HQ 0/10 AIRFOIL (hq010-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 0/10 AIRFOIL (hq010-il) Reynolds number: 200,000 Max Cl/Cd: 50.06 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq010-il-200000.txt Download as CSV file: xf-hq010-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 0/10 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.7335 0.08061 0.07725 -0.0133 1.0000 0.0277
-10.750 -0.8143 0.06107 0.05725 -0.0259 1.0000 0.0199
-10.500 -0.8353 0.05648 0.05249 -0.0271 1.0000 0.0198
-10.250 -0.8563 0.05250 0.04832 -0.0262 1.0000 0.0196
-10.000 -0.8705 0.04973 0.04528 -0.0237 1.0000 0.0204
-9.750 -0.8767 0.04702 0.04223 -0.0217 1.0000 0.0210
-9.250 -0.8882 0.03848 0.03304 -0.0180 1.0000 0.0234
-9.000 -0.8742 0.03721 0.03169 -0.0170 1.0000 0.0259
-8.750 -0.8648 0.03415 0.02817 -0.0151 1.0000 0.0286
-8.500 -0.8502 0.03257 0.02610 -0.0133 1.0000 0.0312
-8.250 -0.8368 0.02961 0.02305 -0.0126 1.0000 0.0354
-8.000 -0.8160 0.02926 0.02255 -0.0118 1.0000 0.0403
-7.750 -0.7954 0.02766 0.02059 -0.0106 1.0000 0.0418
-7.500 -0.7754 0.02478 0.01735 -0.0097 1.0000 0.0438
-7.250 -0.7531 0.02300 0.01552 -0.0091 1.0000 0.0463
-7.000 -0.7296 0.02158 0.01398 -0.0083 1.0000 0.0481
-6.750 -0.7061 0.02032 0.01260 -0.0075 1.0000 0.0504
-6.500 -0.6827 0.01923 0.01140 -0.0066 1.0000 0.0531
-6.250 -0.6610 0.01789 0.01002 -0.0056 1.0000 0.0562
-6.000 -0.6401 0.01692 0.00910 -0.0046 1.0000 0.0621
-5.750 -0.6191 0.01604 0.00815 -0.0034 1.0000 0.0694
-5.500 -0.5989 0.01519 0.00733 -0.0022 1.0000 0.0797
-5.250 -0.5810 0.01416 0.00641 -0.0007 1.0000 0.0971
-5.000 -0.5646 0.01312 0.00563 0.0010 1.0000 0.1333
-4.750 -0.5500 0.01210 0.00514 0.0027 1.0000 0.2254
-4.500 -0.5354 0.01137 0.00475 0.0046 1.0000 0.2938
-4.250 -0.5232 0.01069 0.00450 0.0069 1.0000 0.3776
-4.000 -0.5107 0.01020 0.00434 0.0092 1.0000 0.4626
-3.750 -0.4950 0.00990 0.00437 0.0111 0.9993 0.5404
-3.500 -0.4564 0.00980 0.00447 0.0088 0.9917 0.6127
-3.250 -0.4175 0.00983 0.00453 0.0066 0.9841 0.6572
-3.000 -0.3793 0.00988 0.00457 0.0046 0.9769 0.6905
-2.750 -0.3402 0.00995 0.00464 0.0025 0.9703 0.7186
-2.500 -0.3016 0.01004 0.00474 0.0007 0.9636 0.7450
-2.250 -0.2617 0.01007 0.00477 -0.0014 0.9563 0.7624
-2.000 -0.2249 0.01004 0.00469 -0.0030 0.9471 0.7751
-1.750 -0.1876 0.01003 0.00464 -0.0047 0.9399 0.7875
-1.500 -0.1579 0.01003 0.00464 -0.0047 0.9296 0.7992
-1.250 -0.1287 0.01004 0.00463 -0.0046 0.9198 0.8107
-1.000 -0.1000 0.01003 0.00461 -0.0043 0.9106 0.8218
-0.750 -0.0740 0.01003 0.00461 -0.0035 0.9001 0.8336
