HQ 3.0/15 AIRFOIL (hq3015-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/15 AIRFOIL (hq3015-il) Reynolds number: 50,000 Max Cl/Cd: 25.8 at α=10.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3015-il-50000.txt Download as CSV file: xf-hq3015-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/15 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3060 0.10826 0.10164 -0.0261 1.0000 0.3563
-9.000 -0.3332 0.10877 0.10230 -0.0227 1.0000 0.3677
-8.750 -0.3216 0.10573 0.09928 -0.0204 1.0000 0.3817
-8.500 -0.3203 0.10320 0.09679 -0.0181 1.0000 0.3888
-8.250 -0.3532 0.10383 0.09760 -0.0139 1.0000 0.3998
-8.000 -0.3341 0.09996 0.09368 -0.0126 1.0000 0.4064
-7.750 -0.5373 0.08501 0.07931 -0.0276 1.0000 0.2044
-7.250 -0.6501 0.06604 0.05974 -0.0361 1.0000 0.1599
-7.000 -0.6522 0.06173 0.05521 -0.0357 1.0000 0.1591
-6.750 -0.6518 0.05739 0.05050 -0.0355 1.0000 0.1589
-6.500 -0.6463 0.05325 0.04589 -0.0355 1.0000 0.1591
-6.250 -0.6365 0.04943 0.04146 -0.0356 1.0000 0.1603
-6.000 -0.6219 0.04677 0.03870 -0.0350 1.0000 0.1645
-5.750 -0.6055 0.04424 0.03586 -0.0345 1.0000 0.1675
-5.500 -0.5877 0.04195 0.03314 -0.0342 1.0000 0.1724
-5.250 -0.5682 0.03979 0.03040 -0.0339 1.0000 0.1773
-5.000 -0.5489 0.03808 0.02867 -0.0332 1.0000 0.1824
-4.750 -0.5283 0.03662 0.02687 -0.0326 1.0000 0.1893
-4.500 -0.5084 0.03535 0.02550 -0.0319 1.0000 0.1984
-4.250 -0.4872 0.03426 0.02411 -0.0312 1.0000 0.2084
-4.000 -0.4673 0.03326 0.02318 -0.0303 1.0000 0.2207
-3.750 -0.4473 0.03238 0.02230 -0.0294 1.0000 0.2378
-3.500 -0.4276 0.03148 0.02154 -0.0283 1.0000 0.2592
-3.250 -0.4080 0.03049 0.02081 -0.0273 1.0000 0.2943
-3.000 -0.3891 0.02908 0.02027 -0.0263 1.0000 0.3725
-2.750 -0.3849 0.02914 0.02179 -0.0197 1.0000 0.5836
-2.500 -0.3839 0.03028 0.02302 -0.0124 1.0000 0.6735
-2.250 -0.3817 0.03106 0.02380 -0.0057 1.0000 0.7238
-2.000 -0.3790 0.03153 0.02422 0.0004 1.0000 0.7651
-1.750 -0.3757 0.03174 0.02436 0.0061 1.0000 0.8031
-1.500 -0.3722 0.03174 0.02431 0.0115 1.0000 0.8391
-1.250 -0.3662 0.03166 0.02417 0.0162 1.0000 0.8778
-1.000 -0.3377 0.03217 0.02460 0.0173 1.0000 0.9271
-0.750 -0.1447 0.03712 0.02888 -0.0129 0.9924 0.9905
-0.500 -0.0853 0.03823 0.02972 -0.0219 0.9802 1.0000
-0.250 -0.0745 0.03819 0.02959 -0.0222 0.9726 1.0000
0.000 -0.0640 0.03824 0.02954 -0.0223 0.9645 1.0000
0.250 -0.0562 0.03827 0.02949 -0.0220 0.9574 1.0000
0.500 -0.0509 0.03825 0.02938 -0.0212 0.9500 1.0000
0.750 -0.0247 0.03909 0.03005 -0.0237 0.9397 1.0000
1.000 -0.0114 0.03933 0.03019 -0.0239 0.9306 1.0000
1.250 0.0199 0.04031 0.03102 -0.0269 0.9173 1.0000
1.500 0.0540 0.04140 0.03197 -0.0301 0.9025 1.0000
1.750 0.0890 0.04252 0.03296 -0.0333 0.8867 1.0000
2.000 0.1243 0.04364 0.03395 -0.0362 0.8702 1.0000
2.250 0.1595 0.04475 0.03495 -0.0390 0.8534 1.0000
2.500 0.1945 0.04584 0.03594 -0.0415 0.8365 1.0000
2.750 0.2297 0.04691 0.03693 -0.0438 0.8195 1.0000
3.000 0.2628 0.04795 0.03790 -0.0458 0.8033 1.0000
3.250 0.2952 0.04896 0.03885 -0.0475 0.7871 1.0000
3.500 0.3267 0.04995 0.03979 -0.0490 0.7711 1.0000
3.750 0.3574 0.05092 0.04073 -0.0502 0.7551 1.0000
4.000 0.3878 0.05185 0.04164 -0.0513 0.7391 1.0000
4.250 0.4178 0.05277 0.04254 -0.0522 0.7231 1.0000
4.500 0.4488 0.05359 0.04337 -0.0531 0.7069 1.0000
4.750 0.4784 0.05440 0.04418 -0.0537 0.6910 1.0000
5.000 0.5092 0.05508 0.04487 -0.0543 0.6748 1.0000
5.250 0.5388 0.05575 0.04557 -0.0546 0.6588 1.0000
5.500 0.5690 0.05628 0.04614 -0.0548 0.6428 1.0000
5.750 0.5976 0.05682 0.04673 -0.0548 0.6269 1.0000
6.000 0.6266 0.05722 0.04717 -0.0547 0.6111 1.0000
6.250 0.6538 0.05767 0.04767 -0.0543 0.5955 1.0000
6.500 0.6803 0.05808 0.04816 -0.0539 0.5801 1.0000
6.750 0.7036 0.05870 0.04883 -0.0532 0.5648 1.0000
7.000 0.7264 0.05930 0.04949 -0.0525 0.5496 1.0000
7.250 0.7467 0.06011 0.05038 -0.0516 0.5345 1.0000
7.500 0.7657 0.06102 0.05135 -0.0508 0.5196 1.0000
7.750 0.7831 0.06209 0.05249 -0.0498 0.5048 1.0000
8.000 0.7971 0.06356 0.05402 -0.0489 0.4902 1.0000
8.250 0.9296 0.05252 0.04327 -0.0486 0.4858 1.0000
8.500 0.9474 0.05322 0.04406 -0.0472 0.4710 1.0000
9.000 1.1116 0.04502 0.03611 -0.0511 0.4382 1.0000
9.250 1.1382 0.04543 0.03657 -0.0503 0.4219 1.0000
9.500 0.8799 0.07332 0.06425 -0.0439 0.4116 1.0000
9.750 0.8520 0.08057 0.07149 -0.0446 0.3996 1.0000
10.000 0.9264 0.07426 0.06538 -0.0415 0.3900 1.0000
10.250 1.2443 0.04822 0.03951 -0.0479 0.3602 1.0000
10.500 1.1789 0.05387 0.04539 -0.0403 0.3569 1.0000
10.750 0.8864 0.09174 0.08294 -0.0436 0.3599 1.0000
11.000 0.8214 0.10502 0.09614 -0.0480 0.3564 1.0000
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Polar data table (+)
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