NACA 64(4)-421 (naca644421-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64(4)-421 (naca644421-il) Reynolds number: 100,000 Max Cl/Cd: 26.11 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca644421-il-100000-n5.txt Download as CSV file: xf-naca644421-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(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
------ -------- --------- --------- -------- -------- --------
-17.250 -0.6929 0.09816 0.09162 -0.0713 1.0000 0.0504
-17.000 -0.7268 0.08941 0.08261 -0.0759 1.0000 0.0505
-16.750 -0.7468 0.08332 0.07630 -0.0788 1.0000 0.0509
-16.500 -0.7616 0.07826 0.07104 -0.0810 1.0000 0.0513
-16.250 -0.7719 0.07393 0.06652 -0.0825 1.0000 0.0518
-16.000 -0.7795 0.07010 0.06249 -0.0837 1.0000 0.0524
-15.750 -0.7855 0.06658 0.05877 -0.0846 1.0000 0.0531
-15.500 -0.7899 0.06336 0.05531 -0.0852 1.0000 0.0538
-15.250 -0.7816 0.06149 0.05343 -0.0853 1.0000 0.0546
-15.000 -0.7732 0.05981 0.05175 -0.0853 1.0000 0.0557
-14.750 -0.7660 0.05796 0.04985 -0.0853 1.0000 0.0566
-14.500 -0.7597 0.05610 0.04791 -0.0852 1.0000 0.0578
-14.250 -0.7527 0.05430 0.04599 -0.0849 1.0000 0.0591
-14.000 -0.7450 0.05260 0.04414 -0.0845 1.0000 0.0603
-13.750 -0.7323 0.05148 0.04308 -0.0839 1.0000 0.0616
-13.500 -0.7218 0.05032 0.04196 -0.0833 1.0000 0.0628
-13.250 -0.7133 0.04916 0.04079 -0.0824 1.0000 0.0644
-13.000 -0.7063 0.04808 0.03968 -0.0813 1.0000 0.0662
-12.750 -0.6986 0.04711 0.03866 -0.0801 0.9976 0.0680
-12.500 -0.6696 0.04569 0.03731 -0.0826 0.9795 0.0704
-12.250 -0.6417 0.04439 0.03596 -0.0850 0.9658 0.0735
-12.000 -0.6133 0.04311 0.03462 -0.0874 0.9536 0.0771
-11.750 -0.5865 0.04180 0.03330 -0.0898 0.9411 0.0810
-11.500 -0.5597 0.04064 0.03208 -0.0917 0.9288 0.0857
-11.250 -0.5366 0.03938 0.03080 -0.0935 0.9165 0.0906
-11.000 -0.5162 0.03826 0.02964 -0.0944 0.9034 0.0965
-10.750 -0.5007 0.03717 0.02853 -0.0945 0.8901 0.1028
-10.500 -0.4871 0.03607 0.02741 -0.0944 0.8783 0.1099
-10.250 -0.4750 0.03504 0.02634 -0.0938 0.8665 0.1187
-10.000 -0.4662 0.03391 0.02524 -0.0929 0.8553 0.1282
-9.750 -0.4586 0.03272 0.02407 -0.0919 0.8450 0.1398
-9.500 -0.4534 0.03150 0.02289 -0.0907 0.8346 0.1533
-9.250 -0.4496 0.03019 0.02162 -0.0893 0.8253 0.1699
-9.000 -0.4487 0.02882 0.02034 -0.0877 0.8156 0.1897
-8.750 -0.4498 0.02735 0.01896 -0.0859 0.8065 0.2130
-8.500 -0.4542 0.02585 0.01759 -0.0836 0.7979 0.2409
-8.250 -0.4623 0.02443 0.01635 -0.0806 0.7885 0.2726
