NACA 63(4)-421 (naca634421-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63(4)-421 (naca634421-il) Reynolds number: 100,000 Max Cl/Cd: 24.41 at α=13.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca634421-il-100000.txt Download as CSV file: xf-naca634421-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.7934 0.07968 0.07341 -0.0791 1.0000 0.0937
-15.750 -0.8290 0.07326 0.06676 -0.0815 1.0000 0.0935
-15.500 -0.8633 0.06782 0.06107 -0.0831 1.0000 0.0936
-15.250 -0.8252 0.06727 0.06075 -0.0824 1.0000 0.0970
-15.000 -0.8349 0.06385 0.05721 -0.0830 1.0000 0.0985
-14.750 -0.8515 0.06014 0.05333 -0.0835 1.0000 0.0996
-14.500 -0.8683 0.05674 0.04974 -0.0835 1.0000 0.1009
-14.250 -0.8845 0.05367 0.04645 -0.0831 1.0000 0.1021
-14.000 -0.9004 0.05097 0.04353 -0.0820 1.0000 0.1032
-13.750 -0.9167 0.04874 0.04107 -0.0803 1.0000 0.1042
-13.500 -0.8859 0.04724 0.03975 -0.0804 1.0000 0.1079
-13.250 -0.8845 0.04587 0.03837 -0.0787 1.0000 0.1102
-13.000 -0.8952 0.04487 0.03734 -0.0753 1.0000 0.1118
-12.750 -0.9267 0.04487 0.03734 -0.0686 1.0000 0.1119
-12.500 -0.9558 0.04473 0.03716 -0.0624 1.0000 0.1124
-12.250 -0.9599 0.04361 0.03587 -0.0605 0.9969 0.1142
-12.000 -0.9129 0.04176 0.03406 -0.0642 0.9925 0.1197
-11.750 -0.8787 0.04018 0.03237 -0.0672 0.9853 0.1255
-11.500 -0.8327 0.03863 0.03087 -0.0706 0.9810 0.1326
-11.250 -0.8009 0.03720 0.02933 -0.0733 0.9732 0.1407
-11.000 -0.7570 0.03590 0.02820 -0.0764 0.9684 0.1520
-10.750 -0.7203 0.03452 0.02695 -0.0792 0.9626 0.1659
-10.500 -0.6910 0.03308 0.02564 -0.0815 0.9550 0.1832
-10.250 -0.6573 0.03132 0.02413 -0.0852 0.9503 0.2085
-10.000 -0.6466 0.02993 0.02292 -0.0855 0.9388 0.2320
-9.750 -0.6357 0.02849 0.02172 -0.0860 0.9290 0.2616
-9.500 -0.6315 0.02735 0.02076 -0.0850 0.9181 0.2922
-9.250 -0.6348 0.02694 0.02054 -0.0817 0.9059 0.3190
-9.000 -0.6169 0.02662 0.02036 -0.0813 0.8987 0.3560
-8.750 -0.6159 0.02687 0.02065 -0.0776 0.8871 0.3796
-8.500 -0.5858 0.02739 0.02117 -0.0777 0.8810 0.4073
-8.250 -0.5724 0.02818 0.02194 -0.0752 0.8715 0.4254
-8.000 -0.5400 0.02924 0.02298 -0.0748 0.8652 0.4436
-7.750 -0.4906 0.03088 0.02460 -0.0758 0.8614 0.4590
-7.500 -0.4837 0.03153 0.02519 -0.0726 0.8515 0.4716
-7.250 -0.4213 0.03416 0.02781 -0.0737 0.8472 0.4806
-7.000 -0.3791 0.03546 0.02902 -0.0738 0.8427 0.4910
-6.750 -0.2902 0.03924 0.03271 -0.0759 0.8408 0.4928
-6.500 -0.2707 0.04042 0.03386 -0.0735 0.8317 0.5006
-6.000 -0.2484 0.03989 0.03315 -0.0699 0.8184 0.5231
-5.750 -0.2216 0.04102 0.03425 -0.0681 0.8102 0.5282
-5.500 -0.2395 0.03908 0.03219 -0.0653 0.8030 0.5449
