HQ 3.5/9 AIRFOIL (hq359-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/9 AIRFOIL (hq359-il) Reynolds number: 200,000 Max Cl/Cd: 82.16 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq359-il-200000-n5.txt Download as CSV file: xf-hq359-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3366 0.10008 0.09668 -0.0395 1.0000 0.0191
-8.500 -0.3401 0.09762 0.09429 -0.0389 1.0000 0.0191
-8.250 -0.3469 0.09551 0.09224 -0.0376 1.0000 0.0192
-8.000 -0.3460 0.09252 0.08930 -0.0388 0.9980 0.0192
-7.750 -0.3423 0.08620 0.08303 -0.0407 0.9943 0.0204
-7.500 -0.3279 0.08276 0.07959 -0.0432 0.9895 0.0213
-7.250 -0.3138 0.07842 0.07526 -0.0483 0.9831 0.0218
-7.000 -0.2953 0.07359 0.07044 -0.0552 0.9762 0.0223
-6.750 -0.2749 0.06806 0.06489 -0.0640 0.9696 0.0225
-6.250 -0.2220 0.05406 0.05063 -0.0850 0.9566 0.0171
-6.000 -0.1991 0.04821 0.04459 -0.0912 0.9500 0.0150
-5.500 -0.1419 0.03542 0.03100 -0.0998 0.9377 0.0115
-5.250 -0.1130 0.03063 0.02578 -0.1029 0.9337 0.0113
-5.000 -0.0883 0.02675 0.02144 -0.1038 0.9271 0.0112
-4.750 -0.0587 0.02331 0.01746 -0.1049 0.9226 0.0113
-4.500 -0.0273 0.02029 0.01383 -0.1060 0.9194 0.0121
-4.250 -0.0025 0.01922 0.01260 -0.1060 0.9128 0.0141
-4.000 0.0275 0.01759 0.01066 -0.1063 0.9086 0.0148
-3.750 0.0574 0.01609 0.00889 -0.1065 0.9047 0.0151
-3.500 0.0836 0.01501 0.00766 -0.1061 0.8984 0.0157
-3.250 0.1127 0.01407 0.00659 -0.1062 0.8940 0.0166
-3.000 0.1404 0.01337 0.00577 -0.1061 0.8885 0.0180
-2.750 0.1682 0.01276 0.00503 -0.1061 0.8828 0.0209
-2.500 0.1980 0.01232 0.00456 -0.1064 0.8785 0.0328
-2.250 0.2245 0.01199 0.00424 -0.1062 0.8716 0.0562
-2.000 0.2533 0.01166 0.00394 -0.1064 0.8664 0.0856
-1.750 0.2800 0.01096 0.00371 -0.1067 0.8602 0.2243
-1.500 0.3046 0.00998 0.00369 -0.1066 0.8539 0.5317
-1.250 0.3300 0.00980 0.00373 -0.1057 0.8472 0.6335
-1.000 0.3548 0.00969 0.00374 -0.1047 0.8397 0.7015
-0.750 0.3794 0.00962 0.00372 -0.1036 0.8311 0.7441
-0.500 0.4047 0.00952 0.00360 -0.1025 0.8221 0.7773
-0.250 0.4310 0.00944 0.00346 -0.1019 0.8111 0.7939
0.000 0.4570 0.00937 0.00335 -0.1013 0.7996 0.8069
0.250 0.4832 0.00932 0.00325 -0.1008 0.7891 0.8212
0.500 0.5093 0.00925 0.00316 -0.1002 0.7786 0.8377
0.750 0.5356 0.00917 0.00306 -0.0996 0.7677 0.8579
1.000 0.5621 0.00908 0.00297 -0.0990 0.7553 0.8879
1.250 0.5972 0.00896 0.00288 -0.1004 0.7426 1.0000
1.500 0.6250 0.00904 0.00289 -0.1004 0.7305 1.0000
1.750 0.6526 0.00913 0.00291 -0.1003 0.7177 1.0000
2.000 0.6799 0.00923 0.00294 -0.1002 0.7040 1.0000
