HQ 3.5/12 AIRFOIL (hq3512-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/12 AIRFOIL (hq3512-il) Reynolds number: 50,000 Max Cl/Cd: 37.34 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3512-il-50000-n5.txt Download as CSV file: xf-hq3512-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/12 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3347 0.10497 0.09817 -0.0455 1.0000 0.0561
-9.250 -0.3395 0.10190 0.09520 -0.0454 1.0000 0.0548
-9.000 -0.3472 0.09882 0.09223 -0.0452 1.0000 0.0534
-8.500 -0.3962 0.09071 0.08446 -0.0476 1.0000 0.0480
-8.250 -0.4079 0.08846 0.08231 -0.0456 1.0000 0.0477
-8.000 -0.4247 0.08610 0.08005 -0.0439 1.0000 0.0475
-7.750 -0.4383 0.08345 0.07749 -0.0431 1.0000 0.0471
-7.500 -0.4524 0.08033 0.07444 -0.0429 1.0000 0.0468
-7.250 -0.4643 0.07719 0.07132 -0.0425 1.0000 0.0464
-7.000 -0.4726 0.07346 0.06755 -0.0432 0.9993 0.0461
-6.750 -0.4596 0.06742 0.06130 -0.0495 0.9917 0.0456
-6.500 -0.4439 0.06143 0.05499 -0.0554 0.9846 0.0453
-6.250 -0.4273 0.05608 0.04922 -0.0597 0.9775 0.0452
-6.000 -0.4031 0.05094 0.04351 -0.0640 0.9719 0.0455
-5.750 -0.3812 0.04669 0.03868 -0.0663 0.9653 0.0461
-5.500 -0.3518 0.04273 0.03392 -0.0690 0.9603 0.0479
-5.250 -0.3253 0.04037 0.03141 -0.0707 0.9553 0.0516
-5.000 -0.2978 0.03818 0.02884 -0.0718 0.9496 0.0557
-4.750 -0.2638 0.03577 0.02571 -0.0734 0.9453 0.0615
-4.500 -0.2365 0.03418 0.02405 -0.0741 0.9402 0.0682
-4.250 -0.2075 0.03266 0.02218 -0.0746 0.9348 0.0776
-4.000 -0.1743 0.03149 0.02073 -0.0756 0.9306 0.0894
-3.750 -0.1487 0.03044 0.01967 -0.0753 0.9250 0.0989
-3.500 -0.1205 0.02960 0.01875 -0.0755 0.9195 0.1120
-3.250 -0.0872 0.02874 0.01776 -0.0766 0.9155 0.1247
-3.000 -0.0635 0.02811 0.01709 -0.0763 0.9087 0.1415
-2.750 -0.0315 0.02732 0.01639 -0.0778 0.9036 0.1761
-2.500 0.0012 0.02565 0.01584 -0.0801 0.8997 0.3434
-2.250 0.0146 0.02542 0.01647 -0.0765 0.8920 0.5821
-2.000 0.0403 0.02569 0.01670 -0.0750 0.8868 0.6734
-1.750 0.0535 0.02595 0.01695 -0.0714 0.8787 0.7290
-1.500 0.0674 0.02603 0.01712 -0.0667 0.8729 0.8002
-1.250 0.0733 0.02594 0.01710 -0.0610 0.8648 0.8574
-1.000 0.1036 0.02579 0.01686 -0.0604 0.8596 0.9036
-0.750 0.1453 0.02585 0.01670 -0.0635 0.8539 0.9268
-0.500 0.1906 0.02594 0.01660 -0.0676 0.8474 0.9564
-0.250 0.2404 0.02595 0.01636 -0.0724 0.8429 1.0000
0.000 0.2593 0.02621 0.01645 -0.0722 0.8330 1.0000
0.250 0.2995 0.02628 0.01632 -0.0750 0.8280 1.0000
0.750 0.3580 0.02674 0.01648 -0.0769 0.8122 1.0000
1.000 0.3824 0.02708 0.01669 -0.0771 0.8027 1.0000
1.250 0.4125 0.02733 0.01683 -0.0780 0.7948 1.0000
1.500 0.4450 0.02750 0.01691 -0.0791 0.7871 1.0000
1.750 0.4707 0.02782 0.01716 -0.0791 0.7775 1.0000
2.000 0.5114 0.02766 0.01693 -0.0810 0.7706 1.0000
2.250 0.5389 0.02768 0.01690 -0.0808 0.7581 1.0000
2.500 0.5689 0.02754 0.01673 -0.0807 0.7453 1.0000
2.750 0.5995 0.02736 0.01651 -0.0807 0.7327 1.0000