-5.250 -0.1731 0.04103 0.03405 -0.0662 0.8003 0.5465
-5.000 -0.1330 0.04295 0.03598 -0.0650 0.7921 0.5492
-4.750 -0.1394 0.04206 0.03503 -0.0622 0.7850 0.5623
-4.500 -0.0927 0.04268 0.03555 -0.0626 0.7816 0.5676
-4.250 -0.0593 0.04367 0.03653 -0.0618 0.7753 0.5719
-4.000 -0.1025 0.04207 0.03491 -0.0564 0.7658 0.5860
-3.750 -0.0491 0.04264 0.03540 -0.0575 0.7627 0.5891
-3.500 -0.1055 0.04128 0.03403 -0.0512 0.7516 0.6037
-3.250 -0.0727 0.04180 0.03453 -0.0503 0.7464 0.6067
-3.000 -0.0291 0.04211 0.03478 -0.0508 0.7433 0.6102
-2.750 0.0012 0.04172 0.03431 -0.0510 0.7405 0.6166
-2.500 -0.0614 0.04161 0.03425 -0.0431 0.7272 0.6269
-2.250 -0.0254 0.04178 0.03438 -0.0430 0.7237 0.6305
-2.000 0.0108 0.04135 0.03388 -0.0437 0.7212 0.6363
-1.750 -0.0465 0.04145 0.03399 -0.0370 0.7076 0.6463
-1.500 -0.0165 0.04165 0.03417 -0.0362 0.7040 0.6496
-1.250 0.0197 0.04143 0.03390 -0.0368 0.7017 0.6544
-1.000 -0.0476 0.04263 0.03511 -0.0291 0.6881 0.6633
-0.750 -0.0177 0.04245 0.03490 -0.0294 0.6845 0.6679
-0.500 0.0236 0.04231 0.03474 -0.0302 0.6822 0.6719
-0.250 -0.0255 0.04414 0.03661 -0.0230 0.6711 0.6774
0.000 -0.0033 0.04400 0.03635 -0.0255 0.6665 0.6858
0.250 0.0244 0.04407 0.03644 -0.0246 0.6635 0.6892
0.500 0.0647 0.04384 0.03619 -0.0254 0.6615 0.6935
0.750 0.0236 0.04635 0.03873 -0.0207 0.6515 0.6988
1.000 0.0503 0.04654 0.03883 -0.0231 0.6471 0.7064
1.250 0.0789 0.04655 0.03886 -0.0224 0.6439 0.7102
1.500 0.1187 0.04626 0.03856 -0.0231 0.6417 0.7147
1.750 0.0849 0.04903 0.04137 -0.0199 0.6330 0.7200
2.000 0.1105 0.04947 0.04174 -0.0219 0.6279 0.7269
2.250 0.1371 0.04963 0.04194 -0.0211 0.6247 0.7312
2.500 0.1772 0.04941 0.04172 -0.0218 0.6224 0.7365
2.750 0.1491 0.05219 0.04452 -0.0196 0.6136 0.7423
3.000 0.1689 0.05298 0.04530 -0.0205 0.6090 0.7481
3.250 0.1988 0.05309 0.04544 -0.0202 0.6054 0.7529
3.500 0.2456 0.05264 0.04499 -0.0215 0.6029 0.7594
3.750 0.2150 0.05589 0.04826 -0.0201 0.5931 0.7661
4.000 0.2329 0.05647 0.04889 -0.0190 0.5886 0.7711
4.250 0.2756 0.05608 0.04853 -0.0197 0.5851 0.7776
4.500 0.2644 0.05854 0.05101 -0.0191 0.5763 0.7840
4.750 0.2783 0.05949 0.05201 -0.0185 0.5709 0.7896
5.000 0.3157 0.05928 0.05182 -0.0186 0.5670 0.7969
5.250 0.3144 0.06139 0.05396 -0.0185 0.5582 0.8044
5.500 0.3252 0.06234 0.05498 -0.0172 0.5521 0.8105
5.750 0.3652 0.06204 0.05471 -0.0178 0.5482 0.8189
6.000 0.3570 0.06440 0.05712 -0.0169 0.5384 0.8256
6.250 0.3753 0.06498 0.05777 -0.0160 0.5325 0.8333
6.500 0.4197 0.06438 0.05719 -0.0167 0.5290 0.8430
6.750 0.3974 0.06732 0.06021 -0.0146 0.5177 0.8503
