HQ-2.0/9 9.0% smoothed (hq2090sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ-2.0/9 9.0% smoothed (hq2090sm-il) Reynolds number: 500,000 Max Cl/Cd: 79.34 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2090sm-il-500000-n5.txt Download as CSV file: xf-hq2090sm-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ-2.0/9 9.0% smoothed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4925 0.08491 0.08267 -0.0278 1.0000 0.0050
-9.250 -0.4997 0.07923 0.07703 -0.0309 1.0000 0.0047
-9.000 -0.5082 0.07352 0.07137 -0.0343 1.0000 0.0049
-8.750 -0.5254 0.06643 0.06434 -0.0394 1.0000 0.0047
-8.500 -0.5506 0.05701 0.05488 -0.0483 1.0000 0.0045
-8.250 -0.5678 0.04930 0.04700 -0.0509 1.0000 0.0045
-8.000 -0.5943 0.02551 0.02173 -0.0581 0.9879 0.0045
-7.750 -0.5677 0.02266 0.01847 -0.0597 0.9832 0.0048
-7.500 -0.5386 0.02097 0.01651 -0.0610 0.9788 0.0052
-7.250 -0.5106 0.01869 0.01383 -0.0621 0.9739 0.0055
-7.000 -0.4816 0.01708 0.01193 -0.0629 0.9686 0.0058
-6.750 -0.4525 0.01563 0.01022 -0.0637 0.9635 0.0059
-6.500 -0.4243 0.01451 0.00890 -0.0640 0.9569 0.0061
-6.250 -0.3956 0.01367 0.00788 -0.0645 0.9508 0.0064
-6.000 -0.3699 0.01244 0.00647 -0.0643 0.9425 0.0071
-5.750 -0.3428 0.01185 0.00579 -0.0643 0.9350 0.0078
-5.500 -0.3159 0.01138 0.00524 -0.0642 0.9267 0.0088
-5.250 -0.2895 0.01096 0.00473 -0.0639 0.9179 0.0100
-5.000 -0.2630 0.01054 0.00427 -0.0637 0.9096 0.0124
-4.750 -0.2364 0.01023 0.00388 -0.0634 0.9004 0.0159
-4.500 -0.2098 0.00990 0.00354 -0.0632 0.8917 0.0207
-4.000 -0.1560 0.00944 0.00299 -0.0628 0.8746 0.0311
-3.750 -0.1288 0.00929 0.00279 -0.0627 0.8665 0.0362
-3.500 -0.1018 0.00904 0.00252 -0.0625 0.8583 0.0457
-3.250 -0.0746 0.00885 0.00229 -0.0624 0.8504 0.0542
-3.000 -0.0474 0.00866 0.00209 -0.0622 0.8425 0.0683
-2.750 -0.0202 0.00846 0.00193 -0.0621 0.8344 0.0910
-2.500 0.0068 0.00820 0.00176 -0.0620 0.8263 0.1310
-2.250 0.0335 0.00787 0.00160 -0.0620 0.8164 0.1936
-2.000 0.0598 0.00743 0.00143 -0.0620 0.8065 0.2913
-1.750 0.0853 0.00685 0.00132 -0.0619 0.7977 0.4473
-1.500 0.1119 0.00657 0.00128 -0.0617 0.7893 0.5332
-1.250 0.1391 0.00647 0.00125 -0.0615 0.7818 0.5740
-1.000 0.1662 0.00639 0.00126 -0.0613 0.7734 0.6178
-0.750 0.1933 0.00634 0.00127 -0.0610 0.7635 0.6564
-0.500 0.2199 0.00632 0.00129 -0.0606 0.7516 0.6910
-0.250 0.2469 0.00633 0.00129 -0.0603 0.7385 0.7131
0.000 0.2743 0.00635 0.00127 -0.0601 0.7262 0.7227
0.250 0.3018 0.00637 0.00127 -0.0600 0.7152 0.7312
0.500 0.3296 0.00640 0.00128 -0.0599 0.7041 0.7402
0.750 0.3569 0.00642 0.00129 -0.0597 0.6915 0.7486
1.000 0.3841 0.00647 0.00131 -0.0595 0.6751 0.7573
1.500 0.4381 0.00659 0.00137 -0.0590 0.6394 0.7754
1.750 0.4649 0.00667 0.00141 -0.0587 0.6189 0.7853
2.000 0.4913 0.00676 0.00148 -0.0584 0.5948 0.7960
2.250 0.5172 0.00689 0.00155 -0.0580 0.5667 0.8077
2.500 0.5427 0.00704 0.00165 -0.0575 0.5349 0.8210
