NACA 64(3)-218 (naca643218-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64(3)-218 (naca643218-il) Reynolds number: 200,000 Max Cl/Cd: 62.32 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca643218-il-200000.txt Download as CSV file: xf-naca643218-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.6719 0.11613 0.11211 -0.0378 1.0000 0.0508
-15.750 -0.6888 0.10788 0.10382 -0.0418 1.0000 0.0500
-15.500 -0.7464 0.09330 0.08905 -0.0506 1.0000 0.0485
-15.250 -0.9180 0.07045 0.06516 -0.0632 1.0000 0.0446
-15.000 -0.9390 0.06612 0.06061 -0.0640 1.0000 0.0445
-14.750 -0.9553 0.06210 0.05639 -0.0644 1.0000 0.0445
-14.500 -0.9675 0.05839 0.05248 -0.0643 1.0000 0.0446
-14.250 -0.9756 0.05499 0.04887 -0.0640 1.0000 0.0447
-14.000 -0.9780 0.05185 0.04556 -0.0635 1.0000 0.0449
-13.750 -0.9744 0.04910 0.04267 -0.0630 1.0000 0.0451
-13.500 -0.9666 0.04679 0.04025 -0.0625 1.0000 0.0456
-13.250 -0.9590 0.04467 0.03802 -0.0619 1.0000 0.0460
-13.000 -0.9474 0.04285 0.03611 -0.0613 1.0000 0.0466
-12.750 -0.9360 0.04108 0.03421 -0.0607 1.0000 0.0472
-12.500 -0.9251 0.03947 0.03250 -0.0600 1.0000 0.0481
-12.250 -0.9135 0.03783 0.03070 -0.0591 1.0000 0.0490
-12.000 -0.9034 0.03636 0.02905 -0.0581 1.0000 0.0500
-11.750 -0.8934 0.03503 0.02753 -0.0570 1.0000 0.0508
-11.500 -0.8599 0.03336 0.02586 -0.0575 1.0000 0.0522
-11.250 -0.8368 0.03230 0.02487 -0.0572 1.0000 0.0537
-11.000 -0.8171 0.03134 0.02389 -0.0566 1.0000 0.0550
-10.750 -0.7996 0.03043 0.02294 -0.0558 1.0000 0.0566
-10.500 -0.7946 0.02981 0.02225 -0.0535 1.0000 0.0581
-10.250 -0.7770 0.02899 0.02151 -0.0525 0.9946 0.0600
-10.000 -0.7396 0.02787 0.02047 -0.0554 0.9854 0.0632
-9.750 -0.7021 0.02680 0.01930 -0.0584 0.9761 0.0667
-9.500 -0.6677 0.02550 0.01810 -0.0610 0.9665 0.0709
-9.250 -0.6336 0.02444 0.01697 -0.0639 0.9551 0.0763
-9.000 -0.6099 0.02309 0.01569 -0.0653 0.9406 0.0820
-8.750 -0.5929 0.02213 0.01466 -0.0650 0.9245 0.0886
-8.500 -0.5873 0.02113 0.01369 -0.0628 0.9080 0.0956
-8.250 -0.5853 0.02019 0.01273 -0.0598 0.8933 0.1041
-8.000 -0.5858 0.01936 0.01191 -0.0562 0.8791 0.1156
-7.750 -0.5871 0.01853 0.01116 -0.0524 0.8667 0.1327
-7.500 -0.5859 0.01754 0.01033 -0.0490 0.8568 0.1649
-7.250 -0.5854 0.01632 0.00945 -0.0457 0.8457 0.2249
-7.000 -0.5852 0.01496 0.00861 -0.0424 0.8367 0.3214
-6.750 -0.5752 0.01430 0.00850 -0.0398 0.8276 0.4287
-6.500 -0.5530 0.01432 0.00846 -0.0387 0.8210 0.4730
-6.250 -0.5286 0.01445 0.00859 -0.0380 0.8125 0.4981
-6.000 -0.5034 0.01460 0.00863 -0.0372 0.8062 0.5173
-5.750 -0.4774 0.01481 0.00878 -0.0367 0.7992 0.5323
