HQ-2.0/9 9.0% smoothed (hq2090sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ-2.0/9 9.0% smoothed (hq2090sm-il) Reynolds number: 100,000 Max Cl/Cd: 55.11 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2090sm-il-100000.txt Download as CSV file: xf-hq2090sm-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4806 0.11981 0.11470 -0.0174 1.0000 0.0777
-10.250 -0.4929 0.11739 0.11237 -0.0228 1.0000 0.0787
-10.000 -0.5020 0.11438 0.10945 -0.0273 1.0000 0.0790
-9.750 -0.4660 0.10790 0.10285 -0.0199 1.0000 0.0832
-9.500 -0.4612 0.10460 0.09958 -0.0207 1.0000 0.0869
-9.250 -0.4642 0.10126 0.09631 -0.0235 1.0000 0.0903
-9.000 -0.4803 0.09815 0.09332 -0.0296 1.0000 0.0921
-8.750 -0.4673 0.09341 0.08860 -0.0273 1.0000 0.0953
-8.500 -0.4581 0.09052 0.08572 -0.0265 1.0000 0.1011
-8.250 -0.4662 0.08703 0.08233 -0.0297 1.0000 0.1042
-8.000 -0.4884 0.08287 0.07830 -0.0368 1.0000 0.1057
-7.750 -0.4762 0.07950 0.07497 -0.0325 1.0000 0.1102
-7.500 -0.4767 0.07603 0.07155 -0.0344 1.0000 0.1167
-7.250 -0.4960 0.07156 0.06699 -0.0419 1.0000 0.1197
-7.000 -0.4843 0.06799 0.06356 -0.0384 1.0000 0.1249
-6.750 -0.4995 0.06521 0.06049 -0.0429 1.0000 0.1342
-6.500 -0.4873 0.06097 0.05649 -0.0396 1.0000 0.1383
-6.250 -0.4924 0.05791 0.05322 -0.0408 1.0000 0.1499
-6.000 -0.4817 0.05507 0.05053 -0.0377 1.0000 0.1555
-5.750 -0.4790 0.05209 0.04748 -0.0370 1.0000 0.1676
-5.250 -0.4388 0.03595 0.02883 -0.0399 1.0000 0.0659
-5.000 -0.4216 0.03211 0.02484 -0.0390 1.0000 0.0631
-4.750 -0.4018 0.02934 0.02161 -0.0380 1.0000 0.0632
-4.500 -0.3804 0.02759 0.01925 -0.0367 1.0000 0.0657
-4.250 -0.3581 0.02459 0.01598 -0.0360 1.0000 0.0675
-4.000 -0.3357 0.02288 0.01411 -0.0351 1.0000 0.0723
-3.750 -0.3123 0.02148 0.01244 -0.0342 1.0000 0.0809
-3.500 -0.2893 0.02027 0.01117 -0.0333 1.0000 0.0899
-3.250 -0.2667 0.01917 0.01008 -0.0325 1.0000 0.1031
-3.000 -0.2445 0.01821 0.00914 -0.0316 1.0000 0.1196
-2.750 -0.2229 0.01719 0.00831 -0.0308 1.0000 0.1438
-2.500 -0.2003 0.01577 0.00748 -0.0305 1.0000 0.2274
-2.250 -0.1921 0.01416 0.00797 -0.0260 1.0000 0.7029
-2.000 -0.1819 0.01424 0.00817 -0.0217 1.0000 0.7797
-1.750 -0.1718 0.01426 0.00823 -0.0175 1.0000 0.8360
-1.500 -0.1595 0.01419 0.00822 -0.0139 1.0000 0.8953
-1.250 -0.1100 0.01412 0.00803 -0.0185 0.9979 1.0000
-1.000 -0.0644 0.01449 0.00812 -0.0234 0.9904 1.0000
-0.750 -0.0172 0.01494 0.00833 -0.0284 0.9832 1.0000
-0.500 0.0243 0.01525 0.00843 -0.0322 0.9742 1.0000
-0.250 0.0684 0.01563 0.00865 -0.0362 0.9662 1.0000
0.000 0.1117 0.01597 0.00885 -0.0400 0.9576 1.0000
