HQ 3.0/9 AIRFOIL (hq309-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/9 AIRFOIL (hq309-il) Reynolds number: 200,000 Max Cl/Cd: 84.76 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq309-il-200000.txt Download as CSV file: xf-hq309-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3649 0.08957 0.08619 -0.0359 1.0000 0.0365
-8.000 -0.3691 0.08679 0.08349 -0.0362 1.0000 0.0375
-7.750 -0.3775 0.08445 0.08123 -0.0358 1.0000 0.0381
-7.500 -0.3928 0.08275 0.07962 -0.0337 1.0000 0.0384
-7.250 -0.4117 0.08128 0.07825 -0.0312 1.0000 0.0386
-7.000 -0.4256 0.07904 0.07608 -0.0309 1.0000 0.0389
-6.750 -0.4360 0.07587 0.07295 -0.0334 1.0000 0.0393
-6.500 -0.4408 0.07248 0.06948 -0.0367 1.0000 0.0399
-6.250 -0.4096 0.06682 0.06348 -0.0476 0.9949 0.0405
-6.000 -0.3934 0.05829 0.05487 -0.0534 0.9904 0.0415
-5.750 -0.3710 0.05414 0.05076 -0.0560 0.9864 0.0430
-5.500 -0.3408 0.05011 0.04662 -0.0607 0.9830 0.0453
-5.250 -0.3119 0.04598 0.04224 -0.0648 0.9773 0.0486
-5.000 -0.2724 0.04090 0.03641 -0.0709 0.9721 0.0547
-4.750 -0.2410 0.03704 0.03257 -0.0741 0.9697 0.0571
-4.500 -0.2126 0.03431 0.02962 -0.0757 0.9639 0.0614
-4.250 -0.1776 0.03106 0.02589 -0.0785 0.9595 0.0703
-4.000 -0.1309 0.02415 0.01768 -0.0784 0.9577 0.0288
-3.750 -0.0941 0.02087 0.01405 -0.0808 0.9558 0.0317
-3.500 -0.0654 0.01946 0.01243 -0.0809 0.9498 0.0336
-3.250 -0.0296 0.01779 0.01053 -0.0820 0.9462 0.0344
-3.000 0.0088 0.01649 0.00911 -0.0837 0.9436 0.0381
-2.750 0.0490 0.01529 0.00790 -0.0861 0.9416 0.0519
-2.500 0.0751 0.01439 0.00704 -0.0859 0.9342 0.0829
-2.250 0.1138 0.01357 0.00645 -0.0885 0.9309 0.1396
-2.000 0.1453 0.01170 0.00642 -0.0898 0.9284 0.6425
-1.750 0.1699 0.01167 0.00645 -0.0887 0.9207 0.7014
-1.500 0.2040 0.01154 0.00632 -0.0893 0.9166 0.7497
-1.250 0.2317 0.01146 0.00626 -0.0886 0.9102 0.7875
-1.000 0.2579 0.01127 0.00614 -0.0873 0.9039 0.8307
-0.750 0.2794 0.01100 0.00597 -0.0848 0.8977 0.8750
-0.500 0.3045 0.01077 0.00575 -0.0835 0.8906 0.9065
-0.250 0.3432 0.01051 0.00544 -0.0852 0.8869 0.9297
0.000 0.3848 0.01040 0.00531 -0.0881 0.8794 0.9641
0.250 0.4293 0.01019 0.00502 -0.0916 0.8743 1.0000
0.500 0.4568 0.01014 0.00488 -0.0917 0.8638 1.0000
0.750 0.4858 0.01004 0.00470 -0.0918 0.8537 1.0000
1.000 0.5165 0.00992 0.00449 -0.0920 0.8456 1.0000
1.250 0.5431 0.00995 0.00448 -0.0918 0.8348 1.0000
1.500 0.5704 0.00995 0.00444 -0.0915 0.8245 1.0000
1.750 0.5981 0.00991 0.00435 -0.0912 0.8138 1.0000
2.000 0.6257 0.00987 0.00425 -0.0908 0.8024 1.0000