-0.500 -0.0495 0.01004 0.00462 -0.0022 0.8889 0.8462
-0.250 -0.0250 0.01003 0.00461 -0.0011 0.8781 0.8579
0.000 0.0000 0.01003 0.00459 0.0000 0.8681 0.8682
0.250 0.0250 0.01003 0.00461 0.0011 0.8579 0.8781
0.500 0.0495 0.01004 0.00462 0.0023 0.8461 0.8889
0.750 0.0740 0.01003 0.00461 0.0035 0.8337 0.9001
1.000 0.1000 0.01003 0.00461 0.0043 0.8218 0.9105
1.250 0.1287 0.01004 0.00463 0.0046 0.8107 0.9199
1.500 0.1580 0.01003 0.00464 0.0047 0.7993 0.9296
1.750 0.1876 0.01003 0.00464 0.0046 0.7875 0.9399
2.000 0.2250 0.01004 0.00470 0.0030 0.7751 0.9471
2.250 0.2618 0.01007 0.00477 0.0014 0.7625 0.9563
2.500 0.3016 0.01004 0.00474 -0.0006 0.7448 0.9636
2.750 0.3401 0.00995 0.00464 -0.0025 0.7185 0.9703
3.000 0.3793 0.00988 0.00457 -0.0046 0.6906 0.9769
3.250 0.4175 0.00983 0.00453 -0.0066 0.6573 0.9841
3.500 0.4564 0.00980 0.00446 -0.0088 0.6128 0.9917
3.750 0.4950 0.00990 0.00437 -0.0111 0.5405 0.9994
4.000 0.5106 0.01020 0.00434 -0.0092 0.4625 1.0000
4.250 0.5231 0.01070 0.00450 -0.0069 0.3766 1.0000
4.500 0.5354 0.01137 0.00475 -0.0046 0.2938 1.0000
4.750 0.5500 0.01210 0.00514 -0.0027 0.2253 1.0000
5.000 0.5646 0.01312 0.00563 -0.0010 0.1336 1.0000
5.250 0.5810 0.01417 0.00641 0.0007 0.0970 1.0000
5.500 0.5989 0.01519 0.00733 0.0022 0.0798 1.0000
5.750 0.6191 0.01605 0.00816 0.0035 0.0693 1.0000
6.000 0.6402 0.01690 0.00908 0.0046 0.0617 1.0000
6.250 0.6610 0.01790 0.01003 0.0056 0.0562 1.0000
6.500 0.6827 0.01922 0.01139 0.0067 0.0530 1.0000
6.750 0.7061 0.02032 0.01260 0.0075 0.0504 1.0000
7.000 0.7296 0.02158 0.01398 0.0083 0.0481 1.0000
7.250 0.7530 0.02300 0.01552 0.0091 0.0463 1.0000
7.500 0.7753 0.02482 0.01738 0.0097 0.0437 1.0000
7.750 0.7954 0.02768 0.02060 0.0106 0.0419 1.0000
8.000 0.8159 0.02935 0.02264 0.0118 0.0404 1.0000
8.250 0.8365 0.02978 0.02324 0.0126 0.0356 1.0000
8.500 0.8496 0.03275 0.02629 0.0133 0.0311 1.0000
8.750 0.8649 0.03411 0.02814 0.0151 0.0285 1.0000
9.000 0.8742 0.03718 0.03166 0.0170 0.0258 1.0000
9.250 0.8905 0.03780 0.03225 0.0177 0.0230 1.0000
9.500 0.8915 0.04185 0.03658 0.0193 0.0219 1.0000
10.000 0.8691 0.05003 0.04558 0.0237 0.0206 1.0000
10.250 0.8553 0.05275 0.04856 0.0262 0.0199 1.0000
10.500 0.8356 0.05653 0.05253 0.0270 0.0200 1.0000
10.750 0.8137 0.06140 0.05754 0.0259 0.0205 1.0000
11.000 0.7882 0.06795 0.06419 0.0230 0.0211 1.0000
11.250 0.7125 0.09159 0.08823 0.0055 0.0292 1.0000
11.500 0.6975 0.10038 0.09697 0.0008 0.0302 1.0000
11.750 0.6585 0.12133 0.11780 -0.0103 0.0514 1.0000
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