HQ 3.0/12 AIRFOIL (hq3012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/12 AIRFOIL (hq3012-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.12 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3012-il-1000000.txt Download as CSV file: xf-hq3012-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/12 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.6548 0.04623 0.04430 -0.0750 1.0000 0.0072
-11.250 -0.6932 0.03997 0.03787 -0.0776 1.0000 0.0071
-11.000 -0.7119 0.03394 0.03153 -0.0835 0.9932 0.0071
-10.750 -0.7020 0.02886 0.02601 -0.0884 0.9858 0.0071
-10.500 -0.6790 0.02562 0.02243 -0.0919 0.9828 0.0072
-10.250 -0.6570 0.02337 0.01992 -0.0935 0.9764 0.0073
-10.000 -0.6298 0.02161 0.01793 -0.0954 0.9717 0.0075
-9.750 -0.6046 0.02031 0.01645 -0.0961 0.9644 0.0078
-9.500 -0.5795 0.01911 0.01506 -0.0967 0.9566 0.0080
-9.250 -0.5580 0.01809 0.01388 -0.0962 0.9464 0.0081
-9.000 -0.5352 0.01724 0.01287 -0.0958 0.9374 0.0082
-8.750 -0.5194 0.01521 0.01054 -0.0946 0.9267 0.0086
-8.500 -0.4983 0.01421 0.00940 -0.0938 0.9174 0.0090
-8.250 -0.4746 0.01360 0.00870 -0.0933 0.9097 0.0093
-8.000 -0.4504 0.01306 0.00808 -0.0929 0.9017 0.0096
-7.750 -0.4259 0.01255 0.00746 -0.0924 0.8945 0.0099
-7.500 -0.4010 0.01206 0.00689 -0.0920 0.8869 0.0103
-7.250 -0.3758 0.01160 0.00633 -0.0916 0.8803 0.0107
-7.000 -0.3501 0.01120 0.00584 -0.0913 0.8732 0.0110
-6.750 -0.3248 0.01071 0.00525 -0.0909 0.8668 0.0115
-6.500 -0.2994 0.01018 0.00467 -0.0906 0.8600 0.0127
-6.250 -0.2729 0.00990 0.00433 -0.0904 0.8538 0.0139
-6.000 -0.2461 0.00963 0.00401 -0.0903 0.8475 0.0151
-5.750 -0.2196 0.00927 0.00363 -0.0900 0.8411 0.0184
-5.500 -0.1927 0.00902 0.00338 -0.0899 0.8352 0.0248
-5.250 -0.1653 0.00883 0.00321 -0.0898 0.8289 0.0314
-5.000 -0.1378 0.00871 0.00303 -0.0898 0.8231 0.0349
-4.750 -0.1102 0.00851 0.00286 -0.0898 0.8170 0.0391
-4.500 -0.0825 0.00843 0.00273 -0.0897 0.8109 0.0420
-4.250 -0.0549 0.00824 0.00252 -0.0897 0.8050 0.0466
-4.000 -0.0272 0.00809 0.00237 -0.0897 0.7986 0.0516
-3.750 0.0005 0.00797 0.00220 -0.0896 0.7927 0.0568
-3.500 0.0282 0.00779 0.00205 -0.0896 0.7857 0.0662
-3.250 0.0556 0.00763 0.00189 -0.0895 0.7787 0.0815
-3.000 0.0831 0.00739 0.00175 -0.0895 0.7716 0.1108
-2.750 0.1098 0.00705 0.00159 -0.0895 0.7652 0.1760
-2.500 0.1368 0.00667 0.00147 -0.0896 0.7591 0.2581
-2.250 0.1628 0.00613 0.00131 -0.0896 0.7530 0.3866
-2.000 0.1897 0.00583 0.00127 -0.0895 0.7473 0.4815
-1.750 0.2176 0.00572 0.00124 -0.0895 0.7407 0.5227
-1.500 0.2454 0.00568 0.00122 -0.0895 0.7337 0.5521
-1.250 0.2733 0.00564 0.00122 -0.0894 0.7254 0.5762
-1.000 0.3013 0.00564 0.00122 -0.0894 0.7178 0.5967
-0.750 0.3295 0.00564 0.00121 -0.0893 0.7101 0.6113
-0.500 0.3575 0.00566 0.00122 -0.0893 0.7036 0.6238
-0.250 0.3857 0.00567 0.00125 -0.0893 0.6963 0.6437
0.000 0.4135 0.00570 0.00127 -0.0892 0.6896 0.6565
0.250 0.4418 0.00571 0.00128 -0.0892 0.6819 0.6643
0.500 0.4697 0.00576 0.00130 -0.0892 0.6739 0.6734
0.750 0.4973 0.00579 0.00133 -0.0891 0.6636 0.6833
1.000 0.5252 0.00582 0.00135 -0.0891 0.6538 0.6919
1.250 0.5528 0.00587 0.00139 -0.0890 0.6447 0.6989
1.500 0.5808 0.00592 0.00142 -0.0890 0.6353 0.7053
1.750 0.6085 0.00596 0.00146 -0.0889 0.6253 0.7117
2.000 0.6360 0.00603 0.00150 -0.0888 0.6134 0.7190
2.250 0.6631 0.00609 0.00156 -0.0886 0.6005 0.7257
2.500 0.6902 0.00619 0.00162 -0.0885 0.5849 0.7332
2.750 0.7168 0.00628 0.00169 -0.0882 0.5669 0.7403
