HQ 2.5/10 AIRFOIL (hq2510-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.5/10 AIRFOIL (hq2510-il) Reynolds number: 100,000 Max Cl/Cd: 55.92 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2510-il-100000-n5.txt Download as CSV file: xf-hq2510-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/10 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4083 0.08885 0.08402 -0.0385 1.0000 0.0213
-8.750 -0.4192 0.08206 0.07736 -0.0425 1.0000 0.0199
-8.250 -0.4314 0.07222 0.06765 -0.0478 1.0000 0.0191
-8.000 -0.4453 0.06840 0.06390 -0.0490 1.0000 0.0189
-7.750 -0.4572 0.06460 0.06012 -0.0498 1.0000 0.0188
-7.500 -0.4693 0.06110 0.05660 -0.0494 1.0000 0.0187
-7.250 -0.4799 0.05777 0.05321 -0.0483 1.0000 0.0185
-7.000 -0.4884 0.05422 0.04953 -0.0472 1.0000 0.0185
-6.750 -0.4857 0.04963 0.04469 -0.0482 0.9978 0.0184
-6.500 -0.4636 0.04347 0.03801 -0.0528 0.9907 0.0184
-6.250 -0.4372 0.03802 0.03191 -0.0564 0.9849 0.0187
-6.000 -0.4124 0.03392 0.02729 -0.0586 0.9785 0.0201
-5.750 -0.3816 0.03211 0.02524 -0.0610 0.9737 0.0225
-5.500 -0.3524 0.02919 0.02181 -0.0622 0.9682 0.0240
-5.250 -0.3216 0.02634 0.01841 -0.0631 0.9632 0.0254
-5.000 -0.2875 0.02403 0.01559 -0.0643 0.9596 0.0275
-4.750 -0.2583 0.02233 0.01366 -0.0648 0.9540 0.0310
-4.500 -0.2264 0.02133 0.01254 -0.0659 0.9490 0.0376
-4.250 -0.1923 0.01988 0.01100 -0.0673 0.9455 0.0449
-4.000 -0.1640 0.01912 0.01018 -0.0677 0.9390 0.0580
-3.750 -0.1312 0.01839 0.00941 -0.0689 0.9342 0.0744
-3.500 -0.0984 0.01771 0.00863 -0.0701 0.9297 0.0920
-3.250 -0.0704 0.01706 0.00799 -0.0704 0.9229 0.1113
-3.000 -0.0372 0.01626 0.00739 -0.0718 0.9186 0.1643
-2.750 -0.0134 0.01497 0.00706 -0.0720 0.9117 0.3785
-2.500 0.0136 0.01446 0.00718 -0.0716 0.9063 0.5720
-2.250 0.0408 0.01441 0.00717 -0.0709 0.9002 0.6420
-2.000 0.0676 0.01441 0.00717 -0.0702 0.8936 0.6898
-1.750 0.0937 0.01441 0.00721 -0.0690 0.8881 0.7407
-1.500 0.1156 0.01442 0.00724 -0.0670 0.8804 0.7805
-1.250 0.1441 0.01434 0.00707 -0.0665 0.8751 0.8064
-1.000 0.1692 0.01428 0.00696 -0.0657 0.8670 0.8228
-0.750 0.2008 0.01416 0.00674 -0.0661 0.8616 0.8363
-0.500 0.2266 0.01410 0.00664 -0.0656 0.8530 0.8507
-0.250 0.2569 0.01398 0.00645 -0.0657 0.8467 0.8655
0.000 0.2848 0.01390 0.00636 -0.0655 0.8383 0.8823
0.250 0.3165 0.01381 0.00624 -0.0661 0.8311 0.9015
0.500 0.3527 0.01371 0.00613 -0.0676 0.8236 0.9228
0.750 0.3922 0.01364 0.00605 -0.0700 0.8158 0.9516
1.000 0.4340 0.01352 0.00589 -0.0728 0.8078 1.0000
1.250 0.4598 0.01351 0.00582 -0.0724 0.7952 1.0000
1.500 0.4864 0.01347 0.00571 -0.0721 0.7818 1.0000
1.750 0.5131 0.01347 0.00565 -0.0718 0.7687 1.0000
2.000 0.5398 0.01352 0.00567 -0.0715 0.7567 1.0000
2.250 0.5667 0.01357 0.00573 -0.0712 0.7446 1.0000
