HQ 3.5/13 AIRFOIL (hq3513-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/13 AIRFOIL (hq3513-il) Reynolds number: 100,000 Max Cl/Cd: 56.85 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3513-il-100000.txt Download as CSV file: xf-hq3513-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3317 0.10195 0.09810 -0.0274 1.0000 0.1156
-8.500 -0.3637 0.09989 0.09614 -0.0284 1.0000 0.1179
-8.250 -0.3976 0.09775 0.09410 -0.0293 1.0000 0.1185
-8.000 -0.3736 0.09375 0.09011 -0.0257 0.9996 0.1214
-7.750 -0.3544 0.08989 0.08622 -0.0271 0.9959 0.1272
-7.500 -0.3805 0.08485 0.08125 -0.0338 0.9898 0.1326
-7.250 -0.5141 0.08776 0.08403 -0.0312 0.9992 0.1203
-7.000 -0.4828 0.08680 0.08306 -0.0251 0.9970 0.1256
-6.750 -0.4916 0.07681 0.07287 -0.0453 0.9857 0.1349
-6.500 -0.4618 0.07485 0.07102 -0.0422 0.9832 0.1400
-6.250 -0.4583 0.06878 0.06477 -0.0502 0.9745 0.1514
-6.000 -0.4412 0.04912 0.04344 -0.0647 0.9684 0.0772
-5.750 -0.4193 0.04475 0.03878 -0.0656 0.9630 0.0709
-5.500 -0.3891 0.04043 0.03383 -0.0682 0.9584 0.0705
-5.250 -0.3549 0.03712 0.02981 -0.0704 0.9546 0.0730
-5.000 -0.3297 0.03472 0.02676 -0.0703 0.9490 0.0748
-4.750 -0.2980 0.03250 0.02444 -0.0721 0.9445 0.0826
-4.500 -0.2589 0.03070 0.02223 -0.0744 0.9411 0.0932
-4.250 -0.2371 0.03000 0.02132 -0.0737 0.9346 0.1024
-4.000 -0.2042 0.02873 0.02001 -0.0750 0.9298 0.1124
-3.750 -0.1642 0.02771 0.01886 -0.0772 0.9263 0.1223
-3.500 -0.1448 0.02720 0.01832 -0.0759 0.9193 0.1310
-3.250 -0.1114 0.02645 0.01767 -0.0771 0.9144 0.1439
-3.000 -0.0763 0.02586 0.01716 -0.0785 0.9100 0.1627
-2.750 -0.0566 0.02533 0.01684 -0.0776 0.9027 0.1908
-2.500 -0.0290 0.02338 0.01686 -0.0780 0.8984 0.5462
-2.250 -0.0133 0.02399 0.01763 -0.0746 0.8913 0.6571
-2.000 0.0094 0.02451 0.01813 -0.0726 0.8846 0.7054
-1.750 0.0331 0.02494 0.01851 -0.0709 0.8786 0.7403
-1.500 0.0499 0.02524 0.01878 -0.0683 0.8707 0.7676
-1.000 0.0853 0.02560 0.01910 -0.0629 0.8566 0.8254
-0.750 0.1066 0.02548 0.01899 -0.0598 0.8516 0.8661
-0.500 0.1090 0.02552 0.01907 -0.0547 0.8421 0.8994
-0.250 0.1491 0.02540 0.01891 -0.0560 0.8374 0.9310
0.000 0.1888 0.02566 0.01910 -0.0591 0.8297 0.9523
0.250 0.2482 0.02574 0.01906 -0.0654 0.8244 0.9693
0.500 0.3173 0.02560 0.01879 -0.0731 0.8213 0.9838
0.750 0.3379 0.02579 0.01891 -0.0735 0.8098 1.0000
1.000 0.3967 0.02517 0.01817 -0.0784 0.8049 1.0000
1.250 0.4231 0.02502 0.01795 -0.0787 0.7934 1.0000
1.500 0.4565 0.02478 0.01764 -0.0798 0.7826 1.0000
1.750 0.5132 0.02386 0.01664 -0.0839 0.7778 1.0000
2.000 0.5394 0.02394 0.01668 -0.0841 0.7671 1.0000
2.250 0.5887 0.02321 0.01590 -0.0870 0.7628 1.0000
2.500 0.6142 0.02332 0.01599 -0.0869 0.7519 1.0000
2.750 0.6624 0.02251 0.01515 -0.0895 0.7473 1.0000
3.000 0.6884 0.02253 0.01516 -0.0892 0.7360 1.0000
3.250 0.7370 0.02159 0.01418 -0.0916 0.7312 1.0000
3.500 0.7626 0.02154 0.01415 -0.0910 0.7189 1.0000
3.750 0.7922 0.02132 0.01393 -0.0908 0.7076 1.0000
4.000 0.8313 0.02068 0.01327 -0.0919 0.6986 1.0000
4.250 0.8666 0.02014 0.01275 -0.0923 0.6871 1.0000
4.500 0.8960 0.01984 0.01245 -0.0920 0.6730 1.0000
