HQ 3.0/14 AIRFOIL (hq3014-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/14 AIRFOIL (hq3014-il) Reynolds number: 200,000 Max Cl/Cd: 70.87 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3014-il-200000-n5.txt Download as CSV file: xf-hq3014-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.6582 0.05648 0.05216 -0.0796 1.0000 0.0149
-12.500 -0.6819 0.05072 0.04622 -0.0827 1.0000 0.0149
-12.250 -0.6990 0.04667 0.04204 -0.0839 1.0000 0.0150
-12.000 -0.7185 0.04303 0.03823 -0.0839 1.0000 0.0149
-11.750 -0.7335 0.04082 0.03595 -0.0823 1.0000 0.0150
-11.500 -0.7498 0.03902 0.03408 -0.0799 0.9987 0.0151
-11.250 -0.7370 0.03633 0.03119 -0.0833 0.9874 0.0154
-11.000 -0.7189 0.03420 0.02883 -0.0857 0.9790 0.0159
-10.750 -0.6981 0.03208 0.02647 -0.0879 0.9720 0.0165
-10.500 -0.6774 0.03015 0.02426 -0.0893 0.9647 0.0175
-10.250 -0.6548 0.02824 0.02207 -0.0907 0.9581 0.0184
-10.000 -0.6310 0.02708 0.02082 -0.0916 0.9512 0.0191
-9.750 -0.6063 0.02594 0.01956 -0.0925 0.9444 0.0200
-9.500 -0.5810 0.02468 0.01809 -0.0933 0.9384 0.0212
-9.250 -0.5580 0.02343 0.01662 -0.0933 0.9308 0.0227
-8.750 -0.5081 0.02179 0.01481 -0.0939 0.9178 0.0261
-8.500 -0.4819 0.02089 0.01375 -0.0942 0.9123 0.0287
-8.250 -0.4576 0.02039 0.01321 -0.0941 0.9054 0.0312
-8.000 -0.4319 0.01987 0.01253 -0.0941 0.8992 0.0345
-7.750 -0.4068 0.01929 0.01191 -0.0941 0.8936 0.0372
-7.500 -0.3828 0.01891 0.01145 -0.0937 0.8864 0.0404
-7.250 -0.3567 0.01844 0.01087 -0.0936 0.8812 0.0439
-7.000 -0.3329 0.01807 0.01048 -0.0932 0.8745 0.0474
-6.750 -0.3075 0.01773 0.01003 -0.0929 0.8686 0.0512
-6.500 -0.2825 0.01720 0.00941 -0.0926 0.8634 0.0543
-6.250 -0.2593 0.01671 0.00892 -0.0920 0.8568 0.0573
-6.000 -0.2339 0.01630 0.00842 -0.0917 0.8516 0.0608
-5.750 -0.2089 0.01592 0.00795 -0.0913 0.8460 0.0640
-5.500 -0.1852 0.01542 0.00744 -0.0908 0.8398 0.0675
-5.250 -0.1594 0.01502 0.00699 -0.0905 0.8351 0.0722
-5.000 -0.1342 0.01474 0.00662 -0.0901 0.8292 0.0774
-4.750 -0.1093 0.01435 0.00626 -0.0898 0.8234 0.0854
-4.500 -0.0828 0.01401 0.00589 -0.0896 0.8190 0.0959
-4.250 -0.0579 0.01370 0.00561 -0.0893 0.8129 0.1104
-4.000 -0.0323 0.01335 0.00532 -0.0890 0.8074 0.1342
-3.750 -0.0064 0.01290 0.00503 -0.0889 0.8031 0.1812
-3.500 0.0174 0.01245 0.00482 -0.0886 0.7967 0.2450
-3.250 0.0416 0.01188 0.00456 -0.0883 0.7913 0.3275
-3.000 0.0655 0.01138 0.00451 -0.0877 0.7867 0.4543
-2.750 0.0910 0.01128 0.00453 -0.0872 0.7804 0.5079
-2.500 0.1181 0.01123 0.00449 -0.0869 0.7751 0.5395
-2.250 0.1453 0.01122 0.00447 -0.0866 0.7698 0.5646
-2.000 0.1717 0.01123 0.00450 -0.0861 0.7633 0.5897
-1.750 0.1991 0.01127 0.00451 -0.0857 0.7581 0.6172
-1.500 0.2255 0.01131 0.00457 -0.0853 0.7519 0.6349
-1.250 0.2529 0.01132 0.00454 -0.0850 0.7459 0.6459
-1.000 0.2810 0.01133 0.00450 -0.0849 0.7411 0.6550
-0.750 0.3077 0.01136 0.00451 -0.0846 0.7344 0.6649
-0.500 0.3351 0.01138 0.00451 -0.0843 0.7289 0.6746
-0.250 0.3624 0.01140 0.00452 -0.0841 0.7231 0.6843
0.000 0.3895 0.01143 0.00453 -0.0839 0.7165 0.6926
0.250 0.4175 0.01142 0.00447 -0.0838 0.7102 0.6984
0.500 0.4438 0.01142 0.00447 -0.0834 0.7008 0.7041
0.750 0.4711 0.01143 0.00441 -0.0832 0.6912 0.7110
1.000 0.4979 0.01142 0.00439 -0.0828 0.6821 0.7166
1.250 0.5245 0.01145 0.00442 -0.0825 0.6733 0.7235
1.500 0.5519 0.01148 0.00442 -0.0823 0.6659 0.7297
1.750 0.5781 0.01152 0.00448 -0.0819 0.6570 0.7363
2.000 0.6052 0.01156 0.00449 -0.0817 0.6487 0.7436
2.250 0.6309 0.01160 0.00457 -0.0812 0.6387 0.7502
