HQ 3.0/10 AIRFOIL (hq3010-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/10 AIRFOIL (hq3010-il) Reynolds number: 50,000 Max Cl/Cd: 37.72 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3010-il-50000.txt Download as CSV file: xf-hq3010-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/10 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3622 0.10577 0.09911 -0.0283 1.0000 0.2230
-8.500 -0.3754 0.10482 0.09830 -0.0285 1.0000 0.2326
-8.250 -0.3734 0.10202 0.09558 -0.0272 1.0000 0.2466
-8.000 -0.3698 0.09914 0.09278 -0.0257 1.0000 0.2604
-7.750 -0.3702 0.09661 0.09035 -0.0240 1.0000 0.2746
-7.500 -0.3721 0.09429 0.08813 -0.0221 1.0000 0.2889
-7.250 -0.3778 0.09230 0.08626 -0.0197 1.0000 0.3034
-7.000 -0.3842 0.09044 0.08449 -0.0168 1.0000 0.3179
-6.750 -0.3662 0.08652 0.08058 -0.0143 1.0000 0.3397
-6.500 -0.3766 0.08518 0.07937 -0.0105 1.0000 0.3580
-6.250 -0.3964 0.08455 0.07890 -0.0059 1.0000 0.3741
-6.000 -0.3851 0.08160 0.07598 -0.0026 1.0000 0.4003
-5.750 -0.3821 0.07929 0.07375 0.0012 1.0000 0.4269
-5.500 -0.3845 0.07755 0.07209 0.0058 1.0000 0.4565
-4.500 -0.3842 0.04803 0.04086 -0.0462 1.0000 0.1474
-4.250 -0.3582 0.04331 0.03567 -0.0475 1.0000 0.1296
-4.000 -0.3278 0.03945 0.03093 -0.0491 1.0000 0.1184
-3.750 -0.3008 0.03672 0.02756 -0.0497 1.0000 0.1194
-3.500 -0.2749 0.03396 0.02450 -0.0498 1.0000 0.1224
-3.250 -0.2480 0.03169 0.02186 -0.0496 1.0000 0.1248
-3.000 -0.2216 0.02994 0.01966 -0.0492 1.0000 0.1355
-2.750 -0.1968 0.02826 0.01784 -0.0485 1.0000 0.1499
-2.500 -0.1737 0.02687 0.01647 -0.0475 1.0000 0.1736
-2.250 -0.1506 0.02564 0.01522 -0.0464 1.0000 0.2038
-2.000 -0.1246 0.02437 0.01412 -0.0460 1.0000 0.2471
-1.750 -0.1116 0.02178 0.01425 -0.0412 1.0000 0.7041
-1.500 -0.1170 0.02104 0.01397 -0.0307 1.0000 0.9277
-1.250 -0.0918 0.02099 0.01338 -0.0317 1.0000 1.0000
-1.000 -0.0665 0.02131 0.01323 -0.0327 1.0000 1.0000
-0.750 -0.0419 0.02169 0.01319 -0.0336 1.0000 1.0000
-0.500 -0.0179 0.02212 0.01328 -0.0344 1.0000 1.0000
-0.250 0.0053 0.02261 0.01347 -0.0350 1.0000 1.0000
0.000 0.0279 0.02313 0.01373 -0.0356 1.0000 1.0000
0.250 0.0499 0.02371 0.01405 -0.0360 1.0000 1.0000
0.500 0.0713 0.02433 0.01447 -0.0363 1.0000 1.0000
0.750 0.0922 0.02499 0.01496 -0.0367 1.0000 1.0000
1.000 0.1126 0.02571 0.01552 -0.0370 1.0000 1.0000
1.250 0.1325 0.02647 0.01614 -0.0372 1.0000 1.0000
1.500 0.1610 0.02753 0.01708 -0.0393 0.9957 1.0000
