HQ 3.0/12 AIRFOIL (hq3012-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/12 AIRFOIL (hq3012-il) Reynolds number: 200,000 Max Cl/Cd: 80.78 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3012-il-200000.txt Download as CSV file: xf-hq3012-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3833 0.08928 0.08601 -0.0508 1.0000 0.0534
-9.000 -0.4061 0.08589 0.08273 -0.0514 1.0000 0.0536
-8.750 -0.4287 0.08379 0.08071 -0.0491 1.0000 0.0536
-8.500 -0.4612 0.08230 0.07931 -0.0459 1.0000 0.0536
-8.250 -0.3248 0.06998 0.06714 -0.0475 0.9907 0.0612
-8.000 -0.4616 0.06962 0.06615 -0.0654 0.9846 0.0540
-7.750 -0.4482 0.06155 0.05824 -0.0684 0.9823 0.0557
-7.500 -0.4276 0.05913 0.05586 -0.0694 0.9766 0.0576
-7.250 -0.4057 0.05475 0.05133 -0.0745 0.9713 0.0605
-6.500 -0.3603 0.02831 0.02199 -0.0830 0.9487 0.0333
-6.250 -0.3304 0.02470 0.01802 -0.0846 0.9450 0.0345
-6.000 -0.2934 0.02312 0.01629 -0.0869 0.9426 0.0370
-5.750 -0.2584 0.02223 0.01514 -0.0883 0.9390 0.0417
-5.500 -0.2317 0.02040 0.01319 -0.0884 0.9329 0.0457
-5.250 -0.1942 0.01961 0.01224 -0.0902 0.9299 0.0536
-5.000 -0.1575 0.01845 0.01107 -0.0923 0.9275 0.0646
-4.750 -0.1321 0.01766 0.01028 -0.0920 0.9210 0.0730
-4.500 -0.1001 0.01702 0.00958 -0.0930 0.9164 0.0829
-4.250 -0.0651 0.01634 0.00890 -0.0944 0.9134 0.0926
-4.000 -0.0398 0.01568 0.00828 -0.0941 0.9070 0.1015
-3.750 -0.0111 0.01506 0.00770 -0.0943 0.9016 0.1161
-3.500 0.0210 0.01427 0.00704 -0.0953 0.8981 0.1481
-3.250 0.0390 0.01296 0.00664 -0.0945 0.8903 0.3375
-3.000 0.0634 0.01235 0.00678 -0.0936 0.8853 0.5595
-2.750 0.0934 0.01234 0.00678 -0.0935 0.8812 0.6123
-2.500 0.1166 0.01248 0.00690 -0.0922 0.8734 0.6440
-2.250 0.1465 0.01248 0.00689 -0.0920 0.8691 0.6696
-2.000 0.1711 0.01259 0.00695 -0.0910 0.8622 0.6900
-1.750 0.1986 0.01260 0.00693 -0.0904 0.8564 0.7072
-1.500 0.2260 0.01262 0.00696 -0.0895 0.8514 0.7282
-1.250 0.2481 0.01276 0.00710 -0.0878 0.8435 0.7504
-1.000 0.2763 0.01269 0.00700 -0.0872 0.8389 0.7660
-0.750 0.2999 0.01275 0.00705 -0.0862 0.8311 0.7788
-0.500 0.3270 0.01266 0.00694 -0.0856 0.8256 0.7909
-0.250 0.3522 0.01262 0.00690 -0.0848 0.8191 0.8011
0.000 0.3795 0.01255 0.00679 -0.0846 0.8125 0.8100
0.250 0.4073 0.01243 0.00663 -0.0842 0.8063 0.8186
0.500 0.4333 0.01228 0.00647 -0.0836 0.7973 0.8276
0.750 0.4600 0.01215 0.00630 -0.0830 0.7886 0.8378
1.000 0.4870 0.01196 0.00611 -0.0825 0.7811 0.8473
1.250 0.5118 0.01189 0.00607 -0.0817 0.7727 0.8582
1.500 0.5392 0.01174 0.00590 -0.0813 0.7658 0.8698
1.750 0.5632 0.01167 0.00587 -0.0803 0.7566 0.8833
2.000 0.5913 0.01149 0.00568 -0.0799 0.7495 0.8979
2.250 0.6162 0.01138 0.00564 -0.0791 0.7389 0.9157
2.500 0.6481 0.01124 0.00553 -0.0796 0.7282 0.9385
2.750 0.6895 0.01109 0.00539 -0.0822 0.7170 0.9670
3.000 0.7285 0.01101 0.00526 -0.0847 0.7058 1.0000
3.250 0.7550 0.01106 0.00528 -0.0847 0.6932 1.0000
3.500 0.7822 0.01110 0.00531 -0.0847 0.6800 1.0000
3.750 0.8092 0.01116 0.00533 -0.0846 0.6662 1.0000
4.000 0.8357 0.01122 0.00535 -0.0843 0.6511 1.0000
4.250 0.8619 0.01129 0.00540 -0.0839 0.6349 1.0000
4.500 0.8873 0.01138 0.00545 -0.0834 0.6166 1.0000
