HQ 2.5/11 AIRFOIL (hq2511-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.5/11 AIRFOIL (hq2511-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.19 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2511-il-1000000-n5.txt Download as CSV file: xf-hq2511-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/11 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.7087 0.04858 0.04659 -0.0641 1.0000 0.0041
-11.500 -0.7316 0.04133 0.03916 -0.0703 1.0000 0.0041
-11.250 -0.7559 0.03684 0.03452 -0.0719 1.0000 0.0040
-11.000 -0.7662 0.03358 0.03105 -0.0721 0.9908 0.0041
-10.750 -0.7493 0.02990 0.02707 -0.0761 0.9826 0.0041
-10.500 -0.7273 0.02738 0.02428 -0.0787 0.9745 0.0042
-10.250 -0.7054 0.02489 0.02150 -0.0808 0.9657 0.0042
-10.000 -0.6815 0.02335 0.01976 -0.0819 0.9566 0.0043
-9.750 -0.6629 0.02184 0.01802 -0.0817 0.9447 0.0043
-9.500 -0.6432 0.02069 0.01670 -0.0812 0.9328 0.0044
-9.250 -0.6236 0.01956 0.01537 -0.0806 0.9200 0.0044
-9.000 -0.6026 0.01862 0.01426 -0.0800 0.9073 0.0044
-8.750 -0.5816 0.01765 0.01310 -0.0793 0.8954 0.0044
-8.250 -0.5361 0.01612 0.01126 -0.0783 0.8754 0.0045
-8.000 -0.5121 0.01553 0.01054 -0.0779 0.8672 0.0045
-7.750 -0.4891 0.01459 0.00945 -0.0774 0.8596 0.0046
-7.500 -0.4660 0.01365 0.00835 -0.0769 0.8531 0.0047
-7.250 -0.4413 0.01298 0.00758 -0.0766 0.8466 0.0048
-6.750 -0.3906 0.01190 0.00633 -0.0761 0.8343 0.0048
-6.500 -0.3649 0.01141 0.00575 -0.0759 0.8277 0.0049
-6.250 -0.3388 0.01097 0.00524 -0.0757 0.8214 0.0049
-6.000 -0.3124 0.01060 0.00479 -0.0755 0.8140 0.0049
-5.750 -0.2859 0.01021 0.00434 -0.0753 0.8072 0.0050
-5.500 -0.2590 0.00990 0.00397 -0.0752 0.7999 0.0051
-5.250 -0.2321 0.00960 0.00360 -0.0751 0.7935 0.0052
-5.000 -0.2048 0.00933 0.00328 -0.0750 0.7869 0.0053
-4.750 -0.1776 0.00911 0.00300 -0.0749 0.7806 0.0054
-4.500 -0.1500 0.00889 0.00273 -0.0749 0.7737 0.0057
-4.000 -0.0947 0.00855 0.00227 -0.0748 0.7599 0.0064
-3.750 -0.0670 0.00841 0.00209 -0.0748 0.7534 0.0068
-3.500 -0.0391 0.00827 0.00192 -0.0748 0.7474 0.0079
-3.250 -0.0116 0.00806 0.00174 -0.0748 0.7406 0.0181
-3.000 0.0162 0.00790 0.00161 -0.0748 0.7345 0.0286
-2.750 0.0439 0.00775 0.00150 -0.0748 0.7275 0.0420
-2.500 0.0716 0.00762 0.00141 -0.0748 0.7199 0.0568
-2.250 0.0995 0.00752 0.00132 -0.0748 0.7111 0.0709
-2.000 0.1272 0.00737 0.00123 -0.0749 0.7030 0.0959
-1.750 0.1543 0.00706 0.00112 -0.0749 0.6952 0.1668
-1.500 0.1818 0.00681 0.00104 -0.0750 0.6880 0.2292
-1.250 0.2079 0.00623 0.00093 -0.0751 0.6809 0.3851
-1.000 0.2354 0.00603 0.00089 -0.0752 0.6732 0.4496
-0.750 0.2627 0.00590 0.00087 -0.0751 0.6626 0.5017
-0.500 0.2902 0.00581 0.00087 -0.0751 0.6517 0.5467
-0.250 0.3179 0.00575 0.00090 -0.0750 0.6415 0.5885
0.000 0.3454 0.00573 0.00093 -0.0750 0.6309 0.6218
0.250 0.3732 0.00577 0.00096 -0.0749 0.6194 0.6373
0.500 0.4011 0.00582 0.00098 -0.0749 0.6065 0.6479
0.750 0.4289 0.00588 0.00101 -0.0749 0.5926 0.6568
1.000 0.4566 0.00596 0.00105 -0.0748 0.5775 0.6643
1.250 0.4835 0.00609 0.00110 -0.0746 0.5505 0.6717
1.500 0.5087 0.00639 0.00119 -0.0742 0.5002 0.6783
1.750 0.5336 0.00671 0.00133 -0.0737 0.4545 0.6858
2.000 0.5599 0.00692 0.00144 -0.0735 0.4291 0.6926
2.250 0.5869 0.00706 0.00153 -0.0734 0.4120 0.6984
2.500 0.6137 0.00723 0.00163 -0.0732 0.3903 0.7038
