HQ 3.0/9 AIRFOIL (hq309-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/9 AIRFOIL (hq309-il) Reynolds number: 100,000 Max Cl/Cd: 61.33 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq309-il-100000.txt Download as CSV file: xf-hq309-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/9 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3689 0.09414 0.08941 -0.0348 1.0000 0.0756
-8.000 -0.3755 0.09171 0.08708 -0.0356 1.0000 0.0779
-7.750 -0.3904 0.08996 0.08547 -0.0361 1.0000 0.0792
-7.500 -0.4090 0.08819 0.08384 -0.0373 1.0000 0.0798
-7.250 -0.4251 0.08557 0.08129 -0.0414 1.0000 0.0802
-7.000 -0.4393 0.08336 0.07900 -0.0439 1.0000 0.0805
-6.750 -0.4254 0.07891 0.07478 -0.0348 1.0000 0.0831
-6.500 -0.4264 0.07661 0.07252 -0.0324 1.0000 0.0853
-6.250 -0.4300 0.07386 0.06980 -0.0324 1.0000 0.0879
-6.000 -0.4331 0.07047 0.06636 -0.0358 1.0000 0.0920
-5.750 -0.4339 0.06606 0.06176 -0.0408 1.0000 0.0955
-5.500 -0.4288 0.06336 0.05919 -0.0372 1.0000 0.0983
-5.250 -0.4199 0.06032 0.05602 -0.0390 1.0000 0.1059
-5.000 -0.4108 0.05639 0.05199 -0.0404 1.0000 0.1113
-4.750 -0.3955 0.05318 0.04848 -0.0433 1.0000 0.1233
-4.500 -0.3849 0.05042 0.04585 -0.0414 1.0000 0.1298
-4.250 -0.3681 0.04741 0.04262 -0.0435 1.0000 0.1520
-4.000 -0.3546 0.04505 0.04032 -0.0426 1.0000 0.1704
-3.750 -0.3389 0.04276 0.03796 -0.0425 1.0000 0.1997
-3.250 -0.2329 0.03005 0.02257 -0.0499 1.0000 0.0647
-3.000 -0.2050 0.02731 0.01943 -0.0500 1.0000 0.0605
-2.750 -0.1773 0.02527 0.01691 -0.0497 1.0000 0.0586
-2.500 -0.1432 0.02371 0.01503 -0.0506 0.9976 0.0611
-2.250 -0.1033 0.02239 0.01349 -0.0528 0.9932 0.0710
-2.000 -0.0660 0.02099 0.01211 -0.0543 0.9883 0.0855
-1.750 -0.0268 0.01996 0.01123 -0.0568 0.9836 0.1353
-1.500 0.0043 0.01740 0.01099 -0.0578 0.9801 0.6352
-1.250 0.0215 0.01730 0.01131 -0.0536 0.9722 0.8265
-1.000 0.0627 0.01704 0.01107 -0.0556 0.9649 1.0000
-0.750 0.1061 0.01742 0.01111 -0.0595 0.9574 1.0000
-0.500 0.1441 0.01774 0.01115 -0.0622 0.9487 1.0000
-0.250 0.1904 0.01812 0.01128 -0.0664 0.9420 1.0000
0.000 0.2237 0.01839 0.01138 -0.0681 0.9322 1.0000
0.250 0.2627 0.01869 0.01151 -0.0707 0.9238 1.0000
0.500 0.3046 0.01893 0.01163 -0.0737 0.9159 1.0000
0.750 0.3376 0.01919 0.01179 -0.0751 0.9058 1.0000
1.000 0.3788 0.01938 0.01190 -0.0778 0.8978 1.0000
1.250 0.4193 0.01947 0.01195 -0.0802 0.8887 1.0000
1.500 0.4572 0.01947 0.01193 -0.0819 0.8772 1.0000
1.750 0.4995 0.01933 0.01179 -0.0843 0.8664 1.0000
2.000 0.5523 0.01891 0.01139 -0.0881 0.8597 1.0000
2.250 0.5856 0.01880 0.01131 -0.0887 0.8477 1.0000