3.000 0.6307 0.02719 0.01632 -0.0807 0.7211 1.0000
3.250 0.6674 0.02686 0.01601 -0.0815 0.7123 1.0000
3.500 0.6920 0.02697 0.01615 -0.0808 0.6995 1.0000
3.750 0.7179 0.02702 0.01622 -0.0803 0.6866 1.0000
4.000 0.7447 0.02702 0.01625 -0.0797 0.6736 1.0000
4.250 0.7719 0.02697 0.01628 -0.0792 0.6601 1.0000
4.500 0.7989 0.02693 0.01629 -0.0786 0.6460 1.0000
4.750 0.8255 0.02687 0.01629 -0.0779 0.6306 1.0000
5.000 0.8522 0.02679 0.01630 -0.0772 0.6142 1.0000
5.250 0.8799 0.02667 0.01623 -0.0766 0.5972 1.0000
5.500 0.9027 0.02676 0.01639 -0.0754 0.5769 1.0000
5.750 0.9278 0.02678 0.01645 -0.0744 0.5559 1.0000
6.000 0.9530 0.02684 0.01656 -0.0735 0.5338 1.0000
6.250 0.9786 0.02693 0.01663 -0.0726 0.5104 1.0000
6.500 1.0017 0.02723 0.01693 -0.0715 0.4863 1.0000
6.750 1.0262 0.02755 0.01720 -0.0706 0.4633 1.0000
7.000 1.0476 0.02810 0.01772 -0.0695 0.4410 1.0000
7.250 1.0706 0.02867 0.01821 -0.0686 0.4210 1.0000
7.500 1.0901 0.02944 0.01900 -0.0674 0.4016 1.0000
7.750 1.1103 0.03023 0.01980 -0.0664 0.3841 1.0000
8.000 1.1304 0.03106 0.02068 -0.0654 0.3679 1.0000
8.250 1.1500 0.03193 0.02160 -0.0644 0.3527 1.0000
8.500 1.1690 0.03284 0.02257 -0.0633 0.3383 1.0000
8.750 1.1872 0.03378 0.02359 -0.0622 0.3245 1.0000
9.000 1.2048 0.03475 0.02466 -0.0610 0.3113 1.0000
9.250 1.2215 0.03577 0.02580 -0.0597 0.2983 1.0000
9.500 1.2378 0.03683 0.02695 -0.0584 0.2856 1.0000
9.750 1.2533 0.03793 0.02813 -0.0570 0.2730 1.0000
10.000 1.2690 0.03906 0.02933 -0.0557 0.2607 1.0000
10.250 1.2790 0.04035 0.03079 -0.0538 0.2486 1.0000
10.500 1.2870 0.04179 0.03243 -0.0519 0.2369 1.0000
10.750 1.2949 0.04325 0.03406 -0.0500 0.2256 1.0000
11.000 1.3026 0.04470 0.03569 -0.0482 0.2148 1.0000
11.250 1.3095 0.04619 0.03730 -0.0464 0.2042 1.0000
11.500 1.3086 0.04819 0.03957 -0.0443 0.1938 1.0000
11.750 1.3091 0.05015 0.04171 -0.0425 0.1838 1.0000
12.000 1.3109 0.05201 0.04365 -0.0408 0.1743 1.0000
12.250 1.3071 0.05444 0.04630 -0.0393 0.1647 1.0000
12.500 1.3023 0.05714 0.04918 -0.0380 0.1555 1.0000
12.750 1.2999 0.05959 0.05169 -0.0370 0.1469 1.0000
13.000 1.2922 0.06284 0.05514 -0.0363 0.1383 1.0000
13.250 1.2841 0.06635 0.05879 -0.0359 0.1302 1.0000
13.500 1.2787 0.06944 0.06187 -0.0357 0.1224 1.0000
13.750 1.2653 0.07420 0.06691 -0.0362 0.1151 1.0000
14.000 1.2573 0.07802 0.07071 -0.0367 0.1078 1.0000
14.250 1.2432 0.08346 0.07642 -0.0381 0.1015 1.0000
14.500 1.2345 0.08786 0.08080 -0.0393 0.0949 1.0000
14.750 1.2180 0.09432 0.08755 -0.0416 0.0898 1.0000
15.000 1.2114 0.09868 0.09186 -0.0432 0.0832 1.0000
15.250 1.1925 0.10636 0.09986 -0.0466 0.0797 1.0000
15.500 1.1784 0.11308 0.10673 -0.0499 0.0753 1.0000
15.750 1.1696 0.11865 0.11228 -0.0527 0.0700 1.0000
16.000 1.1491 0.12780 0.12164 -0.0575 0.0684 1.0000
16.250 1.1246 0.13857 0.13260 -0.0635 0.0684 1.0000
16.500 1.0944 0.15193 0.14602 -0.0711 0.0694 1.0000
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