4.750 0.9117 0.01150 0.00555 -0.0827 0.5951 1.0000
5.000 0.9358 0.01166 0.00565 -0.0819 0.5724 1.0000
5.250 0.9588 0.01187 0.00578 -0.0809 0.5458 1.0000
5.500 0.9808 0.01216 0.00596 -0.0798 0.5158 1.0000
5.750 1.0016 0.01253 0.00621 -0.0785 0.4831 1.0000
6.000 1.0213 0.01299 0.00653 -0.0770 0.4494 1.0000
6.250 1.0399 0.01353 0.00691 -0.0755 0.4165 1.0000
6.500 1.0582 0.01411 0.00734 -0.0739 0.3857 1.0000
6.750 1.0761 0.01471 0.00782 -0.0724 0.3568 1.0000
7.000 1.0937 0.01533 0.00833 -0.0708 0.3301 1.0000
7.250 1.1108 0.01598 0.00887 -0.0692 0.3067 1.0000
7.500 1.1277 0.01663 0.00943 -0.0676 0.2850 1.0000
7.750 1.1438 0.01733 0.01003 -0.0659 0.2665 1.0000
8.000 1.1609 0.01794 0.01062 -0.0643 0.2487 1.0000
8.250 1.1773 0.01856 0.01124 -0.0627 0.2325 1.0000
8.500 1.1922 0.01919 0.01185 -0.0608 0.2178 1.0000
8.750 1.2059 0.01984 0.01249 -0.0587 0.2042 1.0000
9.000 1.2190 0.02054 0.01318 -0.0566 0.1914 1.0000
9.250 1.2312 0.02131 0.01392 -0.0545 0.1789 1.0000
9.500 1.2430 0.02211 0.01471 -0.0524 0.1666 1.0000
9.750 1.2550 0.02290 0.01555 -0.0504 0.1539 1.0000
10.000 1.2660 0.02377 0.01644 -0.0485 0.1407 1.0000
10.250 1.2764 0.02470 0.01739 -0.0466 0.1277 1.0000
10.500 1.2861 0.02574 0.01843 -0.0447 0.1149 1.0000
10.750 1.2951 0.02686 0.01956 -0.0428 0.1029 1.0000
11.000 1.3031 0.02813 0.02085 -0.0410 0.0930 1.0000
11.250 1.3093 0.02956 0.02225 -0.0392 0.0842 1.0000
11.500 1.3178 0.03087 0.02360 -0.0377 0.0761 1.0000
11.750 1.3241 0.03243 0.02525 -0.0361 0.0704 1.0000
12.000 1.3309 0.03396 0.02683 -0.0347 0.0648 1.0000
12.250 1.3347 0.03582 0.02874 -0.0332 0.0605 1.0000
12.500 1.3429 0.03734 0.03039 -0.0322 0.0556 1.0000
12.750 1.3436 0.03956 0.03261 -0.0309 0.0516 1.0000
13.000 1.3502 0.04134 0.03456 -0.0300 0.0472 1.0000
13.250 1.3517 0.04362 0.03690 -0.0292 0.0425 1.0000
13.500 1.3516 0.04620 0.03961 -0.0284 0.0377 1.0000
13.750 1.3461 0.04942 0.04286 -0.0279 0.0325 1.0000
14.000 1.3423 0.05270 0.04628 -0.0276 0.0269 1.0000
14.250 1.3325 0.05675 0.05037 -0.0277 0.0247 1.0000
14.500 1.3264 0.06060 0.05440 -0.0278 0.0225 1.0000
14.750 1.3216 0.06445 0.05838 -0.0283 0.0207 1.0000
15.000 1.3154 0.06862 0.06267 -0.0291 0.0197 1.0000
15.250 1.3070 0.07323 0.06736 -0.0302 0.0189 1.0000
15.500 1.2961 0.07827 0.07246 -0.0313 0.0182 1.0000
15.750 1.2917 0.08269 0.07707 -0.0326 0.0177 1.0000
16.000 1.2863 0.08734 0.08190 -0.0340 0.0172 1.0000
16.250 1.2804 0.09221 0.08694 -0.0357 0.0167 1.0000
16.500 1.2746 0.09715 0.09203 -0.0376 0.0163 1.0000
16.750 1.2680 0.10235 0.09739 -0.0397 0.0160 1.0000
17.000 1.2610 0.10774 0.10293 -0.0421 0.0156 1.0000
17.250 1.2536 0.11331 0.10866 -0.0448 0.0154 1.0000
17.500 1.2456 0.11916 0.11465 -0.0477 0.0152 1.0000
17.750 1.2369 0.12525 0.12090 -0.0510 0.0150 1.0000
18.000 1.2271 0.13173 0.12754 -0.0546 0.0150 1.0000
18.250 1.2161 0.13868 0.13466 -0.0587 0.0149 1.0000
18.500 1.2022 0.14654 0.14272 -0.0636 0.0149 1.0000
18.750 1.1844 0.15573 0.15212 -0.0695 0.0151 1.0000
19.000 1.1603 0.16710 0.16371 -0.0770 0.0154 1.0000
19.250 1.1053 0.18908 0.18597 -0.0911 0.0167 1.0000
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