HQ 1.5/8 AIRFOIL (hq158-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.5/8 AIRFOIL (hq158-il) Reynolds number: 50,000 Max Cl/Cd: 35.69 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq158-il-50000.txt Download as CSV file: xf-hq158-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/8 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4916 0.10251 0.09584 -0.0029 1.0000 0.2509
-8.250 -0.4935 0.09989 0.09330 -0.0030 1.0000 0.2684
-8.000 -0.5005 0.09767 0.09119 -0.0034 1.0000 0.2838
-7.500 -0.4716 0.08989 0.08339 0.0003 1.0000 0.3308
-7.250 -0.4843 0.08844 0.08207 0.0010 1.0000 0.3523
-7.000 -0.4620 0.08405 0.07767 0.0030 1.0000 0.3768
-6.750 -0.4513 0.08062 0.07428 0.0046 1.0000 0.4008
-6.500 -0.4441 0.07754 0.07127 0.0064 1.0000 0.4266
-5.250 -0.4480 0.04325 0.03540 -0.0389 1.0000 0.1248
-5.000 -0.4274 0.03923 0.03082 -0.0385 1.0000 0.1140
-4.750 -0.4045 0.03586 0.02641 -0.0377 1.0000 0.1063
-4.500 -0.3826 0.03273 0.02290 -0.0366 1.0000 0.1052
-4.250 -0.3590 0.03017 0.01978 -0.0352 1.0000 0.1066
-4.000 -0.3374 0.02787 0.01741 -0.0341 1.0000 0.1178
-3.750 -0.3137 0.02563 0.01501 -0.0328 1.0000 0.1278
-3.500 -0.2896 0.02370 0.01290 -0.0311 1.0000 0.1470
-3.250 -0.2669 0.02173 0.01117 -0.0295 1.0000 0.1840
-3.000 -0.2461 0.01940 0.00945 -0.0280 1.0000 0.2726
-2.750 -0.0982 0.01738 0.00897 -0.0350 1.0000 1.0000
-2.500 -0.0987 0.01698 0.00847 -0.0320 1.0000 1.0000
-2.250 -0.1036 0.01663 0.00804 -0.0282 1.0000 1.0000
-2.000 -0.1104 0.01633 0.00765 -0.0239 1.0000 1.0000
-1.750 -0.1114 0.01613 0.00727 -0.0205 1.0000 1.0000
-1.500 -0.1014 0.01606 0.00694 -0.0186 1.0000 1.0000
-1.250 -0.0856 0.01607 0.00664 -0.0176 1.0000 1.0000
-1.000 -0.0673 0.01616 0.00648 -0.0169 1.0000 1.0000
-0.750 -0.0478 0.01629 0.00639 -0.0164 1.0000 1.0000
-0.500 -0.0278 0.01646 0.00636 -0.0159 1.0000 1.0000
-0.250 -0.0075 0.01668 0.00639 -0.0155 1.0000 1.0000
0.000 0.0129 0.01692 0.00645 -0.0151 1.0000 1.0000
0.250 0.0332 0.01720 0.00660 -0.0147 1.0000 1.0000
0.500 0.0536 0.01752 0.00680 -0.0143 1.0000 1.0000
0.750 0.0737 0.01787 0.00706 -0.0140 1.0000 1.0000
1.000 0.0938 0.01826 0.00738 -0.0137 1.0000 1.0000
1.250 0.1136 0.01869 0.00776 -0.0135 1.0000 1.0000
1.500 0.1333 0.01916 0.00819 -0.0132 1.0000 1.0000
1.750 0.1526 0.01967 0.00869 -0.0131 1.0000 1.0000
2.000 0.1716 0.02024 0.00926 -0.0129 1.0000 1.0000
2.250 0.1902 0.02086 0.00990 -0.0128 1.0000 1.0000
2.500 0.2083 0.02155 0.01062 -0.0128 1.0000 1.0000
2.750 0.2264 0.02231 0.01147 -0.0129 0.9998 1.0000
3.000 0.2986 0.02392 0.01329 -0.0231 0.9717 1.0000
3.250 0.3693 0.02511 0.01477 -0.0321 0.9422 1.0000
3.500 0.4323 0.02585 0.01591 -0.0390 0.9120 1.0000
3.750 0.4928 0.02621 0.01665 -0.0445 0.8788 1.0000
4.000 0.5660 0.02587 0.01685 -0.0506 0.8425 1.0000
4.250 0.6266 0.02493 0.01650 -0.0528 0.8016 1.0000
4.500 0.6732 0.02358 0.01556 -0.0513 0.7538 1.0000
4.750 0.7073 0.02213 0.01434 -0.0471 0.6972 1.0000
5.000 0.7306 0.02118 0.01338 -0.0419 0.6262 1.0000
5.250 0.7485 0.02097 0.01299 -0.0370 0.5383 1.0000
5.500 0.7633 0.02176 0.01315 -0.0327 0.4376 1.0000
5.750 0.7749 0.02362 0.01422 -0.0291 0.3266 1.0000
6.000 0.7924 0.02636 0.01623 -0.0268 0.2380 1.0000
6.250 0.8125 0.02851 0.01814 -0.0252 0.1858 1.0000
6.500 0.8393 0.03122 0.02071 -0.0242 0.1568 1.0000
6.750 0.8613 0.03358 0.02318 -0.0229 0.1316 1.0000
7.000 0.8863 0.03715 0.02706 -0.0217 0.1184 1.0000
7.250 0.9057 0.04050 0.03047 -0.0206 0.1029 1.0000
7.500 0.9207 0.04463 0.03560 -0.0185 0.0984 1.0000
7.750 0.9390 0.04852 0.03948 -0.0177 0.0905 1.0000
8.000 0.9444 0.05272 0.04446 -0.0156 0.0879 1.0000
8.250 0.9480 0.05744 0.04975 -0.0140 0.0873 1.0000
8.500 0.9504 0.06257 0.05526 -0.0129 0.0884 1.0000
8.750 0.9554 0.06801 0.06089 -0.0121 0.0898 1.0000
9.000 0.9234 0.07361 0.06721 -0.0118 0.0951 1.0000
9.250 0.9046 0.07921 0.07298 -0.0123 0.0983 1.0000
9.500 0.8933 0.08434 0.07815 -0.0126 0.1010 1.0000
9.750 0.7427 0.09047 0.08460 -0.0183 0.1237 1.0000
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Polar data table (+)
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