HQ 3.0/14 AIRFOIL (hq3014-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/14 AIRFOIL (hq3014-il) Reynolds number: 200,000 Max Cl/Cd: 77.5 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3014-il-200000.txt Download as CSV file: xf-hq3014-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/14 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4749 0.06984 0.06633 -0.0710 1.0000 0.0346
-10.500 -0.5005 0.06560 0.06211 -0.0714 1.0000 0.0343
-10.250 -0.5347 0.06336 0.05992 -0.0685 1.0000 0.0342
-10.000 -0.5649 0.06247 0.05909 -0.0643 1.0000 0.0339
-9.750 -0.5861 0.05721 0.05366 -0.0695 0.9938 0.0336
-9.500 -0.5919 0.05003 0.04609 -0.0764 0.9836 0.0330
-9.250 -0.5933 0.04375 0.03925 -0.0799 0.9737 0.0334
-9.000 -0.5836 0.03871 0.03357 -0.0822 0.9667 0.0342
-8.500 -0.5412 0.03112 0.02505 -0.0857 0.9566 0.0363
-8.250 -0.5184 0.02972 0.02353 -0.0859 0.9499 0.0379
-8.000 -0.4887 0.02796 0.02148 -0.0872 0.9455 0.0405
-7.750 -0.4554 0.02557 0.01870 -0.0892 0.9429 0.0444
-7.500 -0.4161 0.02486 0.01799 -0.0921 0.9411 0.0500
-7.250 -0.3967 0.02365 0.01655 -0.0910 0.9329 0.0547
-7.000 -0.3623 0.02284 0.01573 -0.0928 0.9296 0.0602
-6.750 -0.3264 0.02180 0.01449 -0.0947 0.9271 0.0667
-6.500 -0.3020 0.02128 0.01400 -0.0945 0.9206 0.0719
-6.250 -0.2710 0.02074 0.01329 -0.0952 0.9159 0.0767
-6.000 -0.2381 0.01947 0.01203 -0.0964 0.9128 0.0817
-5.750 -0.2105 0.01887 0.01141 -0.0964 0.9077 0.0864
-5.500 -0.1846 0.01845 0.01087 -0.0960 0.9015 0.0909
-5.250 -0.1554 0.01742 0.00994 -0.0965 0.8977 0.0971
-5.000 -0.1302 0.01697 0.00944 -0.0960 0.8921 0.1042
-4.750 -0.1072 0.01635 0.00889 -0.0953 0.8857 0.1136
-4.500 -0.0784 0.01570 0.00828 -0.0956 0.8818 0.1306
-4.250 -0.0579 0.01516 0.00791 -0.0945 0.8749 0.1597
-4.000 -0.0359 0.01417 0.00743 -0.0941 0.8691 0.2636
-3.750 -0.0133 0.01312 0.00722 -0.0935 0.8653 0.4634
-3.500 0.0068 0.01318 0.00744 -0.0919 0.8576 0.5371
-3.250 0.0346 0.01321 0.00750 -0.0914 0.8529 0.5799
-3.000 0.0649 0.01325 0.00750 -0.0913 0.8495 0.6086
-2.750 0.0864 0.01346 0.00770 -0.0899 0.8414 0.6290
-2.500 0.1154 0.01350 0.00766 -0.0896 0.8367 0.6468
-2.250 0.1426 0.01358 0.00771 -0.0890 0.8317 0.6618
-2.000 0.1667 0.01372 0.00785 -0.0880 0.8247 0.6772
-1.750 0.1949 0.01381 0.00791 -0.0873 0.8203 0.6963
-1.500 0.2187 0.01400 0.00811 -0.0861 0.8140 0.7120
-1.250 0.2446 0.01404 0.00815 -0.0853 0.8080 0.7217
-1.000 0.2746 0.01395 0.00799 -0.0853 0.8040 0.7305
-0.750 0.2981 0.01406 0.00810 -0.0844 0.7968 0.7401
-0.500 0.3254 0.01401 0.00803 -0.0839 0.7913 0.7490
-0.250 0.3549 0.01395 0.00791 -0.0839 0.7871 0.7596
0.000 0.3775 0.01401 0.00801 -0.0828 0.7791 0.7678
0.250 0.4078 0.01383 0.00776 -0.0829 0.7737 0.7757
0.500 0.4322 0.01376 0.00770 -0.0820 0.7648 0.7824
0.750 0.4629 0.01352 0.00738 -0.0822 0.7580 0.7901
1.000 0.4870 0.01346 0.00735 -0.0813 0.7491 0.7966
1.250 0.5168 0.01333 0.00715 -0.0815 0.7430 0.8050
1.500 0.5409 0.01329 0.00716 -0.0806 0.7349 0.8123
1.750 0.5698 0.01317 0.00700 -0.0806 0.7282 0.8210
2.000 0.5942 0.01311 0.00699 -0.0798 0.7196 0.8291
2.250 0.6226 0.01297 0.00681 -0.0796 0.7124 0.8381
2.500 0.6466 0.01290 0.00680 -0.0787 0.7026 0.8483
2.750 0.6739 0.01273 0.00661 -0.0783 0.6943 0.8577
3.000 0.6980 0.01261 0.00652 -0.0773 0.6835 0.8689
3.250 0.7219 0.01250 0.00646 -0.0763 0.6727 0.8816
