HQ 3.5/9 AIRFOIL (hq359-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/9 AIRFOIL (hq359-il) Reynolds number: 100,000 Max Cl/Cd: 62.19 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq359-il-100000-n5.txt Download as CSV file: xf-hq359-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/9 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3695 0.09477 0.09036 -0.0357 1.0000 0.0418
-7.500 -0.3834 0.09329 0.08898 -0.0337 1.0000 0.0418
-7.250 -0.3940 0.09115 0.08693 -0.0335 1.0000 0.0419
-7.000 -0.3878 0.08703 0.08283 -0.0393 0.9969 0.0421
-6.750 -0.3650 0.08100 0.07670 -0.0494 0.9900 0.0422
-6.500 -0.3422 0.07549 0.07106 -0.0567 0.9843 0.0423
-6.000 -0.3123 0.06446 0.06008 -0.0587 0.9755 0.0260
-5.750 -0.2888 0.05855 0.05401 -0.0657 0.9687 0.0238
-5.500 -0.2576 0.05093 0.04604 -0.0742 0.9626 0.0211
-5.000 -0.1994 0.04131 0.03571 -0.0826 0.9516 0.0210
-4.750 -0.1669 0.03829 0.03241 -0.0861 0.9479 0.0232
-4.500 -0.1367 0.03464 0.02831 -0.0882 0.9427 0.0235
-4.250 -0.1041 0.03094 0.02400 -0.0901 0.9380 0.0230
-4.000 -0.0677 0.02775 0.02023 -0.0922 0.9350 0.0229
-3.750 -0.0329 0.02526 0.01721 -0.0936 0.9316 0.0233
-3.500 -0.0041 0.02344 0.01502 -0.0936 0.9260 0.0240
-3.250 0.0303 0.02175 0.01302 -0.0946 0.9227 0.0254
-3.000 0.0664 0.02059 0.01162 -0.0960 0.9201 0.0292
-2.750 0.0923 0.01956 0.01058 -0.0958 0.9138 0.0343
-2.500 0.1244 0.01863 0.00949 -0.0965 0.9095 0.0408
-2.250 0.1594 0.01773 0.00857 -0.0979 0.9064 0.0650
-2.000 0.1855 0.01719 0.00816 -0.0979 0.8996 0.1117
-1.750 0.2158 0.01551 0.00773 -0.0994 0.8954 0.4331
-1.500 0.2432 0.01505 0.00788 -0.0985 0.8916 0.6709
-1.250 0.2617 0.01500 0.00792 -0.0958 0.8835 0.7513
-1.000 0.2867 0.01475 0.00773 -0.0941 0.8791 0.8177
-0.750 0.3048 0.01452 0.00758 -0.0913 0.8711 0.8786
-0.500 0.3460 0.01425 0.00723 -0.0936 0.8669 0.9344
-0.250 0.3820 0.01420 0.00701 -0.0955 0.8599 1.0000
0.000 0.4154 0.01418 0.00682 -0.0967 0.8533 1.0000
0.250 0.4449 0.01422 0.00673 -0.0971 0.8452 1.0000
0.500 0.4785 0.01414 0.00652 -0.0981 0.8384 1.0000
0.750 0.5065 0.01414 0.00642 -0.0981 0.8277 1.0000
1.000 0.5360 0.01407 0.00626 -0.0981 0.8168 1.0000
1.250 0.5655 0.01397 0.00608 -0.0981 0.8050 1.0000
1.500 0.5947 0.01389 0.00594 -0.0980 0.7926 1.0000
1.750 0.6234 0.01384 0.00582 -0.0979 0.7802 1.0000
2.000 0.6523 0.01381 0.00575 -0.0978 0.7690 1.0000
2.250 0.6793 0.01387 0.00580 -0.0975 0.7566 1.0000
2.500 0.7065 0.01392 0.00587 -0.0972 0.7437 1.0000
2.750 0.7338 0.01397 0.00592 -0.0969 0.7300 1.0000
