NACA 65(4)-421 (naca654421-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(4)-421 (naca654421-il) Reynolds number: 100,000 Max Cl/Cd: 19.74 at α=11.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca654421-il-100000-n5.txt Download as CSV file: xf-naca654421-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(4)-421
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
------ -------- --------- --------- -------- -------- --------
-16.500 -0.5309 0.10864 0.10283 -0.0789 1.0000 0.0447
-16.250 -0.6202 0.08996 0.08374 -0.0894 1.0000 0.0437
-16.000 -0.6580 0.08206 0.07558 -0.0929 1.0000 0.0436
-15.750 -0.6847 0.07639 0.06968 -0.0947 1.0000 0.0435
-15.500 -0.7049 0.07189 0.06499 -0.0955 1.0000 0.0435
-15.250 -0.7206 0.06827 0.06121 -0.0956 1.0000 0.0436
-15.000 -0.7338 0.06528 0.05807 -0.0951 1.0000 0.0437
-14.750 -0.7471 0.06284 0.05552 -0.0938 1.0000 0.0440
-14.500 -0.7486 0.05999 0.05250 -0.0944 0.9893 0.0444
-14.250 -0.7405 0.05690 0.04916 -0.0969 0.9790 0.0452
-13.750 -0.7137 0.05141 0.04309 -0.1014 0.9612 0.0466
-13.500 -0.6934 0.04912 0.04051 -0.1034 0.9533 0.0471
-13.250 -0.6650 0.04734 0.03860 -0.1053 0.9458 0.0478
-13.000 -0.6342 0.04594 0.03715 -0.1070 0.9388 0.0486
-12.750 -0.6063 0.04466 0.03578 -0.1084 0.9306 0.0494
-12.500 -0.5782 0.04347 0.03449 -0.1098 0.9232 0.0504
-12.250 -0.5536 0.04242 0.03334 -0.1104 0.9140 0.0516
-12.000 -0.5291 0.04142 0.03218 -0.1110 0.9060 0.0532
-11.750 -0.5069 0.04060 0.03128 -0.1110 0.8967 0.0544
-11.500 -0.4848 0.03978 0.03046 -0.1111 0.8893 0.0558
-11.250 -0.4672 0.03902 0.02969 -0.1105 0.8804 0.0574
-11.000 -0.4479 0.03826 0.02885 -0.1102 0.8735 0.0589
-10.750 -0.4317 0.03755 0.02807 -0.1094 0.8653 0.0605
-10.500 -0.4167 0.03676 0.02722 -0.1086 0.8578 0.0623
-10.250 -0.4034 0.03589 0.02633 -0.1078 0.8511 0.0642
-10.000 -0.3916 0.03506 0.02547 -0.1067 0.8433 0.0670
-9.750 -0.3782 0.03422 0.02456 -0.1058 0.8371 0.0708
-9.500 -0.3671 0.03332 0.02367 -0.1048 0.8309 0.0751
-9.250 -0.3562 0.03248 0.02282 -0.1037 0.8242 0.0810
-9.000 -0.3457 0.03156 0.02190 -0.1025 0.8185 0.0895
-8.750 -0.3372 0.03060 0.02102 -0.1010 0.8130 0.1034
-8.500 -0.3327 0.02957 0.02017 -0.0992 0.8062 0.1268
-8.250 -0.3314 0.02834 0.01914 -0.0971 0.8004 0.1632
-8.000 -0.3340 0.02695 0.01797 -0.0945 0.7956 0.2071
-7.750 -0.3410 0.02572 0.01700 -0.0913 0.7887 0.2502
-7.500 -0.3502 0.02443 0.01599 -0.0875 0.7830 0.2998
-7.250 -0.3580 0.02344 0.01537 -0.0831 0.7785 0.3622
