05707 0.04728 -0.0635 1.0000 0.0746
-12.000 -0.7729 0.05439 0.04429 -0.0631 1.0000 0.0764
-11.750 -0.7535 0.05273 0.04267 -0.0628 1.0000 0.0790
-11.500 -0.7364 0.05113 0.04100 -0.0624 1.0000 0.0820
-11.250 -0.7177 0.04948 0.03916 -0.0618 1.0000 0.0854
-11.000 -0.6935 0.04824 0.03785 -0.0612 1.0000 0.0894
-10.750 -0.6731 0.04717 0.03681 -0.0605 1.0000 0.0943
-10.500 -0.6521 0.04609 0.03554 -0.0597 1.0000 0.0998
-10.250 -0.6346 0.04513 0.03475 -0.0587 1.0000 0.1054
-10.000 -0.6195 0.04411 0.03363 -0.0575 1.0000 0.1126
-9.750 -0.6096 0.04304 0.03276 -0.0561 1.0000 0.1193
-9.500 -0.6024 0.04204 0.03177 -0.0543 1.0000 0.1279
-9.250 -0.6039 0.04106 0.03097 -0.0517 1.0000 0.1353
-9.000 -0.6118 0.04036 0.03035 -0.0480 1.0000 0.1430
-8.750 -0.6296 0.03981 0.02992 -0.0432 1.0000 0.1478
-8.500 -0.6182 0.03807 0.02834 -0.0441 0.9867 0.1664
-8.250 -0.6041 0.03593 0.02645 -0.0461 0.9728 0.1952
-8.000 -0.5944 0.03371 0.02458 -0.0477 0.9590 0.2394
-7.750 -0.5843 0.03227 0.02381 -0.0476 0.9459 0.3093
-7.500 -0.5412 0.03408 0.02620 -0.0469 0.9384 0.4056
-7.250 -0.5266 0.03366 0.02556 -0.0469 0.9255 0.4511
-7.000 -0.5064 0.03411 0.02584 -0.0459 0.9136 0.4822
-6.750 -0.4933 0.03426 0.02579 -0.0442 0.9014 0.5075
-6.500 -0.4488 0.03600 0.02733 -0.0443 0.8950 0.5286
-6.250 -0.4212 0.03705 0.02822 -0.0428 0.8851 0.5460
-6.000 -0.3882 0.03787 0.02885 -0.0423 0.8777 0.5625
-5.750 -0.3751 0.03800 0.02882 -0.0401 0.8669 0.5777
-5.500 -0.3241 0.03929 0.02993 -0.0409 0.8615 0.5863
-5.250 -0.3110 0.03909 0.02958 -0.0391 0.8517 0.5983
-5.000 -0.2823 0.03923 0.02957 -0.0387 0.8442 0.6071
-4.750 -0.2672 0.03892 0.02912 -0.0373 0.8357 0.6165
-4.500 -0.2429 0.03890 0.02897 -0.0366 0.8277 0.6236
-4.250 -0.2330 0.03821 0.02814 -0.0350 0.8204 0.6332
-4.000 -0.2098 0.03831 0.02816 -0.0341 0.8120 0.6383
-3.750 -0.2055 0.03738 0.02709 -0.0322 0.8049 0.6487
-3.500 -0.1826 0.03747 0.02709 -0.0314 0.7971 0.6528
-3.250 -0.1591 0.03733 0.02686 -0.0309 0.7905 0.6578
-3.000 -0.1520 0.03646 0.02584 -0.0293 0.7850 0.6672
-2.750 -0.1354 0.03662 0.02599 -0.0278 0.7767 0.6711
-2.500 -0.1114 0.03650 0.02578 -0.0274 0.7712 0.6757
-2.250 -0.0924 0.03598 0.02515 -0.0268 0.7669 0.6824
-2.000 -0.0901 0.03592 0.02506 -0.0241 0.7577 0.6885
-1.750 -0.0652 0.03585 0.02493 -0.0238 0.7527 0.6926
-1.500 -0.0411 0.03554 0.02453 -0.0237 0.7489 0.6977
-1.250 -0.0452 0.03543 0.02440 -0.0206 0.7406 0.7052
-1.000 -0.0228 0.03551 0.02445 -0.0200 0.7357 0.7088
-0.750 0.0028 0.03538 0.02426 -0.0200 0.7320 0.7130
-0.500 0.0111 0.03542 0.02428 -0.0181 0.7255 0.7188
-0.250 0.0215 0.03543 0.02426 -0.0166 0.7192 0.7248
0.000 0.0461 0.03549 0.02431 -0.0163 0.7154 0.7288
0.250 0.0721 0.03543 0.02421 -0.0164 0.7125 0.7337
0.500 0.0689 0.03587 0.02465 -0.0137 0.7046 0.7407
0.750 0.0874 0.03608 0.02487 -0.0129 0.6997 0.7451
1.000 0.1133 0.03614 0.02494 -0.0128 0.6964 0.7498
1.250 0.1408 0.03610 0.02488 -0.0132 0.6938 0.7559
1.500 0.1323 0.03706 0.02588 -0.0098 0.6849 0.7629
1.750 0.1529 0.03733 0.02619 -0.0092 0.6806 0.7681