2.750 0.6396 0.00747 0.00176 -0.0729 0.3559 0.7092
3.000 0.6650 0.00776 0.00191 -0.0726 0.3203 0.7152
3.500 0.7168 0.00823 0.00222 -0.0720 0.2768 0.7265
3.750 0.7431 0.00841 0.00238 -0.0718 0.2616 0.7328
4.000 0.7694 0.00859 0.00253 -0.0716 0.2483 0.7395
4.250 0.7956 0.00877 0.00269 -0.0714 0.2344 0.7485
4.500 0.8213 0.00896 0.00287 -0.0711 0.2191 0.7594
4.750 0.8465 0.00919 0.00307 -0.0707 0.2016 0.7717
5.000 0.8712 0.00945 0.00328 -0.0703 0.1816 0.7845
5.250 0.8947 0.00982 0.00356 -0.0696 0.1527 0.7974
5.500 0.9183 0.01017 0.00383 -0.0690 0.1302 0.8111
5.750 0.9421 0.01045 0.00409 -0.0684 0.1154 0.8272
6.000 0.9663 0.01066 0.00434 -0.0678 0.1061 0.8467
6.250 0.9890 0.01085 0.00459 -0.0669 0.0961 0.8774
6.500 1.0168 0.01105 0.00489 -0.0671 0.0812 1.0000
6.750 1.0404 0.01144 0.00521 -0.0666 0.0681 1.0000
7.000 1.0595 0.01222 0.00576 -0.0654 0.0344 1.0000
7.250 1.0797 0.01288 0.00633 -0.0643 0.0170 1.0000
7.500 1.1027 0.01329 0.00673 -0.0636 0.0136 1.0000
7.750 1.1256 0.01368 0.00713 -0.0629 0.0120 1.0000
8.000 1.1478 0.01411 0.00758 -0.0621 0.0105 1.0000
8.250 1.1706 0.01447 0.00798 -0.0614 0.0098 1.0000
8.500 1.1927 0.01487 0.00841 -0.0606 0.0091 1.0000
8.750 1.2140 0.01531 0.00887 -0.0597 0.0085 1.0000
9.000 1.2344 0.01581 0.00940 -0.0586 0.0079 1.0000
9.250 1.2537 0.01638 0.01001 -0.0574 0.0074 1.0000
9.500 1.2736 0.01685 0.01054 -0.0563 0.0072 1.0000
9.750 1.2928 0.01733 0.01107 -0.0551 0.0070 1.0000
10.000 1.3105 0.01783 0.01160 -0.0536 0.0067 1.0000
10.250 1.3265 0.01833 0.01215 -0.0519 0.0063 1.0000
10.500 1.3416 0.01886 0.01272 -0.0500 0.0060 1.0000
10.750 1.3556 0.01946 0.01336 -0.0481 0.0058 1.0000
11.000 1.3686 0.02013 0.01409 -0.0461 0.0056 1.0000
11.250 1.3801 0.02092 0.01494 -0.0439 0.0054 1.0000
11.500 1.3886 0.02193 0.01604 -0.0415 0.0051 1.0000
11.750 1.3997 0.02278 0.01696 -0.0396 0.0050 1.0000
12.000 1.4112 0.02363 0.01787 -0.0379 0.0050 1.0000
12.250 1.4228 0.02450 0.01881 -0.0362 0.0048 1.0000
12.500 1.4313 0.02561 0.02001 -0.0344 0.0047 1.0000
12.750 1.4407 0.02670 0.02117 -0.0328 0.0046 1.0000
13.000 1.4496 0.02787 0.02242 -0.0313 0.0045 1.0000
13.250 1.4581 0.02911 0.02374 -0.0298 0.0043 1.0000
13.500 1.4632 0.03066 0.02539 -0.0283 0.0042 1.0000
13.750 1.4708 0.03207 0.02687 -0.0271 0.0041 1.0000
14.000 1.4794 0.03344 0.02829 -0.0261 0.0039 1.0000
14.250 1.4844 0.03518 0.03011 -0.0251 0.0038 1.0000
14.500 1.4882 0.03710 0.03212 -0.0242 0.0037 1.0000
14.750 1.4901 0.03929 0.03439 -0.0234 0.0037 1.0000
15.000 1.4911 0.04165 0.03685 -0.0228 0.0036 1.0000
15.250 1.4879 0.04459 0.03990 -0.0224 0.0035 1.0000
15.500 1.4829 0.04788 0.04330 -0.0222 0.0034 1.0000
15.750 1.4746 0.05177 0.04732 -0.0225 0.0033 1.0000
16.000 1.4656 0.05601 0.05169 -0.0232 0.0033 1.0000
16.250 1.4624 0.05968 0.05547 -0.0241 0.0032 1.0000
16.500 1.4549 0.06419 0.06011 -0.0254 0.0032 1.0000
16.750 1.4471 0.06900 0.06506 -0.0272 0.0032 1.0000
17.000 1.4341 0.07491 0.07111 -0.0296 0.0032 1.0000
17.250 1.4177 0.08171 0.07805 -0.0327 0.0032 1.0000
17.500 1.4065 0.08784 0.08432 -0.0357 0.0032 1.0000
17.750 1.3874 0.09564 0.09226 -0.0396 0.0032 1.0000
18.000 1.3710 0.10317 0.09993 -0.0436 0.0032 1.0000
18.250 1.3533 0.11121 0.10811 -0.0479 0.0031 1.0000
18.500 1.3348 0.11954 0.11657 -0.0525 0.0031 1.0000
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