NACA 63(3)-218 (naca633218-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 63(3)-218 (naca633218-il) Reynolds number: 50,000 Max Cl/Cd: 21.77 at α=10.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca633218-il-50000-n5.txt Download as CSV file: xf-naca633218-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.6128 0.11627 0.10866 -0.0325 1.0000 0.0814
-14.500 -0.6777 0.09854 0.09078 -0.0429 1.0000 0.0808
-14.250 -0.7256 0.08696 0.07895 -0.0496 1.0000 0.0803
-14.000 -0.7557 0.07938 0.07112 -0.0534 1.0000 0.0806
-13.750 -0.7771 0.07349 0.06498 -0.0559 1.0000 0.0814
-13.500 -0.7926 0.06861 0.05982 -0.0576 1.0000 0.0824
-13.250 -0.8042 0.06437 0.05527 -0.0586 1.0000 0.0836
-13.000 -0.7904 0.06228 0.05317 -0.0585 1.0000 0.0858
-12.750 -0.7792 0.06022 0.05108 -0.0584 1.0000 0.0883
-12.500 -0.7723 0.05785 0.04856 -0.0585 1.0000 0.0912
-12.250 -0.7661 0.05537 0.04585 -0.0584 1.0000 0.0944
-12.000 -0.7486 0.05377 0.04421 -0.0580 1.0000 0.0980
-11.750 -0.7309 0.05242 0.04287 -0.0575 1.0000 0.1020
-11.500 -0.7180 0.05071 0.04102 -0.0571 1.0000 0.1071
-11.250 -0.7026 0.04934 0.03967 -0.0565 1.0000 0.1124
-11.000 -0.6893 0.04794 0.03828 -0.0559 1.0000 0.1186
-10.750 -0.6760 0.04653 0.03685 -0.0552 1.0000 0.1255
-10.500 -0.6664 0.04506 0.03547 -0.0544 1.0000 0.1337
-10.250 -0.6586 0.04353 0.03404 -0.0536 1.0000 0.1431
-10.000 -0.6520 0.04201 0.03255 -0.0527 1.0000 0.1545
-9.750 -0.6502 0.04043 0.03115 -0.0514 1.0000 0.1667
-9.500 -0.6516 0.03892 0.02985 -0.0497 1.0000 0.1801
-9.250 -0.6587 0.03762 0.02874 -0.0471 1.0000 0.1937
-9.000 -0.6744 0.03667 0.02793 -0.0430 0.9995 0.2057
-8.750 -0.6620 0.03473 0.02624 -0.0448 0.9754 0.2384
-8.500 -0.6468 0.03327 0.02509 -0.0461 0.9585 0.2796
-8.250 -0.6274 0.03255 0.02464 -0.0466 0.9439 0.3259
-8.000 -0.6004 0.03272 0.02494 -0.0468 0.9318 0.3690
-7.750 -0.5742 0.03288 0.02503 -0.0470 0.9207 0.4041
-7.500 -0.5581 0.03281 0.02480 -0.0460 0.9072 0.4310
-7.250 -0.5287 0.03365 0.02553 -0.0452 0.8967 0.4527
-7.000 -0.4996 0.03429 0.02600 -0.0445 0.8867 0.4715
-6.750 -0.4785 0.03463 0.02620 -0.0430 0.8753 0.4876
-6.500 -0.4570 0.03472 0.02611 -0.0419 0.8656 0.5034
-6.250 -0.4338 0.03510 0.02635 -0.0405 0.8548 0.5163
-6.000 -0.3997 0.03582 0.02691 -0.0397 0.8470 0.5265
-5.750 -0.3883 0.03547 0.02643 -0.0379 0.8364 0.5401
-5.500 -0.3548 0.03601 0.02682 -0.0372 0.8296 0.5492
-5.250 -0.3403 0.03577 0.02648 -0.0355 0.8196 0.5601
-5.000 -0.3158 0.03573 0.02630 -0.0346 0.8126 0.5694
-4.750 -0.2996 0.03544 0.02591 -0.0332 0.8035 0.5787
-4.500 -0.2754 0.03537 0.02572 -0.0323 0.7961 0.5865
-4.250 -0.2620 0.03478 0.02501 -0.0309 0.7880 0.5962
-4.000 -0.2367 0.03479 0.02495 -0.0300 0.7794 0.6023
-3.750 -0.2254 0.03393 0.02393 -0.0287 0.7724 0.6132
-3.500 -0.2006 0.03404 0.02400 -0.0276 0.7630 0.6181
-3.250 -0.1800 0.03363 0.02347 -0.0267 0.7558 0.6260
-3.000 -0.1652 0.03319 0.02297 -0.0254 0.7468 0.6339
-2.750 -0.1402 0.03308 0.02278 -0.0246 0.7392 0.6394
-2.500 -0.1273 0.03237 0.02195 -0.0234 0.7310 0.6494
-2.250 -0.1030 0.03228 0.02183 -0.0224 0.7213 0.6542
-2.000 -0.0787 0.03200 0.02146 -0.0216 0.7128 0.6599
-1.750 -0.0660 0.03137 0.02074 -0.0204 0.7022 0.6695
-1.500 -0.0393 0.03123 0.02055 -0.0196 0.6938 0.6738
-1.250 -0.0185 0.03103 0.02033 -0.0186 0.6839 0.6797
-1.000 0.0008 0.03041 0.01959 -0.0181 0.6772 0.6886
-0.750 0.0223 0.03044 0.01965 -0.0169 0.6669 0.6930
-0.500 0.0479 0.03015 0.01930 -0.0164 0.6599 0.6988
-0.250 0.0628 0.02982 0.01894 -0.0155 0.6493 0.7076
