HQ 3.5/10 AIRFOIL (hq3510-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/10 AIRFOIL (hq3510-il) Reynolds number: 50,000 Max Cl/Cd: 40.54 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3510-il-50000-n5.txt Download as CSV file: xf-hq3510-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/10 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3493 0.11244 0.10571 -0.0397 1.0000 0.0951
-9.000 -0.3601 0.11074 0.10415 -0.0410 1.0000 0.0957
-8.750 -0.3706 0.10882 0.10237 -0.0415 1.0000 0.0960
-8.500 -0.3642 0.10460 0.09824 -0.0401 1.0000 0.0968
-8.250 -0.3594 0.10117 0.09486 -0.0384 1.0000 0.0978
-8.000 -0.3568 0.09833 0.09207 -0.0366 1.0000 0.1001
-7.750 -0.3620 0.09383 0.08760 -0.0369 1.0000 0.0628
-7.500 -0.3817 0.09106 0.08496 -0.0364 1.0000 0.0520
-7.250 -0.3897 0.08864 0.08264 -0.0350 1.0000 0.0510
-7.000 -0.3971 0.08600 0.08009 -0.0342 1.0000 0.0494
-6.750 -0.4052 0.08298 0.07716 -0.0347 1.0000 0.0489
-6.500 -0.4113 0.07957 0.07380 -0.0357 1.0000 0.0480
-6.250 -0.4152 0.07584 0.07008 -0.0372 1.0000 0.0465
-6.000 -0.4162 0.07185 0.06606 -0.0390 1.0000 0.0456
-5.750 -0.4136 0.06779 0.06192 -0.0409 1.0000 0.0451
-5.500 -0.4067 0.06319 0.05714 -0.0436 1.0000 0.0441
-5.250 -0.3797 0.05762 0.05122 -0.0497 0.9951 0.0438
-4.750 -0.3099 0.04721 0.03940 -0.0606 0.9850 0.0412
-4.500 -0.2789 0.04328 0.03490 -0.0635 0.9799 0.0412
-4.250 -0.2457 0.03963 0.03079 -0.0663 0.9757 0.0417
-4.000 -0.2117 0.03655 0.02726 -0.0688 0.9718 0.0428
-3.750 -0.1804 0.03427 0.02459 -0.0701 0.9668 0.0445
-3.500 -0.1463 0.03253 0.02247 -0.0718 0.9623 0.0493
-3.250 -0.1102 0.03080 0.02023 -0.0731 0.9585 0.0551
-3.000 -0.0821 0.02945 0.01878 -0.0733 0.9529 0.0615
-2.750 -0.0499 0.02829 0.01742 -0.0740 0.9482 0.0750
-2.500 -0.0177 0.02732 0.01624 -0.0747 0.9435 0.0961
-2.250 0.0121 0.02637 0.01526 -0.0756 0.9376 0.1225
-2.000 0.0489 0.02537 0.01432 -0.0778 0.9331 0.1595
-1.750 0.0759 0.02337 0.01429 -0.0784 0.9286 0.5512
-1.500 0.0918 0.02331 0.01451 -0.0745 0.9213 0.7310
-1.250 0.1052 0.02309 0.01444 -0.0700 0.9143 0.8375
-1.000 0.1442 0.02273 0.01400 -0.0715 0.9075 1.0000
-0.750 0.1797 0.02298 0.01386 -0.0738 0.9010 1.0000
-0.500 0.2128 0.02323 0.01377 -0.0755 0.8935 1.0000
-0.250 0.2468 0.02351 0.01375 -0.0773 0.8864 1.0000
0.000 0.2803 0.02377 0.01377 -0.0789 0.8789 1.0000
0.250 0.3111 0.02405 0.01383 -0.0800 0.8707 1.0000
0.500 0.3474 0.02428 0.01388 -0.0819 0.8638 1.0000
0.750 0.3752 0.02459 0.01404 -0.0824 0.8543 1.0000
1.000 0.4151 0.02473 0.01405 -0.0847 0.8483 1.0000
1.500 0.4707 0.02531 0.01445 -0.0853 0.8287 1.0000
1.750 0.5081 0.02540 0.01449 -0.0870 0.8213 1.0000
2.000 0.5367 0.02555 0.01461 -0.0871 0.8095 1.0000
2.250 0.5689 0.02546 0.01450 -0.0874 0.7966 1.0000
2.500 0.6021 0.02525 0.01427 -0.0876 0.7829 1.0000