-5.500 -0.4512 0.01499 0.00889 -0.0362 0.7920 0.5459
-5.250 -0.4252 0.01518 0.00893 -0.0356 0.7864 0.5594
-5.000 -0.3974 0.01553 0.00933 -0.0351 0.7792 0.5701
-4.750 -0.3706 0.01568 0.00941 -0.0346 0.7725 0.5803
-4.500 -0.3428 0.01593 0.00958 -0.0341 0.7674 0.5894
-4.250 -0.3159 0.01611 0.00975 -0.0338 0.7601 0.5984
-4.000 -0.2881 0.01646 0.01009 -0.0332 0.7541 0.6084
-3.750 -0.2604 0.01672 0.01030 -0.0326 0.7494 0.6173
-3.500 -0.2327 0.01697 0.01056 -0.0323 0.7431 0.6241
-3.250 -0.2063 0.01678 0.01023 -0.0326 0.7372 0.6305
-3.000 -0.1782 0.01670 0.01009 -0.0325 0.7326 0.6337
-2.750 -0.1502 0.01670 0.01006 -0.0325 0.7277 0.6369
-2.500 -0.1227 0.01665 0.01000 -0.0326 0.7217 0.6407
-2.250 -0.0950 0.01651 0.00976 -0.0329 0.7168 0.6450
-2.000 -0.0669 0.01632 0.00941 -0.0333 0.7128 0.6496
-1.750 -0.0396 0.01631 0.00944 -0.0333 0.7073 0.6524
-1.500 -0.0119 0.01631 0.00945 -0.0333 0.7021 0.6557
-1.250 0.0164 0.01627 0.00935 -0.0335 0.6980 0.6595
-1.000 0.0452 0.01618 0.00916 -0.0339 0.6947 0.6635
-0.750 0.0728 0.01613 0.00907 -0.0345 0.6901 0.6679
-0.500 0.1002 0.01614 0.00913 -0.0345 0.6855 0.6707
-0.250 0.1283 0.01614 0.00914 -0.0347 0.6816 0.6737
0.000 0.1570 0.01613 0.00909 -0.0350 0.6784 0.6772
0.250 0.1860 0.01613 0.00903 -0.0354 0.6753 0.6814
0.500 0.2131 0.01618 0.00909 -0.0359 0.6704 0.6862
0.750 0.2403 0.01624 0.00923 -0.0359 0.6666 0.6894
1.000 0.2682 0.01632 0.00933 -0.0360 0.6633 0.6931
1.250 0.2970 0.01636 0.00936 -0.0363 0.6605 0.6975
1.500 0.3266 0.01642 0.00935 -0.0369 0.6579 0.7026
1.750 0.3524 0.01657 0.00961 -0.0370 0.6536 0.7068
2.000 0.3788 0.01673 0.00987 -0.0369 0.6496 0.7107
2.250 0.4066 0.01681 0.00998 -0.0371 0.6459 0.7155
2.500 0.4359 0.01684 0.00999 -0.0375 0.6428 0.7214
2.750 0.4649 0.01691 0.01006 -0.0377 0.6402 0.7261
3.000 0.4890 0.01719 0.01050 -0.0374 0.6358 0.7310
3.250 0.5152 0.01740 0.01079 -0.0375 0.6316 0.7372
3.500 0.5432 0.01749 0.01092 -0.0377 0.6280 0.7432
3.750 0.5711 0.01756 0.01105 -0.0376 0.6250 0.7480
4.000 0.6005 0.01766 0.01115 -0.0379 0.6222 0.7541
4.250 0.6238 0.01797 0.01161 -0.0377 0.6168 0.7611
4.500 0.6496 0.01796 0.01171 -0.0372 0.6110 0.7663
4.750 0.6811 0.01766 0.01137 -0.0373 0.6057 0.7730
5.000 0.7054 0.01763 0.01145 -0.0368 0.5969 0.7802
5.250 0.7346 0.01723 0.01104 -0.0363 0.5891 0.7862
5.500 0.7598 0.01717 0.01107 -0.0358 0.5805 0.7944
5.750 0.7870 0.01693 0.01087 -0.0353 0.5728 0.8011
6.000 0.8120 0.01682 0.01084 -0.0346 0.5643 0.8087
6.250 0.8398 0.01648 0.01050 -0.0342 0.5539 0.8168
6.500 0.8611 0.01633 0.01048 -0.0328 0.5424 0.8241