2.250 0.6531 0.00983 0.00420 -0.0904 0.7904 1.0000
2.500 0.6798 0.00983 0.00418 -0.0899 0.7774 1.0000
2.750 0.7065 0.00985 0.00417 -0.0894 0.7637 1.0000
3.000 0.7330 0.00987 0.00418 -0.0889 0.7490 1.0000
3.250 0.7588 0.00992 0.00423 -0.0883 0.7322 1.0000
3.500 0.7848 0.00997 0.00431 -0.0876 0.7137 1.0000
3.750 0.8109 0.01004 0.00434 -0.0870 0.6943 1.0000
4.000 0.8361 0.01014 0.00443 -0.0862 0.6707 1.0000
4.250 0.8610 0.01028 0.00453 -0.0854 0.6445 1.0000
4.500 0.8853 0.01047 0.00469 -0.0845 0.6138 1.0000
4.750 0.9086 0.01072 0.00486 -0.0834 0.5765 1.0000
5.000 0.9308 0.01108 0.00507 -0.0822 0.5324 1.0000
5.250 0.9515 0.01157 0.00536 -0.0808 0.4813 1.0000
5.500 0.9709 0.01220 0.00575 -0.0793 0.4282 1.0000
5.750 0.9898 0.01292 0.00624 -0.0778 0.3769 1.0000
6.000 1.0091 0.01362 0.00675 -0.0765 0.3300 1.0000
6.250 1.0286 0.01433 0.00729 -0.0753 0.2910 1.0000
6.500 1.0488 0.01501 0.00786 -0.0742 0.2588 1.0000
6.750 1.0684 0.01571 0.00843 -0.0731 0.2264 1.0000
7.000 1.0885 0.01638 0.00899 -0.0720 0.1912 1.0000
7.250 1.1074 0.01715 0.00960 -0.0709 0.1546 1.0000
7.500 1.1266 0.01794 0.01034 -0.0698 0.1238 1.0000
7.750 1.1440 0.01891 0.01117 -0.0684 0.0941 1.0000
8.000 1.1603 0.02002 0.01214 -0.0669 0.0666 1.0000
8.250 1.1740 0.02139 0.01338 -0.0650 0.0439 1.0000
8.500 1.1796 0.02361 0.01552 -0.0618 0.0237 1.0000
8.750 1.1939 0.02479 0.01685 -0.0598 0.0194 1.0000
9.000 1.2027 0.02636 0.01851 -0.0571 0.0169 1.0000
9.250 1.2023 0.02887 0.02115 -0.0533 0.0155 1.0000
9.500 1.2130 0.03055 0.02297 -0.0510 0.0149 1.0000
9.750 1.2244 0.03247 0.02506 -0.0489 0.0143 1.0000
10.000 1.2367 0.03470 0.02754 -0.0470 0.0140 1.0000
10.250 1.2486 0.03723 0.03032 -0.0452 0.0137 1.0000
10.500 1.2579 0.04005 0.03342 -0.0432 0.0135 1.0000
10.750 1.2629 0.04308 0.03677 -0.0409 0.0136 1.0000
11.000 1.2625 0.04630 0.04031 -0.0384 0.0136 1.0000
11.250 1.2575 0.04972 0.04404 -0.0360 0.0137 1.0000
11.500 1.2482 0.05339 0.04802 -0.0337 0.0138 1.0000
11.750 1.2361 0.05729 0.05221 -0.0320 0.0139 1.0000
12.000 1.2213 0.06160 0.05679 -0.0309 0.0141 1.0000
12.250 1.2046 0.06633 0.06177 -0.0306 0.0142 1.0000
12.500 1.1871 0.07143 0.06711 -0.0313 0.0143 1.0000
12.750 1.1680 0.07718 0.07307 -0.0329 0.0144 1.0000
13.000 1.1484 0.08351 0.07961 -0.0356 0.0145 1.0000
13.250 1.1281 0.09060 0.08689 -0.0393 0.0146 1.0000
13.500 1.1077 0.09843 0.09489 -0.0441 0.0147 1.0000
13.750 1.0876 0.10713 0.10375 -0.0498 0.0148 1.0000
14.000 1.0673 0.11685 0.11360 -0.0564 0.0149 1.0000
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