-8.000 -0.4723 0.02335 0.01544 -0.0766 0.7813 0.3084
-7.750 -0.4725 0.02287 0.01527 -0.0732 0.7722 0.3543
-7.500 -0.4548 0.02313 0.01576 -0.0711 0.7657 0.4029
-7.250 -0.4458 0.02278 0.01530 -0.0691 0.7595 0.4338
-7.000 -0.4336 0.02260 0.01501 -0.0673 0.7521 0.4556
-6.750 -0.4157 0.02253 0.01480 -0.0661 0.7462 0.4735
-6.500 -0.3931 0.02263 0.01474 -0.0652 0.7417 0.4885
-6.250 -0.3683 0.02308 0.01518 -0.0642 0.7346 0.4993
-6.000 -0.3486 0.02302 0.01496 -0.0633 0.7284 0.5115
-5.750 -0.3188 0.02353 0.01541 -0.0627 0.7238 0.5211
-5.500 -0.2961 0.02369 0.01545 -0.0618 0.7184 0.5318
-5.250 -0.2682 0.02433 0.01609 -0.0610 0.7122 0.5409
-5.000 -0.2452 0.02441 0.01605 -0.0603 0.7073 0.5507
-4.750 -0.2136 0.02495 0.01653 -0.0598 0.7034 0.5564
-4.500 -0.1943 0.02466 0.01611 -0.0592 0.6985 0.5649
-4.250 -0.1713 0.02460 0.01599 -0.0587 0.6930 0.5698
-4.000 -0.1440 0.02471 0.01603 -0.0583 0.6885 0.5728
-3.750 -0.1173 0.02463 0.01586 -0.0582 0.6848 0.5764
-3.500 -0.0925 0.02435 0.01544 -0.0582 0.6813 0.5811
-3.250 -0.0747 0.02380 0.01477 -0.0580 0.6756 0.5874
-3.000 -0.0488 0.02384 0.01478 -0.0577 0.6709 0.5896
-2.750 -0.0218 0.02380 0.01468 -0.0575 0.6670 0.5920
-2.500 0.0059 0.02370 0.01449 -0.0575 0.6639 0.5949
-2.250 0.0304 0.02363 0.01437 -0.0574 0.6600 0.5984
-2.000 0.0526 0.02350 0.01420 -0.0572 0.6554 0.6027
-1.750 0.0768 0.02320 0.01378 -0.0577 0.6515 0.6076
-1.500 0.1036 0.02320 0.01376 -0.0575 0.6483 0.6096
-1.250 0.1314 0.02317 0.01368 -0.0576 0.6456 0.6118
-1.000 0.1600 0.02312 0.01357 -0.0579 0.6434 0.6145
-0.750 0.1811 0.02327 0.01376 -0.0573 0.6391 0.6176
-0.500 0.2044 0.02330 0.01378 -0.0572 0.6350 0.6209
-0.250 0.2301 0.02322 0.01364 -0.0575 0.6315 0.6244
0.000 0.2579 0.02309 0.01344 -0.0581 0.6286 0.6281
0.250 0.2859 0.02312 0.01345 -0.0581 0.6262 0.6304
0.500 0.3148 0.02315 0.01346 -0.0584 0.6243 0.6330
0.750 0.3338 0.02349 0.01388 -0.0575 0.6203 0.6359
1.000 0.3549 0.02375 0.01419 -0.0571 0.6167 0.6391
1.250 0.3790 0.02391 0.01436 -0.0570 0.6136 0.6427
1.500 0.4058 0.02397 0.01439 -0.0575 0.6109 0.6468
1.750 0.4334 0.02402 0.01444 -0.0577 0.6085 0.6497
2.000 0.4620 0.02408 0.01451 -0.0579 0.6065 0.6524
2.250 0.4892 0.02423 0.01470 -0.0581 0.6045 0.6557
2.500 0.4997 0.02498 0.01558 -0.0562 0.5999 0.6598
2.750 0.5182 0.02543 0.01609 -0.0555 0.5960 0.6645
3.000 0.5425 0.02567 0.01635 -0.0555 0.5929 0.6691
3.250 0.5679 0.02585 0.01659 -0.0553 0.5905 0.6722
3.500 0.5963 0.02594 0.01672 -0.0555 0.5884 0.6758