2.250 0.7071 0.00934 0.00301 -0.1001 0.6895 1.0000
2.750 0.7603 0.00960 0.00315 -0.0995 0.6545 1.0000
3.000 0.7863 0.00977 0.00324 -0.0991 0.6338 1.0000
3.250 0.8120 0.00996 0.00336 -0.0987 0.6098 1.0000
3.500 0.8369 0.01019 0.00353 -0.0981 0.5814 1.0000
3.750 0.8610 0.01048 0.00369 -0.0973 0.5485 1.0000
4.000 0.8841 0.01084 0.00389 -0.0965 0.5098 1.0000
4.250 0.9062 0.01128 0.00415 -0.0955 0.4686 1.0000
4.500 0.9278 0.01179 0.00450 -0.0944 0.4274 1.0000
4.750 0.9494 0.01231 0.00487 -0.0934 0.3896 1.0000
5.000 0.9711 0.01282 0.00526 -0.0925 0.3565 1.0000
5.250 0.9931 0.01333 0.00567 -0.0917 0.3275 1.0000
5.500 1.0153 0.01384 0.00610 -0.0908 0.3034 1.0000
5.750 1.0374 0.01435 0.00659 -0.0900 0.2835 1.0000
6.000 1.0595 0.01485 0.00707 -0.0892 0.2652 1.0000
6.250 1.0806 0.01542 0.00757 -0.0883 0.2416 1.0000
6.500 1.1017 0.01599 0.00807 -0.0874 0.2157 1.0000
6.750 1.1227 0.01656 0.00855 -0.0865 0.1846 1.0000
7.000 1.1433 0.01717 0.00909 -0.0855 0.1560 1.0000
7.250 1.1598 0.01819 0.00982 -0.0841 0.1081 1.0000
7.500 1.1711 0.01979 0.01100 -0.0821 0.0481 1.0000
7.750 1.1833 0.02130 0.01227 -0.0800 0.0148 1.0000
8.000 1.1996 0.02234 0.01337 -0.0783 0.0088 1.0000
8.250 1.2159 0.02333 0.01448 -0.0767 0.0073 1.0000
8.500 1.2302 0.02447 0.01579 -0.0747 0.0065 1.0000
8.750 1.2427 0.02558 0.01708 -0.0725 0.0061 1.0000
9.000 1.2535 0.02675 0.01843 -0.0701 0.0059 1.0000
9.250 1.2621 0.02805 0.01991 -0.0675 0.0057 1.0000
9.500 1.2688 0.02950 0.02153 -0.0648 0.0055 1.0000
9.750 1.2742 0.03107 0.02327 -0.0622 0.0054 1.0000
10.000 1.2784 0.03281 0.02518 -0.0596 0.0053 1.0000
10.250 1.2819 0.03471 0.02723 -0.0572 0.0053 1.0000
10.500 1.2853 0.03673 0.02948 -0.0550 0.0052 1.0000
10.750 1.2877 0.03898 0.03191 -0.0529 0.0051 1.0000
11.000 1.2903 0.04134 0.03445 -0.0510 0.0051 1.0000
11.250 1.2923 0.04390 0.03719 -0.0493 0.0050 1.0000
11.500 1.2935 0.04665 0.04015 -0.0477 0.0050 1.0000
11.750 1.2937 0.04952 0.04322 -0.0464 0.0048 1.0000
12.000 1.2923 0.05261 0.04653 -0.0454 0.0048 1.0000
12.250 1.2898 0.05574 0.04986 -0.0447 0.0046 1.0000
12.500 1.2854 0.05921 0.05352 -0.0444 0.0044 1.0000
12.750 1.2798 0.06284 0.05730 -0.0446 0.0042 1.0000
13.000 1.2719 0.06714 0.06181 -0.0451 0.0041 1.0000
13.250 1.2619 0.07193 0.06678 -0.0462 0.0040 1.0000
13.500 1.2507 0.07726 0.07232 -0.0478 0.0039 1.0000
13.750 1.2383 0.08309 0.07837 -0.0500 0.0039 1.0000
14.000 1.2244 0.08958 0.08506 -0.0529 0.0038 1.0000
14.250 1.2110 0.09643 0.09212 -0.0564 0.0038 1.0000
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