HQ 3.5/13 AIRFOIL (hq3513-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/13 AIRFOIL (hq3513-il) Reynolds number: 50,000 Max Cl/Cd: 35.32 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3513-il-50000-n5.txt Download as CSV file: xf-hq3513-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3379 0.10571 0.09884 -0.0490 1.0000 0.0521
-9.750 -0.3448 0.10252 0.09575 -0.0490 1.0000 0.0522
-9.500 -0.3529 0.09945 0.09279 -0.0487 1.0000 0.0518
-9.250 -0.3638 0.09644 0.08990 -0.0481 1.0000 0.0517
-9.000 -0.3772 0.09355 0.08716 -0.0473 1.0000 0.0516
-8.750 -0.3932 0.09067 0.08440 -0.0463 1.0000 0.0514
-8.500 -0.4116 0.08781 0.08166 -0.0452 1.0000 0.0509
-8.250 -0.4334 0.08486 0.07882 -0.0441 1.0000 0.0500
-8.000 -0.4611 0.08163 0.07570 -0.0432 1.0000 0.0490
-7.750 -0.4875 0.07747 0.07159 -0.0439 1.0000 0.0481
-7.500 -0.4871 0.07069 0.06462 -0.0511 0.9915 0.0481
-7.250 -0.4800 0.06454 0.05819 -0.0572 0.9832 0.0485
-7.000 -0.4709 0.05942 0.05273 -0.0612 0.9751 0.0495
-6.750 -0.4564 0.05442 0.04727 -0.0648 0.9682 0.0505
-6.500 -0.4391 0.04984 0.04215 -0.0673 0.9614 0.0516
-6.250 -0.4149 0.04554 0.03707 -0.0701 0.9562 0.0543
-6.000 -0.3943 0.04265 0.03376 -0.0710 0.9496 0.0577
-5.750 -0.3660 0.04060 0.03147 -0.0726 0.9447 0.0626
-5.500 -0.3383 0.03822 0.02833 -0.0735 0.9395 0.0688
-5.250 -0.3132 0.03654 0.02663 -0.0740 0.9339 0.0747
-5.000 -0.2807 0.03487 0.02448 -0.0752 0.9296 0.0834
-4.750 -0.2551 0.03374 0.02329 -0.0754 0.9242 0.0915
-4.500 -0.2273 0.03256 0.02184 -0.0752 0.9188 0.0982
-4.250 -0.1953 0.03164 0.02085 -0.0762 0.9146 0.1088
-4.000 -0.1717 0.03085 0.02001 -0.0755 0.9087 0.1164
-3.750 -0.1445 0.03019 0.01917 -0.0754 0.9032 0.1268
-3.500 -0.1114 0.02941 0.01844 -0.0769 0.8991 0.1448
-3.250 -0.0905 0.02881 0.01790 -0.0763 0.8922 0.1644
-3.000 -0.0607 0.02787 0.01724 -0.0776 0.8871 0.2159
-2.750 -0.0332 0.02642 0.01716 -0.0783 0.8831 0.4434
-2.500 -0.0203 0.02664 0.01769 -0.0748 0.8752 0.5756
-2.250 0.0057 0.02697 0.01797 -0.0734 0.8701 0.6501
-2.000 0.0199 0.02734 0.01829 -0.0702 0.8624 0.6955
-1.750 0.0376 0.02763 0.01856 -0.0668 0.8564 0.7495
-1.500 0.0473 0.02781 0.01876 -0.0620 0.8493 0.7950
-1.250 0.0615 0.02779 0.01872 -0.0582 0.8426 0.8335
-1.000 0.0883 0.02770 0.01851 -0.0573 0.8376 0.8602
-0.750 0.1094 0.02775 0.01844 -0.0565 0.8294 0.8782
-0.500 0.1480 0.02769 0.01821 -0.0585 0.8249 0.8951
-0.250 0.1764 0.02785 0.01827 -0.0593 0.8169 0.9139
0.000 0.2228 0.02789 0.01818 -0.0631 0.8117 0.9331
0.250 0.2676 0.02803 0.01819 -0.0671 0.8054 0.9589
0.500 0.3054 0.02815 0.01818 -0.0700 0.7980 1.0000
0.750 0.3322 0.02832 0.01822 -0.0707 0.7904 1.0000
1.000 0.3605 0.02852 0.01830 -0.0716 0.7826 1.0000
1.250 0.3868 0.02880 0.01847 -0.0722 0.7743 1.0000
1.500 0.4195 0.02895 0.01851 -0.0734 0.7672 1.0000
1.750 0.4436 0.02931 0.01879 -0.0735 0.7580 1.0000
2.000 0.4821 0.02921 0.01861 -0.0752 0.7512 1.0000