3.000 0.7612 0.01402 0.00597 -0.0966 0.7153 1.0000
3.250 0.7879 0.01409 0.00604 -0.0962 0.6985 1.0000
3.500 0.8140 0.01419 0.00620 -0.0957 0.6799 1.0000
3.750 0.8408 0.01427 0.00627 -0.0952 0.6597 1.0000
4.000 0.8662 0.01442 0.00642 -0.0945 0.6356 1.0000
4.250 0.8914 0.01459 0.00657 -0.0937 0.6081 1.0000
4.500 0.9161 0.01481 0.00674 -0.0929 0.5759 1.0000
4.750 0.9397 0.01511 0.00701 -0.0919 0.5383 1.0000
5.000 0.9622 0.01553 0.00728 -0.0907 0.4966 1.0000
5.250 0.9836 0.01606 0.00765 -0.0895 0.4549 1.0000
5.500 1.0043 0.01667 0.00811 -0.0883 0.4163 1.0000
5.750 1.0247 0.01732 0.00865 -0.0871 0.3831 1.0000
6.000 1.0455 0.01797 0.00929 -0.0860 0.3546 1.0000
6.250 1.0663 0.01863 0.00992 -0.0849 0.3296 1.0000
6.500 1.0871 0.01930 0.01058 -0.0839 0.3074 1.0000
6.750 1.1073 0.02001 0.01128 -0.0827 0.2878 1.0000
7.000 1.1278 0.02071 0.01203 -0.0817 0.2694 1.0000
7.250 1.1481 0.02141 0.01282 -0.0806 0.2519 1.0000
7.500 1.1656 0.02216 0.01365 -0.0792 0.2241 1.0000
7.750 1.1813 0.02297 0.01436 -0.0777 0.1818 1.0000
8.000 1.1939 0.02419 0.01521 -0.0760 0.1220 1.0000
8.250 1.2023 0.02610 0.01659 -0.0738 0.0613 1.0000
8.500 1.2099 0.02820 0.01843 -0.0713 0.0277 1.0000
8.750 1.2182 0.03009 0.02038 -0.0687 0.0196 1.0000
9.000 1.2249 0.03180 0.02229 -0.0659 0.0171 1.0000
9.250 1.2318 0.03340 0.02412 -0.0632 0.0151 1.0000
9.500 1.2374 0.03507 0.02598 -0.0607 0.0132 1.0000
9.750 1.2393 0.03705 0.02813 -0.0581 0.0119 1.0000
10.000 1.2358 0.03954 0.03081 -0.0552 0.0111 1.0000
10.250 1.2380 0.04165 0.03311 -0.0530 0.0107 1.0000
10.500 1.2392 0.04398 0.03566 -0.0510 0.0104 1.0000
10.750 1.2400 0.04653 0.03842 -0.0491 0.0102 1.0000
11.000 1.2410 0.04923 0.04141 -0.0475 0.0099 1.0000
11.250 1.2420 0.05211 0.04453 -0.0461 0.0097 1.0000
11.500 1.2423 0.05522 0.04787 -0.0449 0.0096 1.0000
11.750 1.2414 0.05860 0.05150 -0.0440 0.0094 1.0000
12.000 1.2387 0.06225 0.05540 -0.0433 0.0093 1.0000
12.250 1.2338 0.06626 0.05968 -0.0430 0.0092 1.0000
12.500 1.2266 0.07066 0.06435 -0.0432 0.0092 1.0000
12.750 1.2170 0.07552 0.06947 -0.0439 0.0092 1.0000
13.000 1.2055 0.08085 0.07506 -0.0453 0.0091 1.0000
13.250 1.1923 0.08670 0.08115 -0.0474 0.0092 1.0000
13.500 1.1778 0.09314 0.08783 -0.0503 0.0092 1.0000
13.750 1.1626 0.10018 0.09510 -0.0540 0.0092 1.0000
14.000 1.1469 0.10788 0.10300 -0.0585 0.0093 1.0000
14.250 1.1310 0.11624 0.11155 -0.0637 0.0094 1.0000
14.500 1.1150 0.12525 0.12072 -0.0695 0.0095 1.0000
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