HQ 3.0/11 AIRFOIL (hq3011-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/11 AIRFOIL (hq3011-il) Reynolds number: 100,000 Max Cl/Cd: 58.5 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3011-il-100000.txt Download as CSV file: xf-hq3011-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/11 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3609 0.09508 0.09042 -0.0403 1.0000 0.0971
-8.500 -0.3806 0.09290 0.08839 -0.0418 1.0000 0.1001
-8.250 -0.4076 0.09141 0.08706 -0.0415 1.0000 0.1008
-8.000 -0.4373 0.09011 0.08590 -0.0395 1.0000 0.1010
-7.750 -0.4662 0.08773 0.08360 -0.0407 1.0000 0.1012
-7.500 -0.4929 0.08561 0.08144 -0.0414 1.0000 0.1015
-7.250 -0.4506 0.08262 0.07861 -0.0303 1.0000 0.1065
-7.000 -0.4635 0.08029 0.07635 -0.0294 1.0000 0.1083
-6.750 -0.4770 0.07738 0.07348 -0.0299 1.0000 0.1103
-6.500 -0.5109 0.07365 0.06940 -0.0382 1.0000 0.1156
-6.250 -0.5043 0.06931 0.06527 -0.0351 1.0000 0.1177
-6.000 -0.4975 0.06750 0.06356 -0.0315 1.0000 0.1224
-5.750 -0.5006 0.06333 0.05920 -0.0346 1.0000 0.1325
-5.500 -0.4931 0.06121 0.05713 -0.0327 1.0000 0.1398
-5.250 -0.4870 0.05799 0.05381 -0.0330 1.0000 0.1506
-5.000 -0.4681 0.05438 0.04983 -0.0380 0.9975 0.1745
-4.750 -0.4127 0.03994 0.03388 -0.0462 0.9953 0.0784
-4.500 -0.3724 0.03395 0.02683 -0.0487 0.9921 0.0641
-4.250 -0.3349 0.03059 0.02272 -0.0506 0.9879 0.0632
-4.000 -0.2967 0.02901 0.02082 -0.0530 0.9836 0.0698
-3.750 -0.2611 0.02695 0.01822 -0.0541 0.9790 0.0746
-3.500 -0.2258 0.02577 0.01682 -0.0556 0.9737 0.0873
-3.250 -0.1881 0.02425 0.01537 -0.0579 0.9699 0.1054
-3.000 -0.1582 0.02337 0.01453 -0.0586 0.9637 0.1231
-2.750 -0.1230 0.02264 0.01383 -0.0601 0.9583 0.1432
-2.500 -0.0882 0.02189 0.01328 -0.0617 0.9531 0.1734
-2.250 -0.0637 0.01973 0.01302 -0.0621 0.9473 0.5106
-2.000 -0.0370 0.01991 0.01360 -0.0602 0.9415 0.7019
-1.750 -0.0201 0.02008 0.01385 -0.0573 0.9329 0.7580
-1.500 0.0093 0.02039 0.01416 -0.0563 0.9270 0.8091
-1.250 0.0243 0.02052 0.01426 -0.0533 0.9179 0.8491
-1.000 0.0536 0.02054 0.01429 -0.0521 0.9125 0.9056
-0.500 0.1650 0.02065 0.01415 -0.0636 0.9001 1.0000
-0.250 0.1916 0.02080 0.01413 -0.0649 0.8904 1.0000
0.000 0.2391 0.02091 0.01407 -0.0693 0.8848 1.0000
0.250 0.2653 0.02116 0.01419 -0.0701 0.8746 1.0000
0.500 0.3159 0.02120 0.01410 -0.0745 0.8698 1.0000
0.750 0.3400 0.02149 0.01429 -0.0745 0.8589 1.0000
1.000 0.3753 0.02163 0.01435 -0.0761 0.8503 1.0000
1.250 0.4240 0.02139 0.01405 -0.0795 0.8428 1.0000
1.500 0.4581 0.02133 0.01394 -0.0804 0.8317 1.0000
1.750 0.5112 0.02074 0.01333 -0.0840 0.8266 1.0000
2.000 0.5375 0.02081 0.01337 -0.0836 0.8148 1.0000
2.250 0.5671 0.02079 0.01336 -0.0836 0.8040 1.0000
2.500 0.6125 0.02019 0.01277 -0.0857 0.7983 1.0000
2.750 0.6399 0.02012 0.01270 -0.0851 0.7862 1.0000