2.250 0.5077 0.02931 0.01865 -0.0750 0.7392 1.0000
2.500 0.5386 0.02917 0.01846 -0.0752 0.7276 1.0000
2.750 0.5823 0.02853 0.01775 -0.0768 0.7191 1.0000
3.000 0.6089 0.02848 0.01768 -0.0764 0.7066 1.0000
3.250 0.6326 0.02865 0.01785 -0.0757 0.6944 1.0000
3.500 0.6594 0.02869 0.01788 -0.0754 0.6831 1.0000
3.750 0.6986 0.02821 0.01740 -0.0764 0.6753 1.0000
4.000 0.7211 0.02838 0.01761 -0.0755 0.6622 1.0000
4.250 0.7451 0.02847 0.01773 -0.0747 0.6490 1.0000
4.500 0.7702 0.02850 0.01779 -0.0740 0.6355 1.0000
4.750 0.7956 0.02850 0.01783 -0.0733 0.6217 1.0000
5.000 0.8211 0.02848 0.01788 -0.0725 0.6073 1.0000
5.250 0.8465 0.02843 0.01788 -0.0717 0.5916 1.0000
5.500 0.8722 0.02838 0.01787 -0.0709 0.5753 1.0000
5.750 0.8991 0.02828 0.01783 -0.0702 0.5583 1.0000
6.000 0.9240 0.02829 0.01785 -0.0693 0.5395 1.0000
6.250 0.9454 0.02849 0.01808 -0.0680 0.5189 1.0000
6.500 0.9723 0.02851 0.01811 -0.0673 0.4990 1.0000
6.750 0.9956 0.02877 0.01833 -0.0663 0.4781 1.0000
7.000 1.0182 0.02914 0.01867 -0.0653 0.4578 1.0000
7.250 1.0423 0.02954 0.01899 -0.0645 0.4388 1.0000
7.500 1.0639 0.03012 0.01955 -0.0636 0.4208 1.0000
7.750 1.0836 0.03083 0.02026 -0.0625 0.4040 1.0000
8.000 1.1034 0.03159 0.02101 -0.0614 0.3883 1.0000
8.250 1.1234 0.03238 0.02181 -0.0605 0.3739 1.0000
8.500 1.1433 0.03321 0.02268 -0.0595 0.3602 1.0000
8.750 1.1641 0.03403 0.02352 -0.0587 0.3474 1.0000
9.000 1.1802 0.03501 0.02461 -0.0574 0.3349 1.0000
9.250 1.1964 0.03604 0.02574 -0.0562 0.3231 1.0000
9.500 1.2135 0.03706 0.02684 -0.0551 0.3117 1.0000
9.750 1.2322 0.03803 0.02790 -0.0542 0.3007 1.0000
10.000 1.2498 0.03905 0.02898 -0.0531 0.2897 1.0000
10.250 1.2601 0.04038 0.03048 -0.0514 0.2789 1.0000
10.500 1.2738 0.04162 0.03183 -0.0501 0.2685 1.0000
10.750 1.2902 0.04272 0.03296 -0.0490 0.2579 1.0000
11.000 1.2956 0.04432 0.03482 -0.0471 0.2479 1.0000
11.250 1.3033 0.04589 0.03655 -0.0455 0.2382 1.0000
11.500 1.3162 0.04713 0.03783 -0.0443 0.2285 1.0000
11.750 1.3141 0.04928 0.04027 -0.0422 0.2197 1.0000
12.000 1.3194 0.05103 0.04216 -0.0407 0.2110 1.0000
12.250 1.3214 0.05297 0.04426 -0.0392 0.2024 1.0000
12.500 1.3190 0.05546 0.04698 -0.0377 0.1944 1.0000
12.750 1.3250 0.05713 0.04871 -0.0365 0.1863 1.0000
13.000 1.3135 0.06061 0.05250 -0.0353 0.1791 1.0000
13.250 1.3186 0.06234 0.05424 -0.0344 0.1714 1.0000
13.500 1.3022 0.06673 0.05901 -0.0339 0.1651 1.0000
13.750 1.3077 0.06852 0.06079 -0.0332 0.1578 1.0000
14.000 1.2858 0.07406 0.06667 -0.0336 0.1524 1.0000
14.250 1.2862 0.07653 0.06917 -0.0334 0.1455 1.0000
14.500 1.2655 0.08252 0.07541 -0.0346 0.1409 1.0000
14.750 1.2444 0.08894 0.08204 -0.0364 0.1364 1.0000
15.000 1.2477 0.09135 0.08446 -0.0366 0.1297 1.0000
15.250 1.2090 0.10176 0.09515 -0.0410 0.1276 1.0000
15.500 1.1411 0.11971 0.11321 -0.0504 0.1274 1.0000
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