HQ 3.5/13 AIRFOIL (hq3513-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/13 AIRFOIL (hq3513-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.38 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3513-il-1000000.txt Download as CSV file: xf-hq3513-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6451 0.05425 0.05228 -0.0769 1.0000 0.0080
-12.250 -0.6925 0.04451 0.04233 -0.0830 1.0000 0.0079
-12.000 -0.7147 0.03506 0.03249 -0.0947 0.9932 0.0077
-11.750 -0.7028 0.03120 0.02841 -0.1012 0.9853 0.0078
-11.500 -0.6853 0.02813 0.02511 -0.1058 0.9784 0.0079
-11.250 -0.6647 0.02521 0.02190 -0.1093 0.9723 0.0080
-11.000 -0.6428 0.02335 0.01984 -0.1110 0.9642 0.0081
-10.750 -0.6207 0.02169 0.01795 -0.1121 0.9557 0.0082
-10.500 -0.6025 0.02062 0.01674 -0.1116 0.9443 0.0084
-10.250 -0.5851 0.01941 0.01534 -0.1109 0.9339 0.0085
-10.000 -0.5664 0.01830 0.01405 -0.1101 0.9246 0.0086
-9.750 -0.5465 0.01744 0.01305 -0.1093 0.9157 0.0087
-9.500 -0.5254 0.01662 0.01208 -0.1087 0.9081 0.0089
-9.250 -0.5037 0.01588 0.01119 -0.1080 0.9006 0.0090
-9.000 -0.4810 0.01520 0.01039 -0.1075 0.8939 0.0091
-8.750 -0.4572 0.01469 0.00978 -0.1070 0.8869 0.0093
-8.500 -0.4378 0.01343 0.00833 -0.1062 0.8803 0.0098
-8.250 -0.4141 0.01281 0.00765 -0.1057 0.8739 0.0103
-8.000 -0.3894 0.01234 0.00710 -0.1054 0.8678 0.0106
-7.750 -0.3641 0.01190 0.00658 -0.1050 0.8620 0.0111
-7.500 -0.3386 0.01148 0.00609 -0.1048 0.8560 0.0115
-7.250 -0.3127 0.01113 0.00565 -0.1045 0.8504 0.0120
-7.000 -0.2869 0.01068 0.00515 -0.1042 0.8445 0.0126
-6.750 -0.2610 0.01028 0.00468 -0.1040 0.8388 0.0136
-6.500 -0.2344 0.00999 0.00435 -0.1038 0.8334 0.0149
-6.250 -0.2077 0.00965 0.00399 -0.1037 0.8275 0.0175
-6.000 -0.1809 0.00939 0.00375 -0.1035 0.8220 0.0235
-5.750 -0.1534 0.00922 0.00360 -0.1035 0.8166 0.0295
-5.500 -0.1255 0.00914 0.00349 -0.1035 0.8108 0.0326
-5.250 -0.0983 0.00895 0.00328 -0.1034 0.8054 0.0366
-5.000 -0.0704 0.00882 0.00315 -0.1035 0.7997 0.0390
-4.750 -0.0425 0.00873 0.00300 -0.1035 0.7941 0.0406
-4.500 -0.0152 0.00850 0.00275 -0.1034 0.7887 0.0449
-4.250 0.0127 0.00836 0.00261 -0.1034 0.7828 0.0483
-4.000 0.0405 0.00827 0.00247 -0.1034 0.7772 0.0516
-3.750 0.0682 0.00807 0.00229 -0.1034 0.7714 0.0591
-3.500 0.0959 0.00793 0.00213 -0.1034 0.7650 0.0672
-3.250 0.1235 0.00778 0.00199 -0.1034 0.7585 0.0799
-3.000 0.1510 0.00758 0.00185 -0.1033 0.7507 0.1032
-2.750 0.1778 0.00728 0.00171 -0.1033 0.7433 0.1568
-2.500 0.2045 0.00691 0.00158 -0.1033 0.7356 0.2397
-2.250 0.2305 0.00641 0.00143 -0.1033 0.7293 0.3626
-2.000 0.2575 0.00607 0.00137 -0.1033 0.7230 0.4589
-1.750 0.2849 0.00595 0.00135 -0.1033 0.7167 0.5096
-1.500 0.3130 0.00588 0.00134 -0.1033 0.7100 0.5436
-1.250 0.3409 0.00586 0.00134 -0.1032 0.7035 0.5692
-1.000 0.3691 0.00586 0.00135 -0.1033 0.6977 0.5915
-0.750 0.3973 0.00587 0.00135 -0.1033 0.6908 0.6063
-0.500 0.4252 0.00589 0.00137 -0.1032 0.6838 0.6187
-0.250 0.4532 0.00592 0.00140 -0.1032 0.6762 0.6384
0.000 0.4810 0.00596 0.00144 -0.1031 0.6692 0.6542
0.250 0.5090 0.00598 0.00147 -0.1031 0.6618 0.6625
0.500 0.5369 0.00604 0.00149 -0.1030 0.6547 0.6709
0.750 0.5649 0.00606 0.00152 -0.1030 0.6468 0.6793
1.000 0.5926 0.00612 0.00155 -0.1029 0.6385 0.6859
1.250 0.6203 0.00616 0.00158 -0.1029 0.6298 0.6913
1.500 0.6481 0.00622 0.00162 -0.1029 0.6211 0.6972
1.750 0.6753 0.00629 0.00166 -0.1027 0.6112 0.7028
2.000 0.7027 0.00634 0.00171 -0.1026 0.5993 0.7086