3.750 0.6278 0.02595 0.01675 -0.0562 0.5866 0.6800
4.000 0.6248 0.02722 0.01818 -0.0528 0.5802 0.6850
4.250 0.6380 0.02792 0.01894 -0.0514 0.5757 0.6900
4.500 0.6601 0.02821 0.01933 -0.0508 0.5728 0.6937
4.750 0.6885 0.02830 0.01949 -0.0509 0.5706 0.6983
5.000 0.7209 0.02828 0.01951 -0.0517 0.5688 0.7039
6.000 0.7615 0.03128 0.02289 -0.0440 0.5510 0.7272
6.250 0.8026 0.03092 0.02260 -0.0457 0.5495 0.7330
6.750 0.7704 0.03484 0.02675 -0.0368 0.5330 0.7458
7.000 0.7828 0.03572 0.02771 -0.0356 0.5277 0.7526
7.250 0.8588 0.03289 0.02497 -0.0394 0.5302 0.7585
7.750 0.8490 0.03598 0.02826 -0.0336 0.5133 0.7743
8.250 0.8500 0.03898 0.03146 -0.0296 0.4961 0.7914
8.500 0.8968 0.03704 0.02963 -0.0300 0.4948 0.7997
9.000 0.8420 0.04461 0.03742 -0.0240 0.4646 0.8182
9.250 0.8822 0.04270 0.03561 -0.0237 0.4616 0.8295
9.500 0.9301 0.03998 0.03299 -0.0234 0.4591 0.8409
10.000 0.8914 0.04663 0.03989 -0.0189 0.4285 0.8666
10.500 0.9152 0.04740 0.04091 -0.0161 0.4086 0.9058
10.750 0.9155 0.04936 0.04302 -0.0154 0.3936 0.9421
11.000 0.9252 0.05048 0.04420 -0.0154 0.3791 1.0000
11.250 0.9463 0.05086 0.04461 -0.0156 0.3648 1.0000
11.500 0.9722 0.05063 0.04433 -0.0157 0.3488 1.0000
11.750 0.9990 0.05019 0.04378 -0.0156 0.3285 1.0000
12.000 1.0163 0.05074 0.04419 -0.0153 0.3040 1.0000
12.250 1.0274 0.05196 0.04521 -0.0149 0.2775 1.0000
12.500 1.0325 0.05392 0.04700 -0.0146 0.2527 1.0000
12.750 1.0348 0.05626 0.04918 -0.0144 0.2299 1.0000
13.000 1.0357 0.05884 0.05160 -0.0143 0.2096 1.0000
13.250 1.0371 0.06150 0.05417 -0.0143 0.1914 1.0000
13.500 1.0386 0.06424 0.05682 -0.0145 0.1747 1.0000
13.750 1.0407 0.06696 0.05947 -0.0147 0.1599 1.0000
14.000 1.0429 0.06974 0.06218 -0.0150 0.1469 1.0000
14.500 1.0490 0.07529 0.06766 -0.0158 0.1242 1.0000
14.750 1.0531 0.07799 0.07036 -0.0163 0.1148 1.0000
15.000 1.0566 0.08080 0.07313 -0.0168 0.1066 1.0000
15.250 1.0597 0.08370 0.07601 -0.0174 0.0994 1.0000
15.500 1.0650 0.08637 0.07871 -0.0180 0.0926 1.0000
15.750 1.0681 0.08931 0.08162 -0.0187 0.0871 1.0000
16.000 1.0733 0.09206 0.08443 -0.0194 0.0816 1.0000
16.250 1.0777 0.09488 0.08724 -0.0201 0.0771 1.0000
16.500 1.0828 0.09767 0.09008 -0.0209 0.0728 1.0000
16.750 1.0874 0.10051 0.09291 -0.0218 0.0693 1.0000
17.000 1.0932 0.10324 0.09572 -0.0226 0.0657 1.0000
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Polar data table (+)
Polar graphs
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