3.000 0.6700 0.01990 0.01253 -0.0849 0.7745 1.0000
3.250 0.7024 0.01953 0.01219 -0.0848 0.7630 1.0000
3.500 0.7371 0.01901 0.01168 -0.0848 0.7518 1.0000
3.750 0.7716 0.01845 0.01115 -0.0848 0.7400 1.0000
4.000 0.8013 0.01811 0.01086 -0.0842 0.7255 1.0000
4.250 0.8283 0.01789 0.01068 -0.0832 0.7087 1.0000
4.500 0.8561 0.01763 0.01045 -0.0823 0.6909 1.0000
4.750 0.8854 0.01730 0.01016 -0.0816 0.6721 1.0000
5.000 0.9115 0.01714 0.01002 -0.0805 0.6499 1.0000
5.250 0.9386 0.01695 0.00980 -0.0795 0.6256 1.0000
5.500 0.9626 0.01692 0.00976 -0.0781 0.5967 1.0000
5.750 0.9849 0.01701 0.00984 -0.0766 0.5633 1.0000
6.000 1.0074 0.01722 0.00992 -0.0751 0.5279 1.0000
6.250 1.0277 0.01764 0.01019 -0.0734 0.4897 1.0000
6.500 1.0479 0.01822 0.01057 -0.0718 0.4535 1.0000
6.750 1.0667 0.01893 0.01115 -0.0702 0.4184 1.0000
7.000 1.0854 0.01971 0.01177 -0.0686 0.3867 1.0000
7.250 1.1038 0.02052 0.01246 -0.0671 0.3574 1.0000
7.500 1.1216 0.02136 0.01320 -0.0656 0.3302 1.0000
7.750 1.1390 0.02224 0.01399 -0.0640 0.3050 1.0000
8.000 1.1566 0.02319 0.01481 -0.0626 0.2820 1.0000
8.250 1.1725 0.02409 0.01577 -0.0609 0.2592 1.0000
8.500 1.1884 0.02508 0.01669 -0.0592 0.2383 1.0000
8.750 1.2020 0.02603 0.01767 -0.0573 0.2172 1.0000
9.000 1.2159 0.02713 0.01866 -0.0554 0.1978 1.0000
9.250 1.2271 0.02826 0.01988 -0.0532 0.1778 1.0000
9.500 1.2379 0.02950 0.02106 -0.0510 0.1597 1.0000
9.750 1.2507 0.03099 0.02243 -0.0492 0.1434 1.0000
10.000 1.2647 0.03258 0.02403 -0.0475 0.1293 1.0000
10.250 1.2733 0.03386 0.02542 -0.0451 0.1179 1.0000
10.500 1.2803 0.03524 0.02694 -0.0426 0.1076 1.0000
10.750 1.2893 0.03681 0.02861 -0.0406 0.0984 1.0000
11.000 1.2955 0.03830 0.03001 -0.0385 0.0895 1.0000
11.250 1.2945 0.03964 0.03161 -0.0357 0.0820 1.0000
11.500 1.2944 0.04140 0.03346 -0.0334 0.0741 1.0000
11.750 1.2938 0.04317 0.03520 -0.0315 0.0668 1.0000
12.000 1.2896 0.04552 0.03783 -0.0294 0.0591 1.0000
12.250 1.2881 0.04842 0.04078 -0.0277 0.0519 1.0000
12.500 1.2851 0.05133 0.04381 -0.0261 0.0457 1.0000
12.750 1.2876 0.05520 0.04788 -0.0248 0.0415 1.0000
13.000 1.2850 0.05878 0.05180 -0.0236 0.0391 1.0000
13.250 1.2806 0.06244 0.05570 -0.0227 0.0371 1.0000
13.500 1.2763 0.06617 0.05961 -0.0222 0.0357 1.0000
13.750 1.2717 0.07018 0.06379 -0.0220 0.0348 1.0000
14.000 1.2643 0.07496 0.06874 -0.0221 0.0339 1.0000
14.250 1.2495 0.08058 0.07462 -0.0228 0.0335 1.0000
14.500 1.2316 0.08636 0.08066 -0.0242 0.0334 1.0000
14.750 1.2114 0.09262 0.08717 -0.0265 0.0334 1.0000
15.000 1.1922 0.09882 0.09362 -0.0295 0.0336 1.0000
15.250 1.1684 0.10625 0.10134 -0.0340 0.0341 1.0000
15.500 1.0924 0.12703 0.12267 -0.0493 0.0386 1.0000
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Polar data table (+)
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