0.000 0.0896 0.02965 0.01874 -0.0148 0.6418 0.7120
0.250 0.1093 0.02960 0.01871 -0.0137 0.6311 0.7182
0.500 0.1317 0.02917 0.01819 -0.0134 0.6232 0.7267
0.750 0.1524 0.02921 0.01828 -0.0123 0.6122 0.7316
1.000 0.1780 0.02898 0.01801 -0.0117 0.6044 0.7379
1.250 0.1956 0.02888 0.01791 -0.0109 0.5931 0.7465
1.500 0.2224 0.02873 0.01773 -0.0103 0.5857 0.7516
1.750 0.2412 0.02879 0.01784 -0.0093 0.5743 0.7588
2.000 0.2667 0.02854 0.01752 -0.0090 0.5671 0.7666
2.250 0.2851 0.02872 0.01776 -0.0077 0.5560 0.7730
2.500 0.3105 0.02854 0.01753 -0.0074 0.5493 0.7812
2.750 0.3283 0.02874 0.01778 -0.0063 0.5391 0.7883
3.000 0.3528 0.02868 0.01770 -0.0057 0.5325 0.7960
3.250 0.3717 0.02885 0.01791 -0.0048 0.5242 0.8046
3.500 0.3933 0.02895 0.01805 -0.0039 0.5174 0.8121
3.750 0.4189 0.02887 0.01793 -0.0037 0.5127 0.8215
4.000 0.4341 0.02932 0.01850 -0.0022 0.5054 0.8296
4.250 0.4546 0.02953 0.01875 -0.0016 0.5003 0.8396
4.500 0.4786 0.02965 0.01892 -0.0010 0.4967 0.8479
4.750 0.4998 0.02991 0.01923 -0.0005 0.4932 0.8584
5.000 0.5136 0.03055 0.02003 0.0008 0.4883 0.8689
5.250 0.5317 0.03102 0.02060 0.0016 0.4844 0.8799
5.500 0.5530 0.03134 0.02100 0.0021 0.4811 0.8920
5.750 0.5803 0.03154 0.02131 0.0019 0.4785 0.9032
6.000 0.6002 0.03218 0.02208 0.0020 0.4746 0.9165
6.250 0.6156 0.03329 0.02339 0.0018 0.4699 0.9318
6.500 0.6428 0.03408 0.02434 0.0003 0.4661 0.9469
6.750 0.6798 0.03458 0.02500 -0.0023 0.4630 0.9612
7.000 0.7243 0.03468 0.02524 -0.0055 0.4602 0.9754
7.250 0.7163 0.03676 0.02747 -0.0043 0.4546 1.0000
7.500 0.7076 0.03867 0.02944 -0.0025 0.4496 1.0000
7.750 0.7280 0.03929 0.03014 -0.0026 0.4458 1.0000
8.000 0.7693 0.03844 0.02935 -0.0034 0.4417 1.0000
8.250 0.7319 0.04347 0.03446 -0.0021 0.4329 1.0000
8.500 0.8052 0.03920 0.03026 -0.0025 0.4247 1.0000
8.750 0.7690 0.04448 0.03564 -0.0015 0.4157 1.0000
9.000 0.8239 0.04139 0.03261 -0.0011 0.4059 1.0000
9.250 0.8093 0.04488 0.03623 -0.0005 0.3958 1.0000
9.500 0.8270 0.04522 0.03666 0.0001 0.3845 1.0000
9.750 0.8494 0.04483 0.03635 0.0010 0.3701 1.0000
10.000 0.8695 0.04454 0.03610 0.0020 0.3528 1.0000
10.250 0.9098 0.04218 0.03353 0.0036 0.3289 1.0000
10.500 0.9260 0.04254 0.03374 0.0048 0.3062 1.0000
10.750 0.9035 0.04681 0.03835 0.0049 0.2887 1.0000
11.000 0.8378 0.05752 0.04960 0.0021 0.2682 1.0000
11.250 0.8791 0.05352 0.04499 0.0046 0.2196 1.0000
11.500 0.8862 0.05452 0.04525 0.0061 0.2015 1.0000
11.750 0.8875 0.05696 0.04747 0.0067 0.1864 1.0000
12.000 0.8892 0.05964 0.05013 0.0069 0.1726 1.0000
12.500 0.8914 0.06549 0.05619 0.0062 0.1485 1.0000
12.750 0.8945 0.06828 0.05904 0.0058 0.1385 1.0000
13.000 0.8993 0.07084 0.06158 0.0055 0.1303 1.0000
13.250 0.9052 0.07332 0.06408 0.0052 0.1226 1.0000
13.500 0.9126 0.07570 0.06648 0.0049 0.1157 1.0000
13.750 0.9206 0.07800 0.06878 0.0047 0.1095 1.0000
14.000 0.9320 0.07995 0.07073 0.0047 0.1046 1.0000
14.250 0.9405 0.08248 0.07342 0.0044 0.0994 1.0000
14.500 0.9525 0.08426 0.07512 0.0043 0.0950 1.0000
14.750 0.9602 0.08709 0.07812 0.0039 0.0913 1.0000
15.000 0.9650 0.09041 0.08166 0.0032 0.0881 1.0000
15.250 0.9718 0.09325 0.08461 0.0025 0.0851 1.0000
15.500 0.9870 0.09479 0.08606 0.0026 0.0820 1.0000
15.750 0.9748 0.10082 0.09245 0.0000 0.0803 1.0000
16.000 0.9589 0.10769 0.09963 -0.0032 0.0788 1.0000
16.250 0.9364 0.11613 0.10835 -0.0076 0.0779 1.0000
16.500 0.8918 0.12986 0.12237 -0.0154 0.0776 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 63(3)-218 (naca633218-il)