6.750 0.8869 0.01610 0.01027 -0.0322 0.5308 0.8331
7.000 0.9088 0.01591 0.01016 -0.0307 0.5188 0.8406
7.250 0.9297 0.01583 0.01019 -0.0295 0.5045 0.8506
7.500 0.9474 0.01573 0.01020 -0.0274 0.4887 0.8595
7.750 0.9653 0.01567 0.01019 -0.0255 0.4690 0.8700
8.000 0.9785 0.01570 0.01030 -0.0228 0.4426 0.8816
8.250 0.9850 0.01583 0.01038 -0.0190 0.3988 0.8941
8.500 0.9780 0.01637 0.01062 -0.0132 0.3443 0.9109
8.750 0.9619 0.01716 0.01120 -0.0064 0.3002 0.9348
9.000 0.9558 0.01879 0.01255 -0.0034 0.2428 0.9719
9.250 0.9530 0.02092 0.01435 -0.0026 0.1934 1.0000
9.500 0.9498 0.02309 0.01626 -0.0014 0.1577 1.0000
9.750 0.9478 0.02526 0.01821 -0.0002 0.1312 1.0000
10.000 0.9479 0.02734 0.02014 0.0009 0.1125 1.0000
10.250 0.9494 0.02935 0.02205 0.0019 0.0995 1.0000
10.500 0.9506 0.03142 0.02400 0.0029 0.0902 1.0000
10.750 0.9579 0.03309 0.02567 0.0036 0.0824 1.0000
11.000 0.9632 0.03491 0.02746 0.0044 0.0766 1.0000
11.250 0.9707 0.03660 0.02912 0.0050 0.0716 1.0000
11.500 0.9783 0.03828 0.03078 0.0057 0.0675 1.0000
11.750 0.9883 0.03980 0.03231 0.0062 0.0638 1.0000
12.000 0.9974 0.04141 0.03379 0.0070 0.0607 1.0000
12.250 1.0097 0.04281 0.03531 0.0074 0.0578 1.0000
12.500 1.0220 0.04421 0.03671 0.0078 0.0554 1.0000
12.750 1.0375 0.04542 0.03779 0.0085 0.0529 1.0000
13.000 1.0502 0.04688 0.03938 0.0089 0.0509 1.0000
13.250 1.0636 0.04830 0.04084 0.0092 0.0488 1.0000
13.500 1.0799 0.04950 0.04197 0.0096 0.0470 1.0000
13.750 1.1018 0.05054 0.04301 0.0102 0.0456 1.0000
14.000 1.1148 0.05218 0.04480 0.0105 0.0443 1.0000
14.250 1.1297 0.05373 0.04647 0.0108 0.0431 1.0000
14.500 1.1442 0.05535 0.04815 0.0111 0.0420 1.0000
14.750 1.1613 0.05682 0.04963 0.0113 0.0411 1.0000
15.000 1.1925 0.05810 0.05086 0.0115 0.0400 1.0000
15.250 1.1919 0.06082 0.05383 0.0117 0.0395 1.0000
15.500 1.1915 0.06372 0.05698 0.0117 0.0390 1.0000
15.750 1.1900 0.06685 0.06035 0.0116 0.0384 1.0000
16.000 1.1883 0.07016 0.06387 0.0113 0.0380 1.0000
16.250 1.1845 0.07377 0.06769 0.0108 0.0376 1.0000
16.500 1.1783 0.07774 0.07187 0.0100 0.0373 1.0000
16.750 1.1687 0.08224 0.07660 0.0089 0.0371 1.0000
17.000 1.1547 0.08750 0.08211 0.0073 0.0371 1.0000
17.250 1.1378 0.09326 0.08811 0.0052 0.0370 1.0000
17.500 1.1141 0.10033 0.09546 0.0021 0.0372 1.0000
17.750 1.0838 0.10885 0.10427 -0.0021 0.0375 1.0000
18.000 1.0467 0.11924 0.11496 -0.0079 0.0379 1.0000
18.250 1.0035 0.13183 0.12781 -0.0156 0.0385 1.0000
18.500 0.9534 0.14763 0.14384 -0.0258 0.0394 1.0000
18.750 0.9256 0.15970 0.15601 -0.0330 0.0401 1.0000
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