2.500 0.6572 0.01166 0.00462 -0.0809 0.6282 0.7581
2.750 0.6826 0.01170 0.00467 -0.0803 0.6166 0.7649
3.000 0.7081 0.01177 0.00472 -0.0798 0.6033 0.7734
3.250 0.7327 0.01183 0.00479 -0.0791 0.5893 0.7807
3.500 0.7577 0.01192 0.00487 -0.0785 0.5748 0.7896
3.750 0.7819 0.01201 0.00496 -0.0777 0.5594 0.7981
4.000 0.8057 0.01212 0.00507 -0.0769 0.5435 0.8076
4.250 0.8289 0.01226 0.00520 -0.0760 0.5258 0.8179
4.500 0.8512 0.01240 0.00533 -0.0749 0.5070 0.8288
4.750 0.8729 0.01259 0.00550 -0.0737 0.4864 0.8414
5.000 0.8938 0.01281 0.00568 -0.0724 0.4651 0.8562
5.250 0.9145 0.01303 0.00588 -0.0711 0.4433 0.8756
5.500 0.9367 0.01330 0.00614 -0.0701 0.4209 0.9078
5.750 0.9660 0.01363 0.00644 -0.0709 0.3960 1.0000
6.000 0.9854 0.01407 0.00676 -0.0696 0.3744 1.0000
6.250 1.0048 0.01450 0.00711 -0.0684 0.3536 1.0000
6.500 1.0229 0.01497 0.00750 -0.0670 0.3337 1.0000
6.750 1.0402 0.01547 0.00791 -0.0654 0.3158 1.0000
7.000 1.0569 0.01597 0.00834 -0.0637 0.3000 1.0000
7.250 1.0727 0.01646 0.00879 -0.0619 0.2858 1.0000
7.500 1.0881 0.01695 0.00925 -0.0600 0.2728 1.0000
7.750 1.1034 0.01748 0.00975 -0.0582 0.2606 1.0000
8.000 1.1184 0.01803 0.01027 -0.0564 0.2493 1.0000
8.250 1.1326 0.01863 0.01084 -0.0545 0.2380 1.0000
8.500 1.1480 0.01920 0.01142 -0.0529 0.2264 1.0000
8.750 1.1629 0.01980 0.01203 -0.0513 0.2155 1.0000
9.000 1.1767 0.02047 0.01269 -0.0495 0.2053 1.0000
9.250 1.1895 0.02122 0.01341 -0.0478 0.1949 1.0000
9.500 1.2036 0.02192 0.01413 -0.0463 0.1845 1.0000
9.750 1.2165 0.02272 0.01494 -0.0447 0.1751 1.0000
10.000 1.2281 0.02360 0.01581 -0.0430 0.1662 1.0000
10.250 1.2420 0.02440 0.01666 -0.0417 0.1581 1.0000
10.750 1.2662 0.02625 0.01858 -0.0388 0.1432 1.0000
11.000 1.2765 0.02733 0.01968 -0.0374 0.1354 1.0000
11.250 1.2872 0.02842 0.02079 -0.0361 0.1259 1.0000
11.500 1.2979 0.02955 0.02195 -0.0348 0.1179 1.0000
11.750 1.3056 0.03091 0.02330 -0.0334 0.1099 1.0000
12.000 1.3155 0.03215 0.02458 -0.0323 0.1012 1.0000
12.250 1.3234 0.03359 0.02604 -0.0311 0.0936 1.0000
12.500 1.3299 0.03516 0.02762 -0.0300 0.0859 1.0000
12.750 1.3376 0.03669 0.02922 -0.0290 0.0790 1.0000
13.000 1.3422 0.03853 0.03106 -0.0280 0.0730 1.0000
13.250 1.3493 0.04019 0.03280 -0.0271 0.0677 1.0000
13.500 1.3534 0.04217 0.03482 -0.0263 0.0630 1.0000
13.750 1.3580 0.04416 0.03687 -0.0256 0.0585 1.0000
14.000 1.3623 0.04624 0.03904 -0.0250 0.0550 1.0000
14.250 1.3637 0.04868 0.04153 -0.0245 0.0515 1.0000
14.500 1.3674 0.05097 0.04392 -0.0242 0.0489 1.0000
14.750 1.3704 0.05340 0.04647 -0.0240 0.0463 1.0000
15.000 1.3711 0.05617 0.04933 -0.0239 0.0437 1.0000
15.250 1.3697 0.05927 0.05250 -0.0240 0.0416 1.0000
15.500 1.3715 0.06207 0.05544 -0.0242 0.0395 1.0000
15.750 1.3715 0.06519 0.05868 -0.0246 0.0378 1.0000
16.000 1.3692 0.06872 0.06231 -0.0253 0.0356 1.0000
16.250 1.3649 0.07263 0.06632 -0.0262 0.0341 1.0000
16.500 1.3623 0.07641 0.07023 -0.0271 0.0321 1.0000
16.750 1.3589 0.08040 0.07437 -0.0283 0.0305 1.0000
17.000 1.3524 0.08501 0.07907 -0.0298 0.0283 1.0000
17.250 1.3435 0.09009 0.08427 -0.0317 0.0270 1.0000
17.500 1.3378 0.09480 0.08913 -0.0335 0.0254 1.0000
17.750 1.3302 0.09993 0.09442 -0.0357 0.0239 1.0000
18.000 1.3186 0.10588 0.10048 -0.0384 0.0218 1.0000
18.250 1.3075 0.11187 0.10660 -0.0412 0.0207 1.0000
18.500 1.2974 0.11779 0.11267 -0.0441 0.0196 1.0000
18.750 1.2857 0.12412 0.11915 -0.0474 0.0185 1.0000
19.000 1.2733 0.13071 0.12587 -0.0509 0.0178 1.0000
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