HQ 3.0/14 AIRFOIL (hq3014-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: HQ 3.0/14 AIRFOIL (hq3014-il) Reynolds number: 50,000 Max Cl/Cd: 32.99 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3014-il-50000-n5.txt Download as CSV file: xf-hq3014-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3701 0.10661 0.09939 -0.0519 1.0000 0.0607
-10.750 -0.3771 0.10208 0.09495 -0.0533 1.0000 0.0609
-10.500 -0.3854 0.09750 0.09046 -0.0546 1.0000 0.0608
-10.250 -0.3976 0.09244 0.08552 -0.0563 1.0000 0.0608
-10.000 -0.4129 0.08709 0.08029 -0.0581 1.0000 0.0606
-9.750 -0.4358 0.08121 0.07453 -0.0602 1.0000 0.0600
-9.500 -0.4668 0.07636 0.06978 -0.0610 1.0000 0.0591
-9.250 -0.5035 0.07292 0.06642 -0.0596 1.0000 0.0581
-9.000 -0.5441 0.07040 0.06396 -0.0566 1.0000 0.0571
-8.750 -0.5788 0.06715 0.06066 -0.0540 1.0000 0.0563
-8.500 -0.6026 0.06410 0.05751 -0.0517 1.0000 0.0562
-8.250 -0.6185 0.06115 0.05440 -0.0496 1.0000 0.0567
-8.000 -0.6109 0.05659 0.04946 -0.0524 0.9932 0.0584
-7.750 -0.5995 0.05207 0.04436 -0.0549 0.9855 0.0614
-7.500 -0.5863 0.04743 0.03879 -0.0569 0.9781 0.0647
-7.250 -0.5622 0.04518 0.03655 -0.0583 0.9725 0.0682
-7.000 -0.5386 0.04294 0.03396 -0.0595 0.9667 0.0732
-6.750 -0.5153 0.04025 0.03060 -0.0603 0.9605 0.0781
-6.500 -0.4855 0.03865 0.02896 -0.0619 0.9560 0.0837
-6.250 -0.4619 0.03699 0.02687 -0.0619 0.9496 0.0892
-6.000 -0.4336 0.03552 0.02527 -0.0627 0.9445 0.0952
-5.750 -0.4011 0.03421 0.02374 -0.0638 0.9404 0.1009
-5.500 -0.3778 0.03318 0.02253 -0.0632 0.9337 0.1073
-5.250 -0.3482 0.03228 0.02157 -0.0639 0.9288 0.1156
-5.000 -0.3187 0.03141 0.02060 -0.0642 0.9241 0.1233
-4.750 -0.2957 0.03074 0.01985 -0.0637 0.9174 0.1340
-4.500 -0.2657 0.02997 0.01910 -0.0646 0.9126 0.1487
-4.250 -0.2427 0.02928 0.01846 -0.0643 0.9064 0.1668
-4.000 -0.2173 0.02848 0.01780 -0.0647 0.9003 0.1967
-3.750 -0.1863 0.02729 0.01704 -0.0664 0.8961 0.2651
-3.500 -0.1728 0.02639 0.01703 -0.0646 0.8886 0.3851
-3.250 -0.1491 0.02648 0.01753 -0.0630 0.8829 0.5281
-3.000 -0.1280 0.02685 0.01789 -0.0611 0.8765 0.5922
-2.750 -0.1075 0.02726 0.01823 -0.0589 0.8696 0.6384
-2.500 -0.0801 0.02770 0.01859 -0.0575 0.8651 0.6822
-2.250 -0.0702 0.02809 0.01895 -0.0535 0.8562 0.7130
-2.000 -0.0452 0.02835 0.01912 -0.0518 0.8511 0.7434
-1.750 -0.0302 0.02854 0.01923 -0.0491 0.8433 0.7634
-1.500 -0.0060 0.02861 0.01918 -0.0478 0.8372 0.7850
-1.250 0.0157 0.02867 0.01914 -0.0462 0.8309 0.8061
-1.000 0.0352 0.02870 0.01909 -0.0445 0.8233 0.8237
-0.750 0.0700 0.02861 0.01886 -0.0455 0.8189 0.8383
-0.500 0.0850 0.02871 0.01888 -0.0439 0.8094 0.8507
-0.250 0.1210 0.02862 0.01869 -0.0453 0.8045 0.8616
0.000 0.1409 0.02875 0.01875 -0.0445 0.7957 0.8741
0.250 0.1769 0.02871 0.01863 -0.0461 0.7902 0.8863
0.500 0.2044 0.02885 0.01874 -0.0466 0.7822 0.9001
0.750 0.2431 0.02889 0.01873 -0.0488 0.7759 0.9137
1.000 0.2875 0.02892 0.01871 -0.0521 0.7705 0.9276
1.250 0.3249 0.02916 0.01893 -0.0547 0.7618 0.9456