2.750 0.5675 0.00724 0.00177 -0.0569 0.4976 0.8372
3.000 0.5916 0.00746 0.00192 -0.0561 0.4602 0.8577
3.250 0.6141 0.00774 0.00210 -0.0550 0.4113 0.8885
3.500 0.6402 0.00810 0.00229 -0.0548 0.3499 0.9435
3.750 0.6720 0.00847 0.00250 -0.0560 0.3065 1.0000
4.000 0.6967 0.00891 0.00276 -0.0557 0.2643 1.0000
4.250 0.7218 0.00931 0.00300 -0.0554 0.2299 1.0000
4.500 0.7473 0.00964 0.00324 -0.0551 0.2050 1.0000
4.750 0.7725 0.01001 0.00350 -0.0548 0.1770 1.0000
5.000 0.7974 0.01042 0.00379 -0.0545 0.1489 1.0000
5.250 0.8221 0.01084 0.00413 -0.0541 0.1232 1.0000
5.500 0.8465 0.01129 0.00447 -0.0537 0.0976 1.0000
6.000 0.8946 0.01228 0.00527 -0.0528 0.0565 1.0000
6.250 0.9190 0.01271 0.00568 -0.0524 0.0459 1.0000
6.500 0.9433 0.01316 0.00609 -0.0519 0.0368 1.0000
6.750 0.9678 0.01356 0.00652 -0.0515 0.0306 1.0000
7.000 0.9917 0.01403 0.00698 -0.0510 0.0246 1.0000
7.250 1.0157 0.01446 0.00744 -0.0505 0.0194 1.0000
7.500 1.0385 0.01505 0.00800 -0.0499 0.0126 1.0000
7.750 1.0608 0.01568 0.00863 -0.0492 0.0091 1.0000
8.000 1.0826 0.01639 0.00938 -0.0483 0.0071 1.0000
8.250 1.1043 0.01708 0.01019 -0.0475 0.0063 1.0000
8.500 1.1258 0.01774 0.01096 -0.0466 0.0058 1.0000
8.750 1.1466 0.01848 0.01180 -0.0457 0.0054 1.0000
9.000 1.1665 0.01928 0.01271 -0.0446 0.0051 1.0000
9.250 1.1856 0.02013 0.01367 -0.0435 0.0047 1.0000
9.500 1.2031 0.02112 0.01477 -0.0422 0.0044 1.0000
9.750 1.2188 0.02226 0.01603 -0.0407 0.0041 1.0000
10.000 1.2284 0.02397 0.01792 -0.0384 0.0038 1.0000
10.250 1.2422 0.02514 0.01922 -0.0367 0.0037 1.0000
10.500 1.2576 0.02604 0.02027 -0.0352 0.0035 1.0000
10.750 1.2695 0.02704 0.02140 -0.0333 0.0033 1.0000
11.000 1.2755 0.02842 0.02294 -0.0306 0.0032 1.0000
11.250 1.2816 0.02979 0.02446 -0.0281 0.0031 1.0000
11.500 1.2865 0.03127 0.02609 -0.0258 0.0030 1.0000
11.750 1.2887 0.03303 0.02802 -0.0235 0.0029 1.0000
12.000 1.2901 0.03492 0.03008 -0.0216 0.0028 1.0000
12.250 1.2894 0.03712 0.03245 -0.0198 0.0027 1.0000
12.500 1.2869 0.03962 0.03513 -0.0184 0.0027 1.0000
12.750 1.2832 0.04239 0.03807 -0.0174 0.0027 1.0000
13.000 1.2809 0.04513 0.04096 -0.0169 0.0025 1.0000
13.250 1.2670 0.04957 0.04564 -0.0169 0.0026 1.0000
13.500 1.2644 0.05279 0.04898 -0.0175 0.0025 1.0000
13.750 1.2552 0.05721 0.05357 -0.0188 0.0025 1.0000
14.000 1.2384 0.06324 0.05982 -0.0211 0.0025 1.0000
14.250 1.2246 0.06937 0.06611 -0.0242 0.0025 1.0000
14.500 1.2075 0.07672 0.07365 -0.0284 0.0025 1.0000
14.750 1.1862 0.08561 0.08273 -0.0337 0.0025 1.0000
15.000 1.1601 0.09632 0.09365 -0.0401 0.0026 1.0000
15.250 1.1355 0.10722 0.10471 -0.0466 0.0026 1.0000
15.500 1.1098 0.11882 0.11646 -0.0533 0.0027 1.0000
15.750 1.0797 0.13195 0.12973 -0.0607 0.0028 1.0000
16.000 1.0447 0.14737 0.14528 -0.0692 0.0029 1.0000
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Polar data table (+)
Polar graphs
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