3.000 0.7429 0.00644 0.00178 -0.0879 0.5459 0.7485
3.250 0.7688 0.00658 0.00188 -0.0875 0.5237 0.7564
3.500 0.7941 0.00678 0.00200 -0.0871 0.4980 0.7651
3.750 0.8187 0.00702 0.00215 -0.0865 0.4688 0.7743
4.000 0.8432 0.00726 0.00231 -0.0860 0.4415 0.7838
4.250 0.8677 0.00751 0.00249 -0.0854 0.4144 0.7945
4.500 0.8916 0.00778 0.00268 -0.0848 0.3864 0.8063
4.750 0.9156 0.00802 0.00287 -0.0841 0.3609 0.8196
5.000 0.9388 0.00830 0.00308 -0.0833 0.3333 0.8353
5.250 0.9611 0.00856 0.00330 -0.0824 0.3078 0.8566
5.500 0.9813 0.00869 0.00351 -0.0809 0.2870 0.9071
5.750 1.0129 0.00896 0.00376 -0.0820 0.2650 1.0000
6.000 1.0368 0.00928 0.00400 -0.0814 0.2450 1.0000
6.250 1.0605 0.00960 0.00424 -0.0808 0.2271 1.0000
6.500 1.0834 0.00996 0.00450 -0.0801 0.2084 1.0000
6.750 1.1064 0.01031 0.00477 -0.0794 0.1907 1.0000
7.000 1.1280 0.01074 0.00509 -0.0785 0.1695 1.0000
7.250 1.1503 0.01111 0.00538 -0.0777 0.1554 1.0000
7.500 1.1729 0.01144 0.00568 -0.0769 0.1440 1.0000
7.750 1.1948 0.01180 0.00599 -0.0761 0.1321 1.0000
8.000 1.2161 0.01219 0.00633 -0.0751 0.1201 1.0000
8.250 1.2367 0.01260 0.00669 -0.0740 0.1077 1.0000
8.500 1.2560 0.01308 0.00708 -0.0728 0.0936 1.0000
8.750 1.2739 0.01361 0.00752 -0.0713 0.0790 1.0000
9.000 1.2906 0.01416 0.00800 -0.0696 0.0657 1.0000
9.250 1.3048 0.01473 0.00850 -0.0674 0.0541 1.0000
9.500 1.3196 0.01524 0.00898 -0.0654 0.0463 1.0000
9.750 1.3334 0.01581 0.00951 -0.0632 0.0390 1.0000
10.000 1.3462 0.01644 0.01011 -0.0610 0.0318 1.0000
10.250 1.3607 0.01701 0.01066 -0.0591 0.0273 1.0000
10.500 1.3734 0.01769 0.01133 -0.0570 0.0215 1.0000
10.750 1.3835 0.01854 0.01213 -0.0546 0.0149 1.0000
11.000 1.3904 0.01962 0.01316 -0.0520 0.0071 1.0000
11.250 1.4005 0.02054 0.01410 -0.0498 0.0055 1.0000
11.500 1.4125 0.02136 0.01497 -0.0480 0.0050 1.0000
11.750 1.4237 0.02225 0.01594 -0.0462 0.0047 1.0000
12.000 1.4340 0.02323 0.01699 -0.0444 0.0044 1.0000
12.250 1.4441 0.02426 0.01808 -0.0427 0.0043 1.0000
12.500 1.4531 0.02540 0.01929 -0.0409 0.0041 1.0000
12.750 1.4598 0.02675 0.02072 -0.0391 0.0039 1.0000
13.000 1.4627 0.02846 0.02255 -0.0371 0.0036 1.0000
13.250 1.4681 0.03001 0.02420 -0.0355 0.0035 1.0000
13.500 1.4745 0.03154 0.02581 -0.0342 0.0035 1.0000
13.750 1.4795 0.03323 0.02759 -0.0329 0.0034 1.0000
14.000 1.4831 0.03511 0.02956 -0.0316 0.0034 1.0000
14.250 1.4856 0.03716 0.03171 -0.0305 0.0034 1.0000
14.500 1.4877 0.03932 0.03397 -0.0296 0.0033 1.0000
14.750 1.4879 0.04176 0.03651 -0.0288 0.0033 1.0000
15.000 1.4875 0.04438 0.03923 -0.0282 0.0033 1.0000
15.250 1.4856 0.04728 0.04223 -0.0279 0.0032 1.0000
15.500 1.4813 0.05059 0.04567 -0.0277 0.0032 1.0000
15.750 1.4775 0.05402 0.04920 -0.0279 0.0032 1.0000
16.000 1.4724 0.05778 0.05310 -0.0283 0.0031 1.0000
16.250 1.4650 0.06202 0.05746 -0.0291 0.0031 1.0000
16.500 1.4587 0.06631 0.06186 -0.0302 0.0031 1.0000
16.750 1.4491 0.07130 0.06698 -0.0318 0.0031 1.0000
17.000 1.4364 0.07702 0.07284 -0.0338 0.0031 1.0000
17.250 1.4243 0.08289 0.07885 -0.0362 0.0031 1.0000
17.500 1.4108 0.08924 0.08533 -0.0389 0.0031 1.0000
17.750 1.3964 0.09594 0.09217 -0.0420 0.0031 1.0000
18.000 1.3818 0.10289 0.09924 -0.0454 0.0031 1.0000
18.250 1.3663 0.11020 0.10669 -0.0491 0.0030 1.0000
18.500 1.3510 0.11759 0.11421 -0.0529 0.0030 1.0000
18.750 1.3354 0.12516 0.12190 -0.0570 0.0031 1.0000
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