2.250 0.7298 0.00644 0.00177 -0.1025 0.5859 0.7144
2.500 0.7564 0.00652 0.00183 -0.1022 0.5717 0.7202
2.750 0.7827 0.00665 0.00191 -0.1019 0.5554 0.7267
3.000 0.8082 0.00681 0.00201 -0.1015 0.5355 0.7327
3.250 0.8333 0.00698 0.00212 -0.1010 0.5117 0.7393
3.500 0.8578 0.00722 0.00226 -0.1004 0.4849 0.7462
3.750 0.8813 0.00749 0.00243 -0.0997 0.4557 0.7530
4.000 0.9045 0.00781 0.00261 -0.0989 0.4250 0.7605
4.250 0.9271 0.00812 0.00282 -0.0980 0.3940 0.7679
4.500 0.9496 0.00846 0.00304 -0.0972 0.3633 0.7762
4.750 0.9714 0.00882 0.00328 -0.0962 0.3311 0.7847
5.000 0.9934 0.00916 0.00352 -0.0952 0.3048 0.7940
5.250 1.0159 0.00945 0.00375 -0.0943 0.2872 0.8044
5.500 1.0390 0.00967 0.00397 -0.0936 0.2755 0.8160
5.750 1.0618 0.00989 0.00420 -0.0927 0.2655 0.8301
6.000 1.0843 0.01008 0.00441 -0.0918 0.2567 0.8486
6.250 1.1051 0.01016 0.00461 -0.0905 0.2491 0.8856
6.500 1.1350 0.01027 0.00484 -0.0912 0.2420 1.0000
6.750 1.1586 0.01050 0.00507 -0.0906 0.2361 1.0000
7.000 1.1824 0.01071 0.00528 -0.0900 0.2302 1.0000
7.250 1.2043 0.01101 0.00554 -0.0891 0.2230 1.0000
7.500 1.2281 0.01120 0.00575 -0.0885 0.2174 1.0000
7.750 1.2489 0.01151 0.00602 -0.0874 0.2084 1.0000
8.000 1.2711 0.01173 0.00624 -0.0865 0.2008 1.0000
8.250 1.2901 0.01203 0.00652 -0.0850 0.1930 1.0000
8.500 1.3089 0.01233 0.00679 -0.0836 0.1836 1.0000
8.750 1.3263 0.01268 0.00710 -0.0819 0.1719 1.0000
9.000 1.3418 0.01312 0.00748 -0.0799 0.1577 1.0000
9.250 1.3562 0.01363 0.00791 -0.0778 0.1430 1.0000
9.500 1.3693 0.01421 0.00840 -0.0756 0.1282 1.0000
9.750 1.3823 0.01482 0.00895 -0.0735 0.1151 1.0000
10.000 1.3963 0.01539 0.00949 -0.0715 0.1048 1.0000
10.250 1.4087 0.01607 0.01012 -0.0694 0.0931 1.0000
10.500 1.4210 0.01677 0.01078 -0.0674 0.0827 1.0000
10.750 1.4325 0.01754 0.01150 -0.0653 0.0728 1.0000
11.000 1.4427 0.01842 0.01232 -0.0632 0.0623 1.0000
11.250 1.4521 0.01937 0.01322 -0.0610 0.0520 1.0000
11.500 1.4608 0.02039 0.01419 -0.0589 0.0422 1.0000
11.750 1.4673 0.02160 0.01534 -0.0567 0.0312 1.0000
12.000 1.4691 0.02318 0.01683 -0.0540 0.0190 1.0000
12.250 1.4720 0.02474 0.01836 -0.0517 0.0113 1.0000
12.500 1.4760 0.02629 0.01991 -0.0496 0.0072 1.0000
12.750 1.4831 0.02766 0.02133 -0.0480 0.0060 1.0000
13.000 1.4901 0.02907 0.02280 -0.0464 0.0054 1.0000
13.250 1.4974 0.03051 0.02431 -0.0450 0.0051 1.0000
13.500 1.5051 0.03195 0.02582 -0.0438 0.0048 1.0000
13.750 1.5114 0.03356 0.02750 -0.0425 0.0046 1.0000
14.000 1.5172 0.03525 0.02927 -0.0414 0.0045 1.0000
14.250 1.5210 0.03719 0.03129 -0.0403 0.0043 1.0000
14.500 1.5255 0.03911 0.03329 -0.0394 0.0042 1.0000
14.750 1.5268 0.04143 0.03570 -0.0384 0.0041 1.0000
15.000 1.5278 0.04387 0.03823 -0.0377 0.0040 1.0000
15.250 1.5272 0.04657 0.04103 -0.0371 0.0039 1.0000
15.500 1.5230 0.04980 0.04438 -0.0367 0.0038 1.0000
15.750 1.5179 0.05328 0.04798 -0.0365 0.0037 1.0000
16.000 1.5107 0.05717 0.05199 -0.0366 0.0037 1.0000
16.250 1.5023 0.06140 0.05635 -0.0371 0.0036 1.0000
16.500 1.4973 0.06535 0.06041 -0.0377 0.0036 1.0000
16.750 1.4910 0.06966 0.06483 -0.0386 0.0036 1.0000
17.000 1.4848 0.07408 0.06936 -0.0398 0.0035 1.0000
17.250 1.4736 0.07946 0.07487 -0.0415 0.0036 1.0000
17.500 1.4634 0.08487 0.08041 -0.0434 0.0035 1.0000
17.750 1.4515 0.09074 0.08641 -0.0456 0.0035 1.0000
18.000 1.4401 0.09669 0.09248 -0.0481 0.0035 1.0000
18.250 1.4254 0.10339 0.09931 -0.0510 0.0035 1.0000
18.500 1.4112 0.11017 0.10622 -0.0542 0.0035 1.0000
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