HQ 2.5/9 B AIRFOIL (hq259b-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.5/9 B AIRFOIL (hq259b-il) Reynolds number: 200,000 Max Cl/Cd: 79.57 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq259b-il-200000.txt Download as CSV file: xf-hq259b-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/9 B 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4217 0.08850 0.08495 -0.0365 1.0000 0.0467
-8.500 -0.4351 0.08455 0.08111 -0.0416 1.0000 0.0477
-8.250 -0.4473 0.08073 0.07737 -0.0443 1.0000 0.0478
-8.000 -0.4595 0.07644 0.07305 -0.0486 1.0000 0.0480
-7.750 -0.4706 0.07353 0.07008 -0.0491 1.0000 0.0481
-7.500 -0.4811 0.07101 0.06748 -0.0481 1.0000 0.0482
-7.250 -0.4961 0.06535 0.06184 -0.0471 1.0000 0.0489
-7.000 -0.4946 0.06218 0.05880 -0.0444 1.0000 0.0498
-6.750 -0.4930 0.06079 0.05751 -0.0413 1.0000 0.0513
-6.500 -0.4935 0.05890 0.05561 -0.0395 1.0000 0.0532
-6.250 -0.4734 0.05454 0.05105 -0.0440 0.9970 0.0571
-6.000 -0.4415 0.04735 0.04325 -0.0527 0.9915 0.0628
-5.750 -0.4144 0.04413 0.04005 -0.0551 0.9877 0.0654
-5.500 -0.3765 0.04046 0.03563 -0.0605 0.9837 0.0758
-5.250 -0.3521 0.03690 0.03219 -0.0620 0.9796 0.0787
-5.000 -0.3202 0.03439 0.02924 -0.0648 0.9751 0.0909
-4.750 -0.2872 0.03212 0.02678 -0.0674 0.9721 0.1054
-4.500 -0.2408 0.02406 0.01728 -0.0673 0.9707 0.0475
-4.250 -0.2108 0.02184 0.01474 -0.0679 0.9666 0.0472
-4.000 -0.1790 0.02039 0.01296 -0.0687 0.9627 0.0489
-3.750 -0.1456 0.01858 0.01099 -0.0698 0.9601 0.0496
-3.500 -0.1109 0.01726 0.00963 -0.0713 0.9579 0.0516
-3.250 -0.0739 0.01646 0.00882 -0.0732 0.9559 0.0556
-3.000 -0.0487 0.01598 0.00828 -0.0728 0.9499 0.0599
-2.750 -0.0166 0.01504 0.00738 -0.0738 0.9465 0.0655
-2.500 0.0190 0.01439 0.00676 -0.0756 0.9439 0.0785
-2.250 0.0560 0.01313 0.00605 -0.0781 0.9420 0.1953
-2.000 0.0746 0.01183 0.00632 -0.0770 0.9364 0.6227
-1.750 0.1084 0.01173 0.00637 -0.0775 0.9313 0.7005
-1.500 0.1510 0.01149 0.00623 -0.0794 0.9274 0.7565
-1.250 0.1772 0.01139 0.00617 -0.0782 0.9183 0.7888
-1.000 0.2108 0.01119 0.00601 -0.0781 0.9133 0.8244
-0.750 0.2320 0.01110 0.00597 -0.0758 0.9046 0.8529
-0.500 0.2627 0.01091 0.00575 -0.0758 0.8995 0.8708
-0.250 0.2879 0.01080 0.00564 -0.0749 0.8932 0.8868
0.000 0.3140 0.01064 0.00549 -0.0741 0.8869 0.9044
0.250 0.3462 0.01041 0.00525 -0.0744 0.8825 0.9232
0.500 0.3768 0.01031 0.00517 -0.0748 0.8745 0.9468
0.750 0.4223 0.01008 0.00493 -0.0782 0.8696 0.9701
1.000 0.4615 0.01000 0.00484 -0.0808 0.8617 1.0000
1.250 0.4917 0.00993 0.00471 -0.0812 0.8544 1.0000
1.500 0.5187 0.00995 0.00472 -0.0812 0.8444 1.0000
1.750 0.5478 0.00992 0.00466 -0.0813 0.8354 1.0000