-7.000 -0.3288 0.02455 0.01702 -0.0814 0.7743 0.4491
-6.750 -0.3247 0.02456 0.01704 -0.0780 0.7683 0.4805
-6.500 -0.3337 0.02392 0.01630 -0.0735 0.7631 0.5034
-6.250 -0.3186 0.02424 0.01655 -0.0712 0.7598 0.5306
-6.000 -0.3173 0.02439 0.01663 -0.0675 0.7548 0.5538
-5.750 -0.3001 0.02533 0.01753 -0.0651 0.7502 0.5745
-5.500 -0.2583 0.02694 0.01909 -0.0652 0.7471 0.5860
-5.250 -0.2356 0.02723 0.01926 -0.0641 0.7439 0.5953
-5.000 -0.1980 0.02805 0.01996 -0.0644 0.7416 0.6014
-4.750 -0.1916 0.02774 0.01955 -0.0618 0.7374 0.6120
-4.500 -0.1637 0.02838 0.02014 -0.0612 0.7331 0.6153
-4.250 -0.1411 0.02857 0.02026 -0.0603 0.7296 0.6203
-4.000 -0.1363 0.02778 0.01934 -0.0581 0.7261 0.6298
-3.750 -0.1061 0.02792 0.01938 -0.0582 0.7239 0.6321
-3.500 -0.0767 0.02792 0.01928 -0.0584 0.7219 0.6349
-3.250 -0.0663 0.02802 0.01937 -0.0562 0.7169 0.6395
-3.000 -0.0647 0.02734 0.01859 -0.0537 0.7120 0.6480
-2.750 -0.0392 0.02742 0.01862 -0.0533 0.7091 0.6499
-2.500 -0.0131 0.02741 0.01854 -0.0531 0.7068 0.6522
-2.250 0.0132 0.02730 0.01835 -0.0532 0.7049 0.6551
-2.000 0.0390 0.02707 0.01802 -0.0533 0.7032 0.6589
-1.750 0.0323 0.02702 0.01797 -0.0496 0.6964 0.6657
-1.500 0.0512 0.02711 0.01803 -0.0485 0.6927 0.6681
-1.250 0.0758 0.02715 0.01805 -0.0481 0.6900 0.6702
-1.000 0.1023 0.02711 0.01796 -0.0481 0.6880 0.6727
-0.750 0.1298 0.02699 0.01777 -0.0485 0.6864 0.6754
-0.500 0.1583 0.02679 0.01751 -0.0492 0.6850 0.6787
-0.250 0.1417 0.02756 0.01831 -0.0439 0.6764 0.6847
0.000 0.1622 0.02767 0.01842 -0.0431 0.6731 0.6872
0.250 0.1881 0.02770 0.01844 -0.0430 0.6709 0.6892
0.500 0.2159 0.02768 0.01840 -0.0433 0.6692 0.6914
0.750 0.2453 0.02763 0.01833 -0.0439 0.6679 0.6940
1.250 0.2385 0.02929 0.02003 -0.0366 0.6548 0.7027
1.500 0.2657 0.02928 0.02001 -0.0372 0.6528 0.7058
1.750 0.2935 0.02934 0.02008 -0.0374 0.6512 0.7078
2.000 0.3239 0.02935 0.02010 -0.0380 0.6500 0.7101
3.000 0.3674 0.03192 0.02275 -0.0316 0.6323 0.7249
3.250 0.3993 0.03177 0.02264 -0.0321 0.6313 0.7272
4.000 0.4081 0.03582 0.02686 -0.0257 0.6117 0.7375
4.500 0.4276 0.03799 0.02911 -0.0235 0.5993 0.7455
4.750 0.4560 0.03794 0.02913 -0.0235 0.5976 0.7486
5.000 0.4874 0.03773 0.02899 -0.0239 0.5964 0.7521
5.500 0.4977 0.04048 0.03185 -0.0210 0.5813 0.7609
5.750 0.5289 0.04030 0.03174 -0.0216 0.5797 0.7645
6.250 0.5420 0.04268 0.03429 -0.0183 0.5649 0.7725
6.500 0.5738 0.04239 0.03408 -0.0188 0.5631 0.7774
