HQ 3.5/14 AIRFOIL (hq3514-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/14 AIRFOIL (hq3514-il) Reynolds number: 50,000 Max Cl/Cd: 29.41 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3514-il-50000.txt Download as CSV file: xf-hq3514-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/14 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3405 0.11648 0.10996 -0.0296 1.0000 0.3032
-9.250 -0.3133 0.11136 0.10481 -0.0277 1.0000 0.3141
-9.000 -0.3311 0.11038 0.10396 -0.0252 1.0000 0.3221
-8.750 -0.3369 0.10907 0.10272 -0.0223 1.0000 0.3342
-8.500 -0.3302 0.10625 0.09994 -0.0199 1.0000 0.3456
-8.250 -0.3409 0.10487 0.09865 -0.0170 1.0000 0.3568
-8.000 -0.3749 0.10580 0.09975 -0.0131 1.0000 0.3682
-7.750 -0.3706 0.10341 0.09740 -0.0104 1.0000 0.3833
-7.500 -0.3628 0.10072 0.09473 -0.0080 1.0000 0.3970
-7.250 -0.3608 0.09846 0.09251 -0.0056 1.0000 0.4093
-7.000 -0.3649 0.09682 0.09093 -0.0027 1.0000 0.4243
-6.750 -0.3704 0.09537 0.08952 0.0004 1.0000 0.4411
-6.500 -0.3781 0.09404 0.08827 0.0037 1.0000 0.4582
-6.000 -0.5711 0.06292 0.05670 -0.0354 1.0000 0.1789
-5.750 -0.5598 0.05754 0.05090 -0.0378 1.0000 0.1707
-5.500 -0.5437 0.05174 0.04441 -0.0411 1.0000 0.1639
-5.250 -0.5218 0.04753 0.03939 -0.0430 1.0000 0.1596
-5.000 -0.4995 0.04451 0.03569 -0.0440 1.0000 0.1608
-4.750 -0.4803 0.04224 0.03344 -0.0437 1.0000 0.1647
-4.500 -0.4577 0.04009 0.03093 -0.0438 1.0000 0.1669
-4.250 -0.4345 0.03837 0.02881 -0.0438 1.0000 0.1718
-4.000 -0.4110 0.03679 0.02684 -0.0437 1.0000 0.1778
-3.750 -0.3892 0.03550 0.02546 -0.0432 1.0000 0.1837
-3.500 -0.3662 0.03448 0.02412 -0.0429 1.0000 0.1930
-3.250 -0.3449 0.03354 0.02319 -0.0421 1.0000 0.2033
-3.000 -0.3235 0.03269 0.02234 -0.0413 1.0000 0.2151
-2.750 -0.3025 0.03199 0.02169 -0.0405 1.0000 0.2323
-2.500 -0.2813 0.03139 0.02112 -0.0396 1.0000 0.2538
-2.250 -0.2586 0.03063 0.02066 -0.0394 1.0000 0.2938
-2.000 -0.2414 0.02917 0.02133 -0.0366 1.0000 0.5638
-1.750 -0.2473 0.03013 0.02260 -0.0270 1.0000 0.7172
-1.500 -0.2488 0.03056 0.02304 -0.0195 1.0000 0.7773
-1.250 -0.2482 0.03069 0.02313 -0.0132 1.0000 0.8256
-1.000 -0.2450 0.03063 0.02305 -0.0077 1.0000 0.8705
-0.750 -0.2275 0.03065 0.02309 -0.0050 1.0000 0.9338
-0.500 -0.1736 0.03124 0.02347 -0.0119 1.0000 1.0000
-0.250 -0.1614 0.03123 0.02326 -0.0122 1.0000 1.0000
0.000 -0.1430 0.03156 0.02340 -0.0136 1.0000 1.0000
0.250 -0.0778 0.03390 0.02537 -0.0232 0.9793 1.0000