1.750 0.2105 0.02914 0.01856 -0.0450 0.9806 1.0000
2.000 0.2546 0.03049 0.01982 -0.0497 0.9643 1.0000
2.250 0.2985 0.03177 0.02105 -0.0541 0.9469 1.0000
2.500 0.3461 0.03305 0.02231 -0.0588 0.9288 1.0000
2.750 0.3864 0.03409 0.02336 -0.0621 0.9094 1.0000
3.000 0.4276 0.03505 0.02434 -0.0652 0.8897 1.0000
3.250 0.4754 0.03596 0.02531 -0.0691 0.8708 1.0000
3.500 0.5064 0.03671 0.02614 -0.0703 0.8498 1.0000
3.750 0.5541 0.03727 0.02682 -0.0735 0.8303 1.0000
4.000 0.5861 0.03782 0.02746 -0.0743 0.8082 1.0000
4.250 0.6391 0.03777 0.02763 -0.0773 0.7881 1.0000
4.500 0.6719 0.03794 0.02795 -0.0775 0.7643 1.0000
4.750 0.7200 0.03739 0.02761 -0.0789 0.7422 1.0000
5.000 0.7750 0.03611 0.02664 -0.0804 0.7201 1.0000
5.250 0.8171 0.03506 0.02583 -0.0800 0.6960 1.0000
5.500 0.8706 0.03304 0.02409 -0.0801 0.6730 1.0000
5.750 0.9202 0.03103 0.02236 -0.0795 0.6462 1.0000
6.000 0.9565 0.02984 0.02133 -0.0778 0.6134 1.0000
6.250 1.0003 0.02824 0.01978 -0.0766 0.5779 1.0000
6.500 1.0285 0.02793 0.01946 -0.0745 0.5379 1.0000
6.750 1.0550 0.02804 0.01953 -0.0725 0.4971 1.0000
7.000 1.0787 0.02860 0.01998 -0.0706 0.4570 1.0000
7.250 1.1010 0.02949 0.02072 -0.0688 0.4188 1.0000
7.500 1.1235 0.03052 0.02154 -0.0671 0.3819 1.0000
7.750 1.1400 0.03185 0.02287 -0.0650 0.3470 1.0000
8.000 1.1595 0.03315 0.02403 -0.0632 0.3124 1.0000
8.250 1.1748 0.03480 0.02566 -0.0611 0.2796 1.0000
8.500 1.1904 0.03668 0.02753 -0.0591 0.2489 1.0000
8.750 1.2052 0.03861 0.02943 -0.0571 0.2207 1.0000
9.000 1.2248 0.04109 0.03187 -0.0558 0.1978 1.0000
9.250 1.2370 0.04343 0.03442 -0.0536 0.1784 1.0000
9.500 1.2527 0.04611 0.03724 -0.0520 0.1625 1.0000
9.750 1.2635 0.04954 0.04102 -0.0499 0.1511 1.0000
10.000 1.2702 0.05239 0.04412 -0.0476 0.1384 1.0000
10.250 1.2768 0.05614 0.04812 -0.0454 0.1290 1.0000
10.500 1.2822 0.05944 0.05160 -0.0432 0.1175 1.0000
10.750 1.2659 0.06295 0.05565 -0.0394 0.1126 1.0000
11.000 1.2614 0.06537 0.05814 -0.0368 0.1019 1.0000
11.250 1.2613 0.06776 0.06046 -0.0346 0.0914 1.0000
11.500 1.2394 0.07165 0.06470 -0.0314 0.0908 1.0000
11.750 1.2159 0.07597 0.06930 -0.0292 0.0906 1.0000
12.000 1.1924 0.08081 0.07438 -0.0282 0.0909 1.0000
12.250 1.1688 0.08625 0.08001 -0.0283 0.0915 1.0000
12.500 1.1470 0.09226 0.08616 -0.0294 0.0922 1.0000
12.750 1.1255 0.09885 0.09287 -0.0315 0.0928 1.0000
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Polar data table (+)
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