6.750 0.6089 0.04194 0.03370 -0.0197 0.5617 0.7826
7.250 0.6260 0.04391 0.03588 -0.0167 0.5462 0.7912
7.500 0.6613 0.04323 0.03529 -0.0173 0.5447 0.7963
8.000 0.6862 0.04470 0.03696 -0.0151 0.5291 0.8066
8.500 0.7165 0.04578 0.03824 -0.0135 0.5134 0.8194
8.750 0.7514 0.04452 0.03711 -0.0133 0.5114 0.8249
9.000 0.7470 0.04650 0.03921 -0.0114 0.4975 0.8316
9.250 0.7833 0.04521 0.03803 -0.0115 0.4952 0.8386
10.250 0.8219 0.04812 0.04145 -0.0062 0.4500 0.8715
10.500 0.8333 0.04839 0.04184 -0.0046 0.4348 0.8815
10.750 0.8530 0.04788 0.04140 -0.0033 0.4161 0.8934
11.000 0.8704 0.04762 0.04114 -0.0021 0.3895 0.9073
11.250 0.9010 0.04599 0.03932 -0.0010 0.3524 0.9249
11.750 0.9287 0.04704 0.03995 -0.0001 0.2783 1.0000
12.000 0.9333 0.04912 0.04180 0.0002 0.2451 1.0000
12.250 0.9351 0.05153 0.04401 0.0004 0.2142 1.0000
12.500 0.9362 0.05412 0.04642 0.0005 0.1842 1.0000
12.750 0.9372 0.05680 0.04891 0.0005 0.1558 1.0000
13.000 0.9379 0.05956 0.05150 0.0005 0.1281 1.0000
13.250 0.9390 0.06234 0.05411 0.0005 0.1037 1.0000
13.500 0.9407 0.06511 0.05673 0.0004 0.0857 1.0000
13.750 0.9443 0.06775 0.05928 0.0002 0.0738 1.0000
14.000 0.9480 0.07042 0.06190 0.0000 0.0657 1.0000
14.250 0.9521 0.07308 0.06457 -0.0003 0.0603 1.0000
14.500 0.9576 0.07563 0.06714 -0.0007 0.0560 1.0000
14.750 0.9621 0.07834 0.06986 -0.0011 0.0531 1.0000
15.000 0.9680 0.08087 0.07244 -0.0015 0.0506 1.0000
15.250 0.9741 0.08341 0.07503 -0.0020 0.0481 1.0000
15.500 0.9792 0.08606 0.07770 -0.0026 0.0464 1.0000
15.750 0.9868 0.08839 0.08010 -0.0030 0.0448 1.0000
16.000 0.9955 0.09058 0.08237 -0.0034 0.0434 1.0000
16.250 1.0041 0.09279 0.08462 -0.0039 0.0421 1.0000
16.500 1.0130 0.09492 0.08676 -0.0044 0.0410 1.0000
16.750 1.0230 0.09684 0.08865 -0.0048 0.0400 1.0000
17.000 1.0338 0.09878 0.09073 -0.0052 0.0389 1.0000
17.250 1.0436 0.10088 0.09293 -0.0058 0.0377 1.0000
17.500 1.0532 0.10298 0.09509 -0.0064 0.0368 1.0000
17.750 1.0626 0.10507 0.09722 -0.0070 0.0359 1.0000
18.000 1.0749 0.10669 0.09883 -0.0075 0.0352 1.0000
18.250 1.0862 0.10857 0.10078 -0.0079 0.0346 1.0000
18.500 1.0934 0.11113 0.10353 -0.0087 0.0341 1.0000
18.750 1.0998 0.11384 0.10640 -0.0097 0.0336 1.0000
19.000 1.1040 0.11689 0.10962 -0.0108 0.0332 1.0000
19.250 1.1062 0.12029 0.11318 -0.0123 0.0327 1.0000
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Polar data table (+)
Polar graphs
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