0.500 -0.0333 0.03535 0.02657 -0.0289 0.9646 1.0000
0.750 0.0087 0.03674 0.02775 -0.0338 0.9502 1.0000
1.000 0.0487 0.03813 0.02893 -0.0383 0.9371 1.0000
1.250 0.0895 0.03961 0.03023 -0.0427 0.9243 1.0000
1.500 0.1266 0.04078 0.03123 -0.0461 0.9076 1.0000
1.750 0.1660 0.04184 0.03215 -0.0496 0.8868 1.0000
2.000 0.2169 0.04309 0.03324 -0.0542 0.8657 1.0000
2.250 0.2590 0.04418 0.03421 -0.0575 0.8479 1.0000
2.500 0.2949 0.04520 0.03514 -0.0599 0.8325 1.0000
2.750 0.3252 0.04616 0.03603 -0.0614 0.8179 1.0000
3.000 0.3528 0.04712 0.03693 -0.0625 0.8032 1.0000
3.250 0.3806 0.04810 0.03787 -0.0636 0.7886 1.0000
3.500 0.4085 0.04908 0.03882 -0.0646 0.7739 1.0000
3.750 0.4366 0.05007 0.03978 -0.0655 0.7590 1.0000
4.000 0.4641 0.05106 0.04076 -0.0663 0.7441 1.0000
4.250 0.4924 0.05201 0.04172 -0.0670 0.7287 1.0000
4.500 0.5207 0.05294 0.04266 -0.0676 0.7131 1.0000
4.750 0.5472 0.05393 0.04367 -0.0681 0.6977 1.0000
5.000 0.5738 0.05489 0.04467 -0.0684 0.6820 1.0000
5.250 0.6001 0.05582 0.04563 -0.0687 0.6663 1.0000
5.500 0.6255 0.05676 0.04662 -0.0688 0.6507 1.0000
5.750 0.6571 0.05710 0.04702 -0.0688 0.6339 1.0000
6.000 0.6938 0.05685 0.04683 -0.0688 0.6169 1.0000
6.250 0.7317 0.05629 0.04636 -0.0686 0.6004 1.0000
6.500 0.7634 0.05613 0.04628 -0.0681 0.5847 1.0000
6.750 0.7923 0.05610 0.04634 -0.0675 0.5694 1.0000
7.000 0.8213 0.05599 0.04635 -0.0667 0.5543 1.0000
7.250 0.8510 0.05569 0.04614 -0.0657 0.5394 1.0000
7.500 0.8837 0.05491 0.04549 -0.0646 0.5247 1.0000
7.750 0.9204 0.05355 0.04427 -0.0634 0.5105 1.0000
8.000 0.9800 0.04991 0.04080 -0.0626 0.4971 1.0000
8.250 1.0963 0.04274 0.03385 -0.0662 0.4797 1.0000
8.500 1.1748 0.03995 0.03106 -0.0694 0.4565 1.0000
8.750 1.1948 0.04101 0.03217 -0.0681 0.4369 1.0000
9.000 1.2196 0.04201 0.03320 -0.0673 0.4184 1.0000
9.250 1.2401 0.04330 0.03457 -0.0663 0.4018 1.0000
9.500 1.2549 0.04498 0.03634 -0.0648 0.3877 1.0000
9.750 1.2734 0.04658 0.03802 -0.0638 0.3753 1.0000
10.000 1.3012 0.04768 0.03917 -0.0636 0.3626 1.0000
10.250 1.2711 0.05150 0.04325 -0.0584 0.3556 1.0000
10.500 1.2902 0.05313 0.04498 -0.0576 0.3456 1.0000
10.750 1.2226 0.05970 0.05171 -0.0511 0.3434 1.0000
11.000 0.9487 0.09820 0.08975 -0.0580 0.3477 1.0000
11.250 0.8995 0.11008 0.10157 -0.0623 0.3462 1.0000
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Polar data table (+)
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