2.000 0.1795 0.03738 0.02624 -0.0095 0.6775 0.7742
2.250 0.1851 0.03809 0.02698 -0.0076 0.6712 0.7811
2.500 0.1939 0.03873 0.02767 -0.0058 0.6648 0.7876
2.750 0.2189 0.03889 0.02786 -0.0059 0.6610 0.7954
3.000 0.2490 0.03897 0.02800 -0.0062 0.6583 0.8014
3.250 0.2356 0.04026 0.02934 -0.0024 0.6484 0.8105
3.500 0.2577 0.04059 0.02974 -0.0021 0.6441 0.8180
3.750 0.2879 0.04069 0.02990 -0.0024 0.6410 0.8253
4.000 0.2817 0.04198 0.03126 0.0004 0.6319 0.8356
4.250 0.3025 0.04239 0.03175 0.0010 0.6268 0.8447
4.500 0.3324 0.04246 0.03192 0.0008 0.6234 0.8537
4.750 0.3296 0.04378 0.03332 0.0031 0.6141 0.8661
5.000 0.3525 0.04413 0.03379 0.0035 0.6087 0.8766
5.250 0.3851 0.04414 0.03391 0.0031 0.6052 0.8876
5.500 0.3837 0.04555 0.03544 0.0048 0.5943 0.9029
5.750 0.4164 0.04567 0.03569 0.0041 0.5894 0.9163
6.000 0.4323 0.04676 0.03694 0.0037 0.5797 0.9327
6.250 0.4702 0.04702 0.03737 0.0016 0.5729 0.9476
6.750 0.5421 0.04784 0.03856 -0.0035 0.5549 0.9932
7.000 0.5486 0.04878 0.03953 -0.0027 0.5434 1.0000
7.250 0.5843 0.04818 0.03904 -0.0032 0.5366 1.0000
7.500 0.5926 0.04922 0.04015 -0.0025 0.5231 1.0000
7.750 0.6382 0.04772 0.03879 -0.0029 0.5170 1.0000
8.000 0.6510 0.04831 0.03947 -0.0022 0.5024 1.0000
8.250 0.6658 0.04873 0.03999 -0.0014 0.4873 1.0000
8.750 0.7036 0.04856 0.04004 0.0004 0.4561 1.0000
9.000 0.7224 0.04831 0.03992 0.0014 0.4389 1.0000
9.250 0.7414 0.04792 0.03965 0.0026 0.4199 1.0000
9.500 0.7524 0.04841 0.04025 0.0036 0.3968 1.0000
9.750 0.7738 0.04771 0.03963 0.0049 0.3711 1.0000
10.000 0.8022 0.04625 0.03812 0.0065 0.3368 1.0000
10.250 0.8224 0.04580 0.03741 0.0081 0.2924 1.0000
10.500 0.8321 0.04666 0.03786 0.0096 0.2500 1.0000
10.750 0.8338 0.04866 0.03952 0.0105 0.2172 1.0000
11.000 0.8341 0.05097 0.04157 0.0112 0.1917 1.0000
11.250 0.8354 0.05336 0.04377 0.0117 0.1710 1.0000
11.500 0.8384 0.05571 0.04598 0.0121 0.1538 1.0000
11.750 0.8431 0.05798 0.04812 0.0124 0.1398 1.0000
12.000 0.8495 0.06012 0.05013 0.0127 0.1285 1.0000
12.250 0.8579 0.06218 0.05219 0.0129 0.1181 1.0000
12.500 0.8687 0.06408 0.05410 0.0132 0.1096 1.0000
12.750 0.8800 0.06583 0.05573 0.0135 0.1028 1.0000
13.000 0.8926 0.06775 0.05782 0.0137 0.0959 1.0000
13.250 0.9079 0.06922 0.05918 0.0141 0.0908 1.0000
13.500 0.9204 0.07135 0.06156 0.0142 0.0857 1.0000
13.750 0.9345 0.07317 0.06342 0.0143 0.0816 1.0000
14.000 0.9503 0.07498 0.06529 0.0146 0.0780 1.0000
14.250 0.9572 0.07790 0.06848 0.0143 0.0749 1.0000
14.500 0.9656 0.08052 0.07124 0.0140 0.0722 1.0000
14.750 0.9823 0.08223 0.07290 0.0141 0.0697 1.0000
15.000 0.9769 0.08671 0.07769 0.0129 0.0683 1.0000
15.250 0.9668 0.09187 0.08317 0.0112 0.0671 1.0000
15.500 0.9536 0.09760 0.08919 0.0090 0.0660 1.0000
15.750 0.9363 0.10421 0.09606 0.0060 0.0652 1.0000
16.000 0.9107 0.11269 0.10481 0.0017 0.0650 1.0000
16.250 0.8660 0.12590 0.11831 -0.0060 0.0655 1.0000
16.500 0.8064 0.14562 0.13822 -0.0178 0.0663 1.0000
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