NACA 64(3)-618 (naca643618-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64(3)-618 (naca643618-il) Reynolds number: 100,000 Max Cl/Cd: 41.75 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca643618-il-100000-n5.txt Download as CSV file: xf-naca643618-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(3)-618
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.4953 0.08793 0.08226 -0.0808 1.0000 0.0450
-13.500 -0.5461 0.07728 0.07146 -0.0869 1.0000 0.0445
-13.250 -0.5858 0.07023 0.06428 -0.0900 1.0000 0.0442
-13.000 -0.6196 0.06520 0.05912 -0.0910 1.0000 0.0442
-12.750 -0.6501 0.06173 0.05555 -0.0900 1.0000 0.0441
-12.500 -0.6778 0.05877 0.05248 -0.0886 0.9982 0.0441
-12.250 -0.6841 0.05377 0.04710 -0.0934 0.9861 0.0446
-12.000 -0.6860 0.04967 0.04260 -0.0968 0.9742 0.0451
-11.750 -0.6863 0.04618 0.03864 -0.0993 0.9619 0.0459
-11.500 -0.6615 0.04415 0.03655 -0.1019 0.9562 0.0469
-11.250 -0.6440 0.04242 0.03470 -0.1031 0.9463 0.0480
-11.000 -0.6227 0.04039 0.03246 -0.1049 0.9390 0.0493
-10.750 -0.6042 0.03844 0.03026 -0.1057 0.9295 0.0505
-10.500 -0.5782 0.03638 0.02784 -0.1074 0.9240 0.0519
-10.250 -0.5576 0.03502 0.02638 -0.1073 0.9143 0.0532
-10.000 -0.5292 0.03377 0.02509 -0.1087 0.9082 0.0549
-9.750 -0.5075 0.03267 0.02387 -0.1086 0.8995 0.0568
-9.500 -0.4807 0.03147 0.02248 -0.1091 0.8924 0.0586
-9.250 -0.4531 0.03035 0.02125 -0.1095 0.8859 0.0604
-9.000 -0.4323 0.02951 0.02045 -0.1091 0.8769 0.0625
-8.750 -0.4060 0.02861 0.01946 -0.1094 0.8708 0.0653
-8.500 -0.3875 0.02794 0.01867 -0.1083 0.8613 0.0680
-8.250 -0.3653 0.02709 0.01786 -0.1080 0.8542 0.0705
-8.000 -0.3477 0.02644 0.01719 -0.1069 0.8458 0.0736
-7.750 -0.3281 0.02583 0.01648 -0.1060 0.8379 0.0778
-7.500 -0.3096 0.02508 0.01575 -0.1053 0.8311 0.0821
-7.250 -0.2941 0.02455 0.01518 -0.1038 0.8222 0.0871
-7.000 -0.2750 0.02382 0.01445 -0.1032 0.8159 0.0937
-6.750 -0.2594 0.02328 0.01389 -0.1018 0.8078 0.1021
-6.500 -0.2412 0.02264 0.01324 -0.1009 0.8006 0.1136
-6.250 -0.2210 0.02185 0.01251 -0.1006 0.7951 0.1315
-6.000 -0.2064 0.02119 0.01199 -0.0993 0.7867 0.1577
-5.750 -0.1877 0.02020 0.01123 -0.0991 0.7805 0.2083
-5.500 -0.1705 0.01901 0.01056 -0.0989 0.7745 0.3056
-5.250 -0.1519 0.01872 0.01089 -0.0976 0.7672 0.4223
-5.000 -0.1243 0.01875 0.01086 -0.0975 0.7620 0.4756
-4.750 -0.0959 0.01884 0.01080 -0.0976 0.7573 0.5071
-4.500 -0.0722 0.01910 0.01104 -0.0967 0.7503 0.5278
-4.250 -0.0450 0.01932 0.01115 -0.0962 0.7449 0.5465
-4.000 -0.0159 0.01950 0.01121 -0.0961 0.7407 0.5636
-3.750 0.0068 0.01989 0.01157 -0.0948 0.7338 0.5796
-3.500 0.0311 0.02037 0.01206 -0.0932 0.7283 0.5935
-3.250 0.0586 0.02058 0.01218 -0.0926 0.7241 0.6051
-3.000 0.0845 0.02065 0.01217 -0.0922 0.7192 0.6119
-2.750 0.1111 0.02050 0.01188 -0.0928 0.7134 0.6191
-2.500 0.1378 0.02052 0.01184 -0.0924 0.7089 0.6224
-2.250 0.1668 0.02047 0.01169 -0.0925 0.7053 0.6263
-2.000 0.1922 0.02048 0.01164 -0.0924 0.7001 0.6311
-1.750 0.2194 0.02040 0.01145 -0.0929 0.6946 0.6370
-1.500 0.2471 0.02036 0.01135 -0.0929 0.6903 0.6406
-1.250 0.2764 0.02031 0.01122 -0.0931 0.6870 0.6440
-1.000 0.3008 0.02040 0.01130 -0.0928 0.6819 0.6480
-0.750 0.3269 0.02044 0.01130 -0.0930 0.6771 0.6525
-0.500 0.3569 0.02038 0.01113 -0.0940 0.6733 0.6573
-0.250 0.3852 0.02039 0.01112 -0.0940 0.6702 0.6603
0.000 0.4126 0.02046 0.01116 -0.0940 0.6669 0.6639