2.750 0.6343 0.02503 0.01408 -0.0877 0.7690 1.0000
3.000 0.6647 0.02491 0.01399 -0.0876 0.7557 1.0000
3.250 0.6939 0.02486 0.01399 -0.0873 0.7429 1.0000
3.500 0.7230 0.02480 0.01398 -0.0871 0.7295 1.0000
3.750 0.7518 0.02472 0.01402 -0.0867 0.7153 1.0000
4.000 0.7804 0.02462 0.01400 -0.0862 0.7002 1.0000
4.250 0.8094 0.02448 0.01394 -0.0857 0.6843 1.0000
4.500 0.8395 0.02427 0.01383 -0.0853 0.6675 1.0000
4.750 0.8628 0.02436 0.01407 -0.0840 0.6462 1.0000
5.000 0.8922 0.02417 0.01397 -0.0834 0.6253 1.0000
5.250 0.9162 0.02425 0.01415 -0.0822 0.5998 1.0000
5.500 0.9418 0.02429 0.01424 -0.0811 0.5722 1.0000
5.750 0.9678 0.02438 0.01440 -0.0801 0.5426 1.0000
6.000 0.9920 0.02463 0.01464 -0.0789 0.5108 1.0000
6.250 1.0152 0.02504 0.01502 -0.0777 0.4790 1.0000
6.500 1.0374 0.02561 0.01552 -0.0765 0.4491 1.0000
6.750 1.0587 0.02632 0.01623 -0.0753 0.4220 1.0000
7.000 1.0796 0.02711 0.01700 -0.0742 0.3975 1.0000
7.250 1.0999 0.02797 0.01787 -0.0730 0.3750 1.0000
7.500 1.1199 0.02888 0.01884 -0.0719 0.3541 1.0000
7.750 1.1395 0.02982 0.01985 -0.0708 0.3344 1.0000
8.000 1.1589 0.03078 0.02087 -0.0697 0.3158 1.0000
8.250 1.1768 0.03181 0.02205 -0.0684 0.2971 1.0000
8.500 1.1941 0.03289 0.02330 -0.0670 0.2789 1.0000
8.750 1.2108 0.03401 0.02449 -0.0656 0.2613 1.0000
9.000 1.2242 0.03522 0.02591 -0.0639 0.2433 1.0000
9.250 1.2357 0.03647 0.02737 -0.0619 0.2254 1.0000
9.500 1.2428 0.03771 0.02876 -0.0594 0.2079 1.0000
9.750 1.2463 0.03903 0.03020 -0.0566 0.1906 1.0000
10.000 1.2451 0.04056 0.03193 -0.0537 0.1712 1.0000
10.250 1.2402 0.04230 0.03370 -0.0509 0.1520 1.0000
10.500 1.2346 0.04446 0.03590 -0.0487 0.1295 1.0000
10.750 1.2277 0.04712 0.03848 -0.0469 0.1071 1.0000
11.000 1.2194 0.05035 0.04159 -0.0457 0.0869 1.0000
11.250 1.2118 0.05398 0.04518 -0.0447 0.0682 1.0000
11.500 1.2033 0.05793 0.04914 -0.0441 0.0570 1.0000
11.750 1.1929 0.06224 0.05353 -0.0440 0.0502 1.0000
12.000 1.1864 0.06645 0.05794 -0.0439 0.0442 1.0000
12.250 1.1775 0.07101 0.06259 -0.0444 0.0407 1.0000
12.500 1.1693 0.07569 0.06739 -0.0451 0.0381 1.0000
12.750 1.1635 0.08033 0.07229 -0.0458 0.0352 1.0000
13.000 1.1563 0.08526 0.07742 -0.0471 0.0329 1.0000
13.250 1.1487 0.09037 0.08267 -0.0488 0.0313 1.0000
13.500 1.1411 0.09563 0.08803 -0.0506 0.0300 1.0000
13.750 1.1345 0.10089 0.09337 -0.0524 0.0290 1.0000
14.000 1.1286 0.10649 0.09928 -0.0545 0.0282 1.0000
14.250 1.1216 0.11253 0.10558 -0.0570 0.0276 1.0000
14.500 1.1134 0.11906 0.11235 -0.0600 0.0273 1.0000
14.750 1.1040 0.12616 0.11968 -0.0637 0.0271 1.0000
15.000 1.0928 0.13402 0.12776 -0.0680 0.0270 1.0000
15.250 1.0807 0.14256 0.13648 -0.0730 0.0272 1.0000
15.500 1.0681 0.15173 0.14578 -0.0784 0.0275 1.0000
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