HQ 3.5/8 AIRFOIL (hq358-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/8 AIRFOIL (hq358-il) Reynolds number: 50,000 Max Cl/Cd: 40.94 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq358-il-50000.txt Download as CSV file: xf-hq358-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/8 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3764 0.09932 0.09308 -0.0271 1.0000 0.1763
-7.250 -0.3702 0.09578 0.08960 -0.0253 1.0000 0.1839
-7.000 -0.3880 0.09508 0.08908 -0.0240 1.0000 0.1899
-6.750 -0.3835 0.09180 0.08587 -0.0217 1.0000 0.1988
-6.500 -0.4043 0.09128 0.08552 -0.0233 1.0000 0.2047
-6.250 -0.4004 0.08813 0.08243 -0.0202 1.0000 0.2172
-6.000 -0.4005 0.08544 0.07982 -0.0180 1.0000 0.2295
-5.750 -0.4032 0.08304 0.07751 -0.0164 1.0000 0.2430
-5.500 -0.4096 0.08103 0.07559 -0.0166 1.0000 0.2589
-5.250 -0.4062 0.07812 0.07276 -0.0122 1.0000 0.2784
-5.000 -0.4099 0.07602 0.07074 -0.0109 1.0000 0.3028
-4.750 -0.4067 0.07376 0.06855 -0.0049 1.0000 0.3349
-4.500 -0.4067 0.07184 0.06672 0.0009 1.0000 0.3768
-4.250 -0.4082 0.07010 0.06507 0.0075 1.0000 0.4267
-3.000 -0.2122 0.04176 0.03468 -0.0556 1.0000 0.2179
-2.750 -0.1577 0.03703 0.02889 -0.0607 1.0000 0.1435
-2.500 -0.1189 0.03434 0.02536 -0.0622 1.0000 0.1201
-2.250 -0.0848 0.03237 0.02260 -0.0627 1.0000 0.1088
-2.000 -0.0561 0.03021 0.02017 -0.0627 1.0000 0.1061
-1.750 -0.0280 0.02867 0.01824 -0.0624 1.0000 0.1066
-1.500 -0.0029 0.02729 0.01672 -0.0618 1.0000 0.1168
-1.250 0.0220 0.02612 0.01537 -0.0607 1.0000 0.1264
-1.000 0.0488 0.02502 0.01418 -0.0600 1.0000 0.1444
-0.750 0.0882 0.02125 0.01302 -0.0616 1.0000 0.6537
-0.500 0.0926 0.02046 0.01215 -0.0554 1.0000 1.0000
-0.250 0.1161 0.02091 0.01201 -0.0553 1.0000 1.0000
0.000 0.1389 0.02139 0.01208 -0.0553 1.0000 1.0000
0.250 0.1611 0.02191 0.01226 -0.0553 1.0000 1.0000
0.500 0.1829 0.02247 0.01255 -0.0553 1.0000 1.0000
0.750 0.2041 0.02307 0.01288 -0.0554 1.0000 1.0000
1.000 0.2248 0.02372 0.01333 -0.0554 1.0000 1.0000
1.250 0.2452 0.02441 0.01387 -0.0554 1.0000 1.0000
1.500 0.2651 0.02516 0.01448 -0.0554 1.0000 1.0000
1.750 0.2844 0.02597 0.01518 -0.0555 1.0000 1.0000
2.000 0.3033 0.02683 0.01597 -0.0556 1.0000 1.0000
2.250 0.3216 0.02777 0.01682 -0.0557 1.0000 1.0000
2.500 0.3777 0.02952 0.01851 -0.0628 0.9812 1.0000
2.750 0.4403 0.03100 0.02000 -0.0705 0.9555 1.0000
3.000 0.4922 0.03200 0.02107 -0.0758 0.9305 1.0000
3.250 0.5379 0.03283 0.02197 -0.0796 0.9074 1.0000
3.500 0.5864 0.03350 0.02276 -0.0836 0.8848 1.0000
3.750 0.6385 0.03389 0.02331 -0.0876 0.8622 1.0000
4.000 0.6818 0.03408 0.02378 -0.0898 0.8373 1.0000
4.250 0.7284 0.03396 0.02389 -0.0920 0.8117 1.0000
4.500 0.7790 0.03336 0.02358 -0.0940 0.7855 1.0000
4.750 0.8347 0.03210 0.02277 -0.0959 0.7585 1.0000
5.000 0.8894 0.03032 0.02136 -0.0966 0.7299 1.0000
5.250 0.9370 0.02859 0.01995 -0.0960 0.6962 1.0000
5.500 0.9828 0.02690 0.01850 -0.0948 0.6576 1.0000
5.750 1.0170 0.02615 0.01796 -0.0929 0.6135 1.0000
6.000 1.0476 0.02594 0.01776 -0.0910 0.5696 1.0000
6.250 1.0747 0.02625 0.01804 -0.0891 0.5276 1.0000
6.500 1.0990 0.02694 0.01870 -0.0873 0.4871 1.0000
6.750 1.1213 0.02786 0.01959 -0.0853 0.4468 1.0000
7.000 1.1418 0.02896 0.02064 -0.0832 0.4053 1.0000
7.250 1.1595 0.03017 0.02190 -0.0807 0.3601 1.0000
7.500 1.1684 0.03122 0.02278 -0.0770 0.3058 1.0000
7.750 1.1676 0.03261 0.02379 -0.0724 0.2395 1.0000
8.000 1.1577 0.03473 0.02553 -0.0667 0.1668 1.0000
8.250 1.1557 0.03744 0.02772 -0.0627 0.1151 1.0000
8.500 1.1713 0.04077 0.03085 -0.0608 0.0871 1.0000
8.750 1.1925 0.04411 0.03419 -0.0597 0.0726 1.0000
9.000 1.2192 0.04859 0.03906 -0.0589 0.0671 1.0000
9.250 1.2357 0.05291 0.04395 -0.0571 0.0647 1.0000
9.500 1.2448 0.05738 0.04895 -0.0550 0.0637 1.0000
9.750 1.2461 0.06197 0.05406 -0.0526 0.0636 1.0000
10.000 1.2403 0.06658 0.05915 -0.0500 0.0641 1.0000
10.250 1.2287 0.07112 0.06409 -0.0474 0.0647 1.0000
10.500 1.2119 0.07531 0.06860 -0.0447 0.0654 1.0000
10.750 1.1924 0.07963 0.07316 -0.0428 0.0661 1.0000
11.000 1.1715 0.08434 0.07809 -0.0420 0.0668 1.0000
11.250 1.1497 0.08958 0.08351 -0.0424 0.0674 1.0000
11.500 1.1285 0.09541 0.08947 -0.0440 0.0682 1.0000
11.750 1.1095 0.10179 0.09595 -0.0466 0.0689 1.0000
12.000 1.0942 0.10859 0.10281 -0.0496 0.0697 1.0000
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Polar data table (+)
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