2.500 0.5936 0.01362 0.00576 -0.0709 0.7316 1.0000
2.750 0.6202 0.01367 0.00580 -0.0705 0.7172 1.0000
3.000 0.6466 0.01373 0.00585 -0.0700 0.7015 1.0000
3.250 0.6732 0.01379 0.00593 -0.0696 0.6847 1.0000
3.500 0.6991 0.01388 0.00603 -0.0690 0.6660 1.0000
3.750 0.7246 0.01399 0.00614 -0.0683 0.6453 1.0000
4.000 0.7498 0.01411 0.00627 -0.0676 0.6219 1.0000
4.250 0.7745 0.01427 0.00640 -0.0668 0.5945 1.0000
4.500 0.7987 0.01447 0.00660 -0.0659 0.5625 1.0000
4.750 0.8222 0.01474 0.00678 -0.0649 0.5258 1.0000
5.000 0.8449 0.01511 0.00702 -0.0638 0.4858 1.0000
5.250 0.8666 0.01558 0.00734 -0.0627 0.4448 1.0000
5.500 0.8875 0.01614 0.00775 -0.0615 0.4048 1.0000
5.750 0.9081 0.01676 0.00829 -0.0603 0.3665 1.0000
6.000 0.9284 0.01741 0.00883 -0.0592 0.3314 1.0000
6.250 0.9484 0.01811 0.00943 -0.0581 0.3003 1.0000
6.500 0.9686 0.01881 0.01007 -0.0570 0.2739 1.0000
6.750 0.9887 0.01952 0.01076 -0.0559 0.2509 1.0000
7.000 1.0090 0.02022 0.01150 -0.0549 0.2295 1.0000
7.250 1.0283 0.02097 0.01223 -0.0538 0.2047 1.0000
7.500 1.0466 0.02176 0.01303 -0.0526 0.1771 1.0000
7.750 1.0649 0.02258 0.01384 -0.0514 0.1563 1.0000
8.000 1.0835 0.02339 0.01469 -0.0502 0.1357 1.0000
8.250 1.0977 0.02456 0.01554 -0.0489 0.0920 1.0000
8.500 1.1091 0.02617 0.01676 -0.0472 0.0435 1.0000
8.750 1.1186 0.02800 0.01840 -0.0450 0.0226 1.0000
9.000 1.1303 0.02950 0.02004 -0.0430 0.0181 1.0000
9.250 1.1384 0.03114 0.02181 -0.0406 0.0158 1.0000
9.500 1.1430 0.03292 0.02376 -0.0378 0.0145 1.0000
9.750 1.1489 0.03454 0.02560 -0.0353 0.0139 1.0000
10.000 1.1532 0.03631 0.02759 -0.0330 0.0135 1.0000
10.250 1.1554 0.03832 0.02989 -0.0307 0.0129 1.0000
10.500 1.1573 0.04043 0.03222 -0.0286 0.0126 1.0000
10.750 1.1589 0.04269 0.03469 -0.0268 0.0123 1.0000
11.000 1.1595 0.04521 0.03740 -0.0252 0.0119 1.0000
11.250 1.1600 0.04783 0.04022 -0.0239 0.0116 1.0000
11.500 1.1597 0.05062 0.04323 -0.0229 0.0112 1.0000
11.750 1.1576 0.05362 0.04640 -0.0222 0.0106 1.0000
12.000 1.1550 0.05686 0.04986 -0.0218 0.0104 1.0000
12.250 1.1499 0.06046 0.05364 -0.0219 0.0101 1.0000
12.500 1.1428 0.06447 0.05784 -0.0224 0.0097 1.0000
12.750 1.1339 0.06895 0.06251 -0.0234 0.0095 1.0000
13.000 1.1234 0.07395 0.06770 -0.0249 0.0093 1.0000
13.250 1.1151 0.07895 0.07293 -0.0266 0.0094 1.0000
13.500 1.1011 0.08506 0.07924 -0.0294 0.0092 1.0000
13.750 1.0873 0.09161 0.08599 -0.0327 0.0091 1.0000
14.000 1.0737 0.09862 0.09320 -0.0367 0.0091 1.0000
14.250 1.0615 0.10593 0.10072 -0.0410 0.0093 1.0000
14.500 1.0460 0.11433 0.10930 -0.0461 0.0093 1.0000
14.750 1.0296 0.12384 0.11903 -0.0519 0.0097 1.0000
15.000 0.9996 0.13834 0.13382 -0.0604 0.0108 1.0000
15.250 0.9737 0.15241 0.14800 -0.0682 0.0118 1.0000
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