1.500 0.3784 0.02902 0.01875 -0.0595 0.7575 0.9625
1.750 0.4081 0.02936 0.01908 -0.0613 0.7466 1.0000
2.000 0.4335 0.02937 0.01902 -0.0614 0.7390 1.0000
2.500 0.4776 0.02970 0.01924 -0.0606 0.7181 1.0000
2.750 0.5188 0.02930 0.01879 -0.0623 0.7116 1.0000
3.000 0.5384 0.02957 0.01903 -0.0614 0.6990 1.0000
3.250 0.5620 0.02974 0.01919 -0.0610 0.6877 1.0000
3.500 0.6022 0.02932 0.01875 -0.0623 0.6810 1.0000
3.750 0.6217 0.02965 0.01908 -0.0613 0.6684 1.0000
4.000 0.6446 0.02987 0.01932 -0.0606 0.6566 1.0000
4.250 0.6793 0.02957 0.01903 -0.0612 0.6478 1.0000
4.500 0.7063 0.02956 0.01904 -0.0608 0.6363 1.0000
4.750 0.7283 0.02972 0.01926 -0.0598 0.6229 1.0000
5.000 0.7521 0.02978 0.01935 -0.0589 0.6096 1.0000
5.250 0.7774 0.02976 0.01936 -0.0582 0.5960 1.0000
5.500 0.8032 0.02967 0.01934 -0.0574 0.5819 1.0000
5.750 0.8285 0.02959 0.01930 -0.0566 0.5669 1.0000
6.000 0.8530 0.02955 0.01929 -0.0556 0.5512 1.0000
6.250 0.8772 0.02953 0.01933 -0.0546 0.5346 1.0000
6.500 0.9017 0.02952 0.01934 -0.0536 0.5175 1.0000
6.750 0.9271 0.02952 0.01934 -0.0527 0.4999 1.0000
7.000 0.9526 0.02956 0.01938 -0.0519 0.4818 1.0000
7.250 0.9700 0.03001 0.01985 -0.0503 0.4623 1.0000
7.500 0.9901 0.03040 0.02022 -0.0490 0.4430 1.0000
7.750 1.0110 0.03080 0.02058 -0.0478 0.4239 1.0000
8.000 1.0318 0.03128 0.02102 -0.0466 0.4059 1.0000
8.250 1.0468 0.03206 0.02180 -0.0450 0.3876 1.0000
8.500 1.0620 0.03289 0.02262 -0.0435 0.3703 1.0000
8.750 1.0775 0.03375 0.02349 -0.0421 0.3541 1.0000
9.000 1.0924 0.03467 0.02443 -0.0406 0.3385 1.0000
9.250 1.1075 0.03564 0.02540 -0.0393 0.3239 1.0000
9.500 1.1227 0.03664 0.02641 -0.0380 0.3101 1.0000
9.750 1.1378 0.03768 0.02744 -0.0367 0.2967 1.0000
10.000 1.1543 0.03870 0.02846 -0.0357 0.2841 1.0000
10.250 1.1644 0.04006 0.02995 -0.0342 0.2717 1.0000
10.500 1.1750 0.04143 0.03142 -0.0328 0.2599 1.0000
10.750 1.1872 0.04275 0.03280 -0.0316 0.2489 1.0000
11.000 1.2002 0.04397 0.03401 -0.0304 0.2380 1.0000
11.250 1.2046 0.04576 0.03599 -0.0289 0.2276 1.0000
11.500 1.2117 0.04745 0.03778 -0.0276 0.2180 1.0000
11.750 1.2222 0.04882 0.03916 -0.0265 0.2084 1.0000
12.000 1.2223 0.05108 0.04167 -0.0252 0.1995 1.0000
12.250 1.2284 0.05292 0.04357 -0.0241 0.1910 1.0000
12.500 1.2308 0.05503 0.04579 -0.0231 0.1825 1.0000
12.750 1.2316 0.05748 0.04840 -0.0222 0.1748 1.0000
13.000 1.2359 0.05956 0.05053 -0.0214 0.1672 1.0000
13.250 1.2322 0.06263 0.05380 -0.0209 0.1604 1.0000
13.500 1.2331 0.06515 0.05641 -0.0204 0.1536 1.0000
13.750 1.2300 0.06839 0.05981 -0.0201 0.1477 1.0000
14.000 1.2220 0.07225 0.06391 -0.0202 0.1421 1.0000
14.250 1.2285 0.07432 0.06596 -0.0199 0.1362 1.0000
14.500 1.2072 0.08028 0.07226 -0.0211 0.1323 1.0000
14.750 1.1946 0.08533 0.07750 -0.0223 0.1282 1.0000
15.000 1.2084 0.08657 0.07868 -0.0218 0.1230 1.0000
15.250 1.1731 0.09558 0.08804 -0.0253 0.1211 1.0000
15.500 1.1206 0.10881 0.10156 -0.0318 0.1196 1.0000
|
Polar data table (+)
Polar graphs
<< Back to HQ 3.0/14 AIRFOIL (hq3014-il)