2.500 0.6196 0.01863 0.01117 -0.0892 0.8359 1.0000
2.750 0.6546 0.01833 0.01096 -0.0897 0.8238 1.0000
3.000 0.6892 0.01795 0.01063 -0.0899 0.8110 1.0000
3.250 0.7224 0.01755 0.01029 -0.0897 0.7974 1.0000
3.500 0.7542 0.01717 0.00998 -0.0893 0.7828 1.0000
3.750 0.7853 0.01677 0.00970 -0.0888 0.7672 1.0000
4.000 0.8165 0.01636 0.00934 -0.0881 0.7506 1.0000
4.250 0.8426 0.01614 0.00921 -0.0868 0.7291 1.0000
4.500 0.8711 0.01583 0.00894 -0.0858 0.7066 1.0000
4.750 0.8972 0.01564 0.00883 -0.0844 0.6793 1.0000
5.000 0.9216 0.01557 0.00879 -0.0828 0.6461 1.0000
5.250 0.9454 0.01560 0.00878 -0.0812 0.6070 1.0000
5.500 0.9678 0.01578 0.00886 -0.0794 0.5605 1.0000
5.750 0.9882 0.01621 0.00909 -0.0775 0.5078 1.0000
6.000 1.0072 0.01689 0.00956 -0.0756 0.4545 1.0000
6.250 1.0252 0.01775 0.01013 -0.0737 0.4056 1.0000
6.500 1.0428 0.01863 0.01084 -0.0720 0.3603 1.0000
6.750 1.0601 0.01954 0.01158 -0.0703 0.3203 1.0000
7.000 1.0772 0.02050 0.01240 -0.0687 0.2838 1.0000
7.250 1.0940 0.02151 0.01332 -0.0670 0.2488 1.0000
7.500 1.1094 0.02261 0.01438 -0.0652 0.2146 1.0000
7.750 1.1228 0.02385 0.01552 -0.0632 0.1769 1.0000
8.000 1.1351 0.02544 0.01690 -0.0610 0.1434 1.0000
8.250 1.1481 0.02696 0.01833 -0.0590 0.1167 1.0000
8.500 1.1588 0.02826 0.01954 -0.0570 0.0938 1.0000
8.750 1.1698 0.02960 0.02094 -0.0550 0.0721 1.0000
9.000 1.1763 0.03207 0.02336 -0.0522 0.0533 1.0000
9.250 1.1887 0.03524 0.02654 -0.0501 0.0425 1.0000
9.500 1.2074 0.03799 0.02948 -0.0487 0.0373 1.0000
9.750 1.2310 0.04278 0.03434 -0.0487 0.0340 1.0000
10.000 1.2415 0.04550 0.03751 -0.0465 0.0325 1.0000
10.250 1.2472 0.04828 0.04080 -0.0440 0.0308 1.0000
10.500 1.2484 0.05124 0.04415 -0.0412 0.0294 1.0000
10.750 1.2443 0.05439 0.04765 -0.0382 0.0288 1.0000
11.000 1.2355 0.05775 0.05135 -0.0352 0.0285 1.0000
11.250 1.2222 0.06150 0.05544 -0.0326 0.0287 1.0000
11.500 1.2057 0.06556 0.05982 -0.0306 0.0288 1.0000
11.750 1.1872 0.06999 0.06454 -0.0296 0.0290 1.0000
12.000 1.1669 0.07496 0.06977 -0.0297 0.0293 1.0000
12.250 1.1451 0.08053 0.07558 -0.0309 0.0295 1.0000
12.500 1.1228 0.08674 0.08201 -0.0333 0.0299 1.0000
12.750 1.0994 0.09388 0.08933 -0.0371 0.0303 1.0000
13.000 1.0756 0.10207 0.09761 -0.0422 0.0309 1.0000
13.250 1.0530 0.11118 0.10683 -0.0481 0.0319 1.0000
13.500 1.0338 0.12052 0.11622 -0.0541 0.0328 1.0000
13.750 1.0198 0.12926 0.12498 -0.0588 0.0336 1.0000
14.000 0.9757 0.15404 0.14974 -0.0741 0.0434 1.0000
14.250 0.9754 0.16110 0.15680 -0.0771 0.0460 1.0000
14.500 0.9707 0.17217 0.16780 -0.0811 0.0560 1.0000
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