3.500 0.7478 0.01237 0.00633 -0.0756 0.6628 0.8954
3.750 0.7727 0.01225 0.00625 -0.0748 0.6515 0.9111
4.000 0.8006 0.01217 0.00625 -0.0746 0.6390 0.9310
4.250 0.8376 0.01213 0.00624 -0.0765 0.6251 0.9573
4.500 0.8792 0.01212 0.00625 -0.0795 0.6093 1.0000
4.750 0.9044 0.01219 0.00627 -0.0794 0.5935 1.0000
5.000 0.9298 0.01230 0.00631 -0.0792 0.5763 1.0000
5.250 0.9545 0.01245 0.00639 -0.0788 0.5578 1.0000
5.500 0.9774 0.01265 0.00654 -0.0780 0.5364 1.0000
5.750 0.9997 0.01290 0.00668 -0.0770 0.5140 1.0000
6.000 1.0206 0.01320 0.00690 -0.0759 0.4895 1.0000
6.250 1.0403 0.01358 0.00716 -0.0745 0.4645 1.0000
6.500 1.0586 0.01402 0.00748 -0.0729 0.4385 1.0000
6.750 1.0761 0.01451 0.00785 -0.0713 0.4131 1.0000
7.000 1.0926 0.01506 0.00826 -0.0695 0.3897 1.0000
7.250 1.1088 0.01559 0.00872 -0.0677 0.3668 1.0000
7.500 1.1239 0.01618 0.00919 -0.0657 0.3466 1.0000
7.750 1.1386 0.01678 0.00970 -0.0637 0.3281 1.0000
8.000 1.1520 0.01737 0.01023 -0.0614 0.3112 1.0000
8.250 1.1646 0.01801 0.01081 -0.0591 0.2960 1.0000
8.500 1.1774 0.01869 0.01142 -0.0570 0.2820 1.0000
8.750 1.1902 0.01941 0.01206 -0.0548 0.2689 1.0000
9.000 1.2034 0.02006 0.01272 -0.0528 0.2560 1.0000
9.250 1.2163 0.02074 0.01341 -0.0509 0.2435 1.0000
9.500 1.2289 0.02146 0.01415 -0.0490 0.2322 1.0000
9.750 1.2406 0.02227 0.01491 -0.0471 0.2217 1.0000
10.000 1.2525 0.02304 0.01571 -0.0452 0.2113 1.0000
10.250 1.2650 0.02385 0.01657 -0.0436 0.2016 1.0000
10.500 1.2756 0.02482 0.01749 -0.0418 0.1928 1.0000
10.750 1.2864 0.02572 0.01845 -0.0401 0.1832 1.0000
11.000 1.2966 0.02673 0.01952 -0.0385 0.1738 1.0000
11.250 1.3042 0.02792 0.02065 -0.0367 0.1646 1.0000
11.500 1.3138 0.02898 0.02181 -0.0352 0.1553 1.0000
11.750 1.3218 0.03024 0.02309 -0.0337 0.1465 1.0000
12.000 1.3276 0.03165 0.02448 -0.0322 0.1379 1.0000
12.250 1.3362 0.03293 0.02587 -0.0310 0.1288 1.0000
12.500 1.3414 0.03452 0.02748 -0.0296 0.1210 1.0000
12.750 1.3473 0.03610 0.02911 -0.0285 0.1129 1.0000
13.000 1.3527 0.03781 0.03088 -0.0274 0.1057 1.0000
13.250 1.3563 0.03970 0.03278 -0.0263 0.0991 1.0000
13.500 1.3610 0.04160 0.03476 -0.0254 0.0931 1.0000
13.750 1.3641 0.04367 0.03687 -0.0246 0.0874 1.0000
14.000 1.3661 0.04594 0.03918 -0.0239 0.0829 1.0000
14.250 1.3706 0.04804 0.04140 -0.0234 0.0780 1.0000
14.500 1.3705 0.05064 0.04401 -0.0229 0.0743 1.0000
14.750 1.3725 0.05313 0.04661 -0.0225 0.0709 1.0000
15.000 1.3756 0.05561 0.04922 -0.0224 0.0673 1.0000
15.250 1.3759 0.05841 0.05210 -0.0224 0.0643 1.0000
15.500 1.3726 0.06171 0.05538 -0.0224 0.0614 1.0000
15.750 1.3752 0.06448 0.05834 -0.0226 0.0591 1.0000
16.000 1.3755 0.06761 0.06162 -0.0231 0.0563 1.0000
16.250 1.3734 0.07110 0.06521 -0.0239 0.0538 1.0000
16.500 1.3670 0.07520 0.06931 -0.0248 0.0511 1.0000
16.750 1.3659 0.07885 0.07316 -0.0258 0.0490 1.0000
17.000 1.3623 0.08297 0.07744 -0.0272 0.0463 1.0000
17.250 1.3563 0.08750 0.08207 -0.0289 0.0440 1.0000
17.500 1.3464 0.09260 0.08718 -0.0307 0.0418 1.0000
17.750 1.3404 0.09749 0.09231 -0.0328 0.0394 1.0000
18.000 1.3305 0.10319 0.09817 -0.0355 0.0364 1.0000
18.250 1.3172 0.10939 0.10441 -0.0385 0.0343 1.0000
18.500 1.3063 0.11537 0.11054 -0.0414 0.0320 1.0000
18.750 1.2946 0.12169 0.11700 -0.0447 0.0297 1.0000
19.000 1.2821 0.12815 0.12353 -0.0482 0.0280 1.0000
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