4.750 0.9265 0.01949 0.01209 -0.0917 0.6580 1.0000
5.000 0.9577 0.01911 0.01170 -0.0915 0.6416 1.0000
5.250 0.9809 0.01901 0.01162 -0.0902 0.6206 1.0000
5.500 1.0088 0.01875 0.01131 -0.0895 0.5986 1.0000
5.750 1.0322 0.01870 0.01122 -0.0882 0.5721 1.0000
6.000 1.0556 0.01873 0.01115 -0.0869 0.5430 1.0000
6.250 1.0779 0.01896 0.01122 -0.0855 0.5127 1.0000
6.500 1.0994 0.01939 0.01146 -0.0842 0.4838 1.0000
6.750 1.1214 0.01995 0.01185 -0.0831 0.4584 1.0000
7.000 1.1428 0.02060 0.01236 -0.0821 0.4360 1.0000
7.250 1.1664 0.02130 0.01290 -0.0815 0.4173 1.0000
7.500 1.1876 0.02203 0.01358 -0.0805 0.3999 1.0000
7.750 1.2097 0.02278 0.01430 -0.0797 0.3845 1.0000
8.000 1.2319 0.02354 0.01502 -0.0790 0.3701 1.0000
8.250 1.2545 0.02432 0.01575 -0.0783 0.3565 1.0000
8.500 1.2750 0.02508 0.01653 -0.0774 0.3432 1.0000
8.750 1.2939 0.02586 0.01740 -0.0762 0.3302 1.0000
9.000 1.3126 0.02668 0.01827 -0.0749 0.3176 1.0000
9.250 1.3319 0.02756 0.01919 -0.0739 0.3055 1.0000
9.500 1.3518 0.02848 0.02012 -0.0729 0.2935 1.0000
9.750 1.3732 0.02946 0.02108 -0.0722 0.2814 1.0000
10.000 1.3910 0.03042 0.02207 -0.0710 0.2691 1.0000
10.250 1.4031 0.03142 0.02325 -0.0689 0.2573 1.0000
10.500 1.4168 0.03250 0.02443 -0.0671 0.2456 1.0000
10.750 1.4311 0.03354 0.02550 -0.0654 0.2340 1.0000
11.000 1.4460 0.03450 0.02643 -0.0639 0.2223 1.0000
11.250 1.4467 0.03541 0.02758 -0.0602 0.2122 1.0000
11.500 1.4494 0.03645 0.02875 -0.0569 0.2023 1.0000
11.750 1.4568 0.03738 0.02965 -0.0545 0.1924 1.0000
12.000 1.4543 0.03846 0.03088 -0.0509 0.1833 1.0000
12.250 1.4527 0.03975 0.03231 -0.0478 0.1742 1.0000
12.500 1.4562 0.04085 0.03335 -0.0455 0.1651 1.0000
12.750 1.4489 0.04245 0.03518 -0.0424 0.1566 1.0000
13.000 1.4451 0.04413 0.03693 -0.0400 0.1481 1.0000
13.250 1.4431 0.04570 0.03843 -0.0381 0.1394 1.0000
13.500 1.4327 0.04810 0.04109 -0.0359 0.1311 1.0000
13.750 1.4261 0.05041 0.04341 -0.0344 0.1229 1.0000
14.000 1.4171 0.05304 0.04615 -0.0332 0.1147 1.0000
14.250 1.4069 0.05621 0.04948 -0.0323 0.1067 1.0000
14.500 1.3986 0.05931 0.05251 -0.0317 0.0990 1.0000
14.750 1.3860 0.06325 0.05669 -0.0316 0.0916 1.0000
15.000 1.3759 0.06721 0.06070 -0.0316 0.0844 1.0000
15.250 1.3638 0.07160 0.06517 -0.0321 0.0776 1.0000
15.500 1.3505 0.07654 0.07024 -0.0329 0.0709 1.0000
15.750 1.3387 0.08131 0.07496 -0.0340 0.0647 1.0000
16.000 1.3239 0.08707 0.08095 -0.0356 0.0594 1.0000
16.250 1.3138 0.09205 0.08590 -0.0371 0.0545 1.0000
16.500 1.3028 0.09759 0.09161 -0.0388 0.0506 1.0000
16.750 1.2925 0.10317 0.09735 -0.0409 0.0473 1.0000
17.000 1.2962 0.10605 0.10005 -0.0408 0.0433 1.0000
17.250 1.2838 0.11234 0.10665 -0.0436 0.0421 1.0000
17.500 1.2715 0.11877 0.11334 -0.0467 0.0410 1.0000
17.750 1.2579 0.12564 0.12045 -0.0502 0.0402 1.0000
18.000 1.2429 0.13304 0.12807 -0.0544 0.0398 1.0000
18.250 1.2236 0.14169 0.13694 -0.0597 0.0398 1.0000
18.500 1.1969 0.15256 0.14805 -0.0668 0.0405 1.0000
18.750 1.1642 0.16567 0.16134 -0.0755 0.0418 1.0000
19.000 1.1319 0.17972 0.17547 -0.0846 0.0431 1.0000
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