2.000 0.5763 0.00988 0.00459 -0.0811 0.8253 1.0000
2.250 0.6031 0.00987 0.00458 -0.0807 0.8133 1.0000
2.500 0.6302 0.00985 0.00454 -0.0802 0.8005 1.0000
2.750 0.6571 0.00981 0.00451 -0.0796 0.7861 1.0000
3.000 0.6838 0.00976 0.00445 -0.0789 0.7693 1.0000
3.250 0.7097 0.00970 0.00437 -0.0779 0.7475 1.0000
3.500 0.7343 0.00965 0.00427 -0.0767 0.7145 1.0000
3.750 0.7582 0.00967 0.00419 -0.0754 0.6711 1.0000
4.000 0.7814 0.00982 0.00415 -0.0740 0.6089 1.0000
4.250 0.8021 0.01028 0.00421 -0.0724 0.5349 1.0000
4.500 0.8229 0.01092 0.00453 -0.0710 0.4807 1.0000
4.750 0.8449 0.01151 0.00491 -0.0700 0.4412 1.0000
5.000 0.8679 0.01202 0.00531 -0.0692 0.4094 1.0000
5.250 0.8910 0.01251 0.00571 -0.0685 0.3800 1.0000
5.500 0.9134 0.01302 0.00612 -0.0676 0.3452 1.0000
5.750 0.9352 0.01354 0.00650 -0.0667 0.3031 1.0000
6.000 0.9563 0.01415 0.00693 -0.0657 0.2532 1.0000
6.250 0.9751 0.01505 0.00748 -0.0645 0.1853 1.0000
6.500 0.9926 0.01621 0.00831 -0.0632 0.1328 1.0000
6.750 1.0110 0.01731 0.00922 -0.0619 0.1040 1.0000
7.000 1.0294 0.01841 0.01023 -0.0606 0.0827 1.0000
7.250 1.0470 0.01963 0.01141 -0.0590 0.0680 1.0000
7.500 1.0642 0.02097 0.01273 -0.0574 0.0594 1.0000
7.750 1.0830 0.02207 0.01384 -0.0562 0.0531 1.0000
8.000 1.1015 0.02359 0.01541 -0.0548 0.0492 1.0000
8.250 1.1224 0.02477 0.01670 -0.0538 0.0458 1.0000
8.500 1.1422 0.02597 0.01791 -0.0528 0.0425 1.0000
8.750 1.1631 0.02820 0.02022 -0.0520 0.0398 1.0000
9.000 1.1847 0.02973 0.02199 -0.0511 0.0381 1.0000
9.250 1.2049 0.03129 0.02373 -0.0500 0.0359 1.0000
9.500 1.2230 0.03261 0.02516 -0.0489 0.0338 1.0000
9.750 1.2417 0.03528 0.02791 -0.0483 0.0320 1.0000
10.000 1.2554 0.03917 0.03218 -0.0468 0.0311 1.0000
10.250 1.2654 0.04164 0.03504 -0.0447 0.0306 1.0000
10.500 1.2710 0.04436 0.03817 -0.0422 0.0299 1.0000
10.750 1.2721 0.04714 0.04134 -0.0394 0.0290 1.0000
11.000 1.2683 0.05006 0.04459 -0.0363 0.0283 1.0000
11.250 1.2581 0.05306 0.04789 -0.0328 0.0280 1.0000
11.500 1.2431 0.05647 0.05158 -0.0295 0.0279 1.0000
11.750 1.2239 0.06045 0.05584 -0.0270 0.0280 1.0000
12.000 1.2023 0.06491 0.06057 -0.0256 0.0281 1.0000
12.250 1.1787 0.07002 0.06592 -0.0255 0.0283 1.0000
12.500 1.1539 0.07583 0.07196 -0.0268 0.0286 1.0000
12.750 1.1282 0.08250 0.07882 -0.0296 0.0289 1.0000
13.000 1.1011 0.09039 0.08687 -0.0341 0.0293 1.0000
13.250 1.0734 0.09981 0.09643 -0.0406 0.0297 1.0000
13.500 1.0466 0.11050 0.10722 -0.0479 0.0305 1.0000
13.750 1.0249 0.12090 0.11765 -0.0538 0.0312 1.0000
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Polar data table (+)
Polar graphs
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