0.250 0.1497 0.01626 0.00904 -0.0427 0.9481 1.0000
0.500 0.1949 0.01658 0.00927 -0.0466 0.9402 1.0000
0.750 0.2338 0.01681 0.00945 -0.0492 0.9301 1.0000
1.000 0.2716 0.01702 0.00963 -0.0515 0.9195 1.0000
1.250 0.3162 0.01711 0.00971 -0.0548 0.9088 1.0000
1.500 0.3744 0.01691 0.00956 -0.0601 0.8992 1.0000
1.750 0.4159 0.01678 0.00947 -0.0623 0.8867 1.0000
2.000 0.4528 0.01671 0.00945 -0.0636 0.8743 1.0000
2.500 0.5246 0.01639 0.00928 -0.0653 0.8485 1.0000
2.750 0.5584 0.01614 0.00910 -0.0654 0.8342 1.0000
3.000 0.5902 0.01586 0.00890 -0.0650 0.8188 1.0000
3.250 0.6206 0.01558 0.00872 -0.0643 0.8027 1.0000
3.500 0.6485 0.01536 0.00857 -0.0631 0.7845 1.0000
3.750 0.6743 0.01518 0.00847 -0.0616 0.7632 1.0000
4.000 0.7007 0.01495 0.00831 -0.0601 0.7405 1.0000
4.250 0.7264 0.01474 0.00818 -0.0585 0.7139 1.0000
4.500 0.7502 0.01457 0.00805 -0.0566 0.6796 1.0000
4.750 0.7733 0.01442 0.00787 -0.0545 0.6354 1.0000
5.000 0.7951 0.01446 0.00779 -0.0524 0.5794 1.0000
5.250 0.8157 0.01480 0.00792 -0.0503 0.5148 1.0000
5.500 0.8346 0.01546 0.00824 -0.0483 0.4463 1.0000
5.750 0.8529 0.01631 0.00878 -0.0465 0.3811 1.0000
6.000 0.8704 0.01727 0.00945 -0.0449 0.3182 1.0000
6.250 0.8862 0.01850 0.01030 -0.0431 0.2534 1.0000
6.500 0.9006 0.02005 0.01146 -0.0412 0.1857 1.0000
6.750 0.9166 0.02176 0.01283 -0.0394 0.1437 1.0000
7.000 0.9350 0.02332 0.01423 -0.0380 0.1172 1.0000
7.250 0.9549 0.02504 0.01588 -0.0368 0.0984 1.0000
7.500 0.9750 0.02672 0.01757 -0.0357 0.0817 1.0000
7.750 0.9968 0.02891 0.01980 -0.0347 0.0695 1.0000
8.000 1.0181 0.03131 0.02227 -0.0338 0.0595 1.0000
8.250 1.0407 0.03383 0.02501 -0.0329 0.0540 1.0000
8.500 1.0617 0.03801 0.02942 -0.0321 0.0507 1.0000
8.750 1.0759 0.04044 0.03246 -0.0300 0.0477 1.0000
9.000 1.0882 0.04345 0.03592 -0.0281 0.0451 1.0000
9.250 1.0956 0.04737 0.04034 -0.0260 0.0447 1.0000
9.500 1.0967 0.05175 0.04525 -0.0235 0.0451 1.0000
9.750 1.0914 0.05637 0.05035 -0.0210 0.0458 1.0000
10.000 1.0809 0.06098 0.05535 -0.0186 0.0467 1.0000
10.250 1.0662 0.06531 0.05996 -0.0162 0.0475 1.0000
10.500 1.0477 0.06934 0.06420 -0.0141 0.0482 1.0000
10.750 1.0281 0.07368 0.06871 -0.0132 0.0488 1.0000
11.000 1.0081 0.07860 0.07377 -0.0137 0.0494 1.0000
11.250 0.9900 0.08410 0.07936 -0.0152 0.0501 1.0000
11.500 0.8676 0.08621 0.08191 -0.0149 0.0500 1.0000
11.750 0.8465 0.09367 0.08944 -0.0183 0.0507 1.0000
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Polar data table (+)
Polar graphs
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