HQ 3.5/13 AIRFOIL (hq3513-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/13 AIRFOIL (hq3513-il) Reynolds number: 100,000 Max Cl/Cd: 55.97 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3513-il-100000-n5.txt Download as CSV file: xf-hq3513-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/13 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3681 0.09327 0.08853 -0.0519 1.0000 0.0270
-9.750 -0.3816 0.08992 0.08527 -0.0512 1.0000 0.0270
-9.500 -0.3985 0.08666 0.08211 -0.0502 1.0000 0.0270
-9.250 -0.4049 0.08108 0.07659 -0.0538 0.9965 0.0269
-9.000 -0.4072 0.07177 0.06726 -0.0635 0.9882 0.0267
-8.750 -0.4176 0.06317 0.05855 -0.0741 0.9763 0.0263
-8.500 -0.4258 0.05565 0.05074 -0.0826 0.9632 0.0262
-8.250 -0.4256 0.04930 0.04396 -0.0878 0.9536 0.0262
-8.000 -0.4193 0.04364 0.03775 -0.0910 0.9450 0.0264
-7.750 -0.4090 0.03884 0.03229 -0.0924 0.9370 0.0268
-7.500 -0.3892 0.03500 0.02787 -0.0938 0.9312 0.0276
-7.250 -0.3600 0.03280 0.02544 -0.0958 0.9280 0.0286
-7.000 -0.3413 0.03120 0.02361 -0.0952 0.9201 0.0299
-6.750 -0.3128 0.02917 0.02120 -0.0962 0.9160 0.0322
-6.500 -0.2826 0.02733 0.01898 -0.0972 0.9125 0.0358
-6.250 -0.2610 0.02660 0.01821 -0.0967 0.9052 0.0392
-6.000 -0.2303 0.02528 0.01657 -0.0974 0.9013 0.0449
-5.750 -0.1987 0.02453 0.01580 -0.0988 0.8980 0.0520
-5.500 -0.1779 0.02379 0.01490 -0.0978 0.8905 0.0582
-5.000 -0.1172 0.02220 0.01317 -0.0992 0.8828 0.0724
-4.750 -0.0961 0.02165 0.01258 -0.0981 0.8755 0.0772
-4.500 -0.0664 0.02099 0.01180 -0.0984 0.8714 0.0836
-4.250 -0.0388 0.02038 0.01120 -0.0986 0.8669 0.0915
-4.000 -0.0161 0.01994 0.01072 -0.0978 0.8602 0.0990
-3.750 0.0136 0.01940 0.01012 -0.0983 0.8561 0.1115
-3.500 0.0395 0.01887 0.00969 -0.0982 0.8510 0.1333
-3.250 0.0629 0.01830 0.00935 -0.0978 0.8447 0.1821
-3.000 0.0892 0.01713 0.00896 -0.0983 0.8406 0.3495
-2.750 0.1097 0.01680 0.00918 -0.0969 0.8345 0.5046
-2.500 0.1342 0.01682 0.00929 -0.0958 0.8288 0.5722
-2.250 0.1639 0.01683 0.00926 -0.0956 0.8250 0.6154
-2.000 0.1853 0.01702 0.00944 -0.0941 0.8180 0.6472
-1.750 0.2100 0.01716 0.00957 -0.0927 0.8127 0.6838
-1.500 0.2376 0.01722 0.00961 -0.0918 0.8091 0.7156
-1.250 0.2562 0.01741 0.00978 -0.0897 0.8009 0.7352
-1.000 0.2851 0.01734 0.00962 -0.0896 0.7963 0.7492
-0.750 0.3101 0.01733 0.00956 -0.0888 0.7900 0.7579
-0.500 0.3368 0.01730 0.00945 -0.0886 0.7837 0.7669
-0.250 0.3685 0.01714 0.00920 -0.0890 0.7797 0.7754
0.000 0.3899 0.01722 0.00926 -0.0878 0.7714 0.7842
0.250 0.4205 0.01709 0.00906 -0.0881 0.7662 0.7935
0.500 0.4443 0.01707 0.00902 -0.0872 0.7579 0.8022
0.750 0.4750 0.01687 0.00875 -0.0874 0.7511 0.8116
1.000 0.4990 0.01681 0.00867 -0.0865 0.7411 0.8216
1.250 0.5291 0.01656 0.00838 -0.0864 0.7333 0.8312
1.500 0.5535 0.01648 0.00830 -0.0856 0.7230 0.8424
1.750 0.5788 0.01638 0.00820 -0.0849 0.7128 0.8543
2.000 0.6077 0.01616 0.00797 -0.0846 0.7040 0.8668
2.250 0.6317 0.01612 0.00797 -0.0838 0.6935 0.8821