0.250 0.4352 0.02066 0.01141 -0.0936 0.6619 0.6680
0.500 0.4623 0.02074 0.01146 -0.0939 0.6576 0.6726
0.750 0.4922 0.02075 0.01141 -0.0946 0.6542 0.6772
1.000 0.5211 0.02077 0.01142 -0.0948 0.6514 0.6804
1.250 0.5450 0.02100 0.01169 -0.0944 0.6476 0.6845
1.500 0.5676 0.02128 0.01203 -0.0940 0.6432 0.6897
1.750 0.5951 0.02146 0.01220 -0.0945 0.6396 0.6957
2.000 0.6212 0.02160 0.01239 -0.0942 0.6366 0.6994
2.250 0.6503 0.02167 0.01247 -0.0945 0.6341 0.7038
2.500 0.6761 0.02189 0.01273 -0.0945 0.6307 0.7091
2.750 0.6963 0.02234 0.01326 -0.0939 0.6260 0.7152
3.000 0.7182 0.02265 0.01365 -0.0931 0.6223 0.7194
3.250 0.7444 0.02283 0.01389 -0.0930 0.6192 0.7249
3.500 0.7751 0.02292 0.01399 -0.0937 0.6166 0.7318
3.750 0.8011 0.02313 0.01426 -0.0936 0.6137 0.7374
4.000 0.8127 0.02381 0.01510 -0.0915 0.6078 0.7436
4.250 0.8372 0.02411 0.01547 -0.0913 0.6037 0.7510
4.500 0.8637 0.02424 0.01568 -0.0912 0.6006 0.7567
4.750 0.8941 0.02429 0.01578 -0.0916 0.5982 0.7632
5.000 0.9083 0.02501 0.01663 -0.0901 0.5930 0.7712
5.250 0.9211 0.02562 0.01739 -0.0880 0.5878 0.7779
5.500 0.9471 0.02583 0.01769 -0.0879 0.5842 0.7863
5.750 0.9770 0.02582 0.01776 -0.0882 0.5814 0.7939
6.000 0.9936 0.02634 0.01840 -0.0867 0.5767 0.8030
6.250 0.9980 0.02721 0.01944 -0.0836 0.5700 0.8121
6.500 1.0279 0.02708 0.01940 -0.0838 0.5657 0.8215
6.750 1.0668 0.02648 0.01884 -0.0848 0.5616 0.8302
7.000 1.0553 0.02769 0.02026 -0.0796 0.5519 0.8429
7.250 1.0913 0.02701 0.01965 -0.0800 0.5467 0.8532
7.500 1.0864 0.02775 0.02055 -0.0752 0.5384 0.8675
7.750 1.1106 0.02726 0.02014 -0.0740 0.5304 0.8817
8.000 1.1103 0.02774 0.02075 -0.0698 0.5213 0.9023
8.250 1.1340 0.02716 0.02027 -0.0685 0.5123 0.9261
8.500 1.1293 0.02823 0.02151 -0.0651 0.5015 1.0000
8.750 1.1603 0.02788 0.02119 -0.0656 0.4912 1.0000
9.000 1.1676 0.02882 0.02222 -0.0640 0.4785 1.0000
9.250 1.1657 0.03042 0.02392 -0.0618 0.4645 1.0000
9.500 1.1671 0.03195 0.02552 -0.0600 0.4489 1.0000
9.750 1.1664 0.03376 0.02739 -0.0583 0.4310 1.0000
10.000 1.1681 0.03546 0.02911 -0.0569 0.4096 1.0000
10.250 1.1732 0.03692 0.03054 -0.0556 0.3818 1.0000
10.500 1.1908 0.03709 0.03044 -0.0544 0.3447 1.0000
10.750 1.1931 0.03882 0.03193 -0.0529 0.3088 1.0000
11.000 1.1900 0.04121 0.03411 -0.0514 0.2762 1.0000
11.250 1.1844 0.04399 0.03670 -0.0501 0.2469 1.0000
11.500 1.1792 0.04693 0.03948 -0.0490 0.2207 1.0000
11.750 1.1749 0.04993 0.04237 -0.0483 0.1974 1.0000
12.000 1.1724 0.05289 0.04522 -0.0477 0.1760 1.0000
12.250 1.1703 0.05590 0.04813 -0.0473 0.1568 1.0000
12.500 1.1696 0.05885 0.05100 -0.0470 0.1400 1.0000
12.750 1.1703 0.06174 0.05384 -0.0468 0.1248 1.0000
13.000 1.1713 0.06467 0.05671 -0.0468 0.1119 1.0000
13.250 1.1726 0.06762 0.05961 -0.0468 0.1009 1.0000
13.500 1.1756 0.07043 0.06244 -0.0469 0.0913 1.0000
13.750 1.1786 0.07328 0.06531 -0.0470 0.0832 1.0000
14.000 1.1806 0.07631 0.06831 -0.0472 0.0769 1.0000
14.250 1.1843 0.07918 0.07122 -0.0475 0.0710 1.0000
14.500 1.1878 0.08210 0.07416 -0.0478 0.0661 1.0000
14.750 1.1913 0.08505 0.07716 -0.0482 0.0620 1.0000
15.000 1.1955 0.08793 0.08008 -0.0486 0.0583 1.0000
15.250 1.1998 0.09084 0.08305 -0.0492 0.0549 1.0000
15.500 1.2036 0.09382 0.08605 -0.0497 0.0523 1.0000
15.750 1.2095 0.09654 0.08888 -0.0502 0.0495 1.0000
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