7.000 0.4310 0.06720 0.06014 -0.0149 0.5126 0.8605
7.250 0.4748 0.06599 0.05898 -0.0142 0.5098 0.8710
7.500 0.4494 0.06955 0.06260 -0.0131 0.4964 0.8798
7.750 0.4890 0.06854 0.06165 -0.0125 0.4927 0.8929
8.000 0.4726 0.07135 0.06455 -0.0110 0.4806 0.9040
8.250 0.5063 0.07047 0.06374 -0.0102 0.4759 0.9199
8.500 0.5540 0.06864 0.06200 -0.0098 0.4734 0.9401
8.750 0.5437 0.07206 0.06554 -0.0108 0.4588 0.9602
9.000 0.6065 0.07015 0.06371 -0.0136 0.4559 1.0000
9.250 0.5995 0.07400 0.06760 -0.0155 0.4414 1.0000
9.500 0.6599 0.07205 0.06570 -0.0177 0.4386 1.0000
9.750 0.6541 0.07587 0.06957 -0.0194 0.4241 1.0000
10.000 0.7119 0.07368 0.06743 -0.0209 0.4213 1.0000
10.250 0.7074 0.07737 0.07116 -0.0223 0.4067 1.0000
10.500 0.7640 0.07470 0.06855 -0.0232 0.4040 1.0000
10.750 0.7597 0.07831 0.07220 -0.0242 0.3895 1.0000
11.000 0.8154 0.07512 0.06907 -0.0245 0.3869 1.0000
11.250 0.8773 0.07077 0.06478 -0.0244 0.3856 1.0000
11.500 0.9419 0.06552 0.05962 -0.0239 0.3851 1.0000
11.750 1.0191 0.05872 0.05289 -0.0235 0.3852 1.0000
12.000 1.1469 0.04720 0.04142 -0.0240 0.3852 1.0000
12.250 1.1250 0.05112 0.04539 -0.0229 0.3696 1.0000
12.500 1.1309 0.05235 0.04665 -0.0223 0.3552 1.0000
12.750 1.1680 0.05031 0.04459 -0.0219 0.3414 1.0000
13.000 1.1959 0.04934 0.04356 -0.0214 0.3252 1.0000
13.250 1.2123 0.04966 0.04379 -0.0208 0.3078 1.0000
13.500 1.2223 0.05073 0.04475 -0.0202 0.2897 1.0000
13.750 1.2274 0.05241 0.04632 -0.0196 0.2719 1.0000
14.000 1.2303 0.05442 0.04821 -0.0191 0.2545 1.0000
14.250 1.2312 0.05675 0.05042 -0.0188 0.2379 1.0000
14.500 1.2312 0.05928 0.05285 -0.0185 0.2219 1.0000
14.750 1.2309 0.06196 0.05543 -0.0183 0.2068 1.0000
15.000 1.2312 0.06466 0.05803 -0.0183 0.1925 1.0000
15.250 1.2322 0.06737 0.06065 -0.0182 0.1791 1.0000
15.500 1.2354 0.06991 0.06307 -0.0182 0.1666 1.0000
15.750 1.2417 0.07212 0.06513 -0.0182 0.1550 1.0000
16.000 1.2455 0.07470 0.06765 -0.0183 0.1449 1.0000
16.250 1.2466 0.07779 0.07081 -0.0187 0.1363 1.0000
16.500 1.2592 0.07946 0.07234 -0.0186 0.1281 1.0000
16.750 1.2610 0.08252 0.07548 -0.0191 0.1216 1.0000
17.000 1.2743 0.08423 0.07712 -0.0190 0.1155 1.0000
17.250 1.2749 0.08754 0.08057 -0.0197 0.1107 1.0000
17.500 1.2996 0.08795 0.08078 -0.0193 0.1052 1.0000
17.750 1.2913 0.09245 0.08556 -0.0205 0.1022 1.0000
18.000 1.2959 0.09530 0.08849 -0.0211 0.0986 1.0000
18.250 1.3189 0.09600 0.08906 -0.0209 0.0945 1.0000
18.500 1.3048 0.10132 0.09468 -0.0226 0.0926 1.0000
18.750 1.2951 0.10617 0.09976 -0.0244 0.0903 1.0000
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