2.500 0.6593 0.01606 0.00795 -0.0836 0.6840 0.9008
2.750 0.6951 0.01590 0.00783 -0.0849 0.6753 0.9246
3.000 0.7310 0.01590 0.00786 -0.0867 0.6632 1.0000
3.250 0.7576 0.01600 0.00794 -0.0867 0.6515 1.0000
3.500 0.7847 0.01609 0.00801 -0.0868 0.6396 1.0000
3.750 0.8115 0.01618 0.00807 -0.0867 0.6267 1.0000
4.000 0.8373 0.01630 0.00816 -0.0864 0.6122 1.0000
4.250 0.8623 0.01643 0.00829 -0.0859 0.5965 1.0000
4.500 0.8867 0.01658 0.00842 -0.0853 0.5794 1.0000
4.750 0.9109 0.01675 0.00854 -0.0846 0.5606 1.0000
5.000 0.9346 0.01693 0.00867 -0.0839 0.5399 1.0000
5.250 0.9570 0.01719 0.00887 -0.0829 0.5162 1.0000
5.500 0.9788 0.01749 0.00908 -0.0818 0.4913 1.0000
5.750 0.9996 0.01786 0.00932 -0.0806 0.4655 1.0000
6.000 1.0191 0.01832 0.00967 -0.0793 0.4395 1.0000
6.250 1.0378 0.01883 0.01007 -0.0778 0.4149 1.0000
6.500 1.0558 0.01940 0.01052 -0.0764 0.3930 1.0000
6.750 1.0738 0.01999 0.01103 -0.0749 0.3727 1.0000
7.000 1.0916 0.02059 0.01158 -0.0735 0.3550 1.0000
7.250 1.1093 0.02121 0.01215 -0.0721 0.3395 1.0000
7.500 1.1266 0.02182 0.01273 -0.0706 0.3260 1.0000
7.750 1.1434 0.02245 0.01333 -0.0691 0.3140 1.0000
8.250 1.1775 0.02378 0.01467 -0.0662 0.2931 1.0000
8.500 1.1946 0.02447 0.01537 -0.0649 0.2836 1.0000
8.750 1.2111 0.02522 0.01610 -0.0635 0.2746 1.0000
9.000 1.2274 0.02593 0.01690 -0.0621 0.2651 1.0000
9.250 1.2433 0.02672 0.01772 -0.0607 0.2565 1.0000
9.500 1.2581 0.02750 0.01858 -0.0592 0.2474 1.0000
9.750 1.2729 0.02831 0.01948 -0.0577 0.2389 1.0000
10.000 1.2861 0.02917 0.02039 -0.0562 0.2305 1.0000
10.250 1.2995 0.03003 0.02141 -0.0546 0.2219 1.0000
10.500 1.3111 0.03099 0.02239 -0.0530 0.2141 1.0000
10.750 1.3225 0.03195 0.02356 -0.0514 0.2051 1.0000
11.000 1.3326 0.03301 0.02471 -0.0498 0.1971 1.0000
11.250 1.3415 0.03414 0.02597 -0.0482 0.1883 1.0000
11.500 1.3500 0.03535 0.02732 -0.0466 0.1793 1.0000
11.750 1.3560 0.03671 0.02873 -0.0450 0.1712 1.0000
12.000 1.3627 0.03814 0.03032 -0.0435 0.1615 1.0000
12.250 1.3670 0.03975 0.03203 -0.0420 0.1518 1.0000
12.500 1.3693 0.04157 0.03390 -0.0407 0.1428 1.0000
12.750 1.3709 0.04356 0.03600 -0.0394 0.1329 1.0000
13.000 1.3725 0.04569 0.03822 -0.0384 0.1232 1.0000
13.250 1.3713 0.04813 0.04071 -0.0375 0.1135 1.0000
13.750 1.3665 0.05365 0.04637 -0.0362 0.0957 1.0000
14.000 1.3632 0.05672 0.04953 -0.0359 0.0881 1.0000
14.250 1.3577 0.06017 0.05306 -0.0359 0.0814 1.0000
14.500 1.3530 0.06374 0.05676 -0.0361 0.0742 1.0000
14.750 1.3432 0.06809 0.06117 -0.0367 0.0686 1.0000
15.000 1.3364 0.07230 0.06555 -0.0375 0.0624 1.0000
15.250 1.3233 0.07760 0.07092 -0.0389 0.0575 1.0000
15.500 1.3134 0.08269 0.07619 -0.0405 0.0526 1.0000
15.750 1.2994 0.08867 0.08229 -0.0426 0.0488 1.0000
16.000 1.2832 0.09526 0.08899 -0.0453 0.0465 1.0000
16.250 1.2705 0.10155 0.09548 -0.0480 0.0430 1.0000
16.500 1.2558 0.10834 0.10242 -0.0511 0.0405 1.0000
16.750 1.2397 0.11558 0.10976 -0.0546 0.0382 1.0000
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