HQ 3.0/12 AIRFOIL (hq3012-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/12 AIRFOIL (hq3012-il) Reynolds number: 100,000 Max Cl/Cd: 56.48 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3012-il-100000-n5.txt Download as CSV file: xf-hq3012-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3793 0.09371 0.08873 -0.0483 1.0000 0.0263
-9.750 -0.3855 0.08937 0.08446 -0.0495 1.0000 0.0261
-9.500 -0.3937 0.08497 0.08015 -0.0507 1.0000 0.0260
-9.250 -0.4051 0.08044 0.07573 -0.0519 1.0000 0.0258
-9.000 -0.4196 0.07620 0.07160 -0.0526 1.0000 0.0254
-8.750 -0.4429 0.07165 0.06716 -0.0532 1.0000 0.0251
-8.500 -0.4747 0.06865 0.06425 -0.0516 1.0000 0.0248
-8.250 -0.4853 0.06092 0.05639 -0.0600 0.9902 0.0245
-8.000 -0.4833 0.05306 0.04815 -0.0677 0.9790 0.0243
-7.750 -0.4732 0.04624 0.04080 -0.0730 0.9707 0.0244
-7.500 -0.4609 0.04102 0.03503 -0.0754 0.9616 0.0247
-7.250 -0.4391 0.03630 0.02960 -0.0779 0.9560 0.0256
-7.000 -0.4183 0.03286 0.02541 -0.0785 0.9485 0.0277
-6.750 -0.3886 0.03096 0.02337 -0.0804 0.9444 0.0295
-6.500 -0.3623 0.02915 0.02127 -0.0811 0.9386 0.0313
-6.250 -0.3339 0.02714 0.01891 -0.0817 0.9334 0.0336
-6.000 -0.3013 0.02521 0.01659 -0.0828 0.9299 0.0368
-5.750 -0.2750 0.02433 0.01570 -0.0832 0.9238 0.0415
-5.500 -0.2455 0.02326 0.01440 -0.0837 0.9187 0.0482
-5.250 -0.2128 0.02242 0.01352 -0.0851 0.9151 0.0564
-5.000 -0.1877 0.02164 0.01269 -0.0848 0.9085 0.0642
-4.750 -0.1576 0.02102 0.01189 -0.0854 0.9036 0.0731
-4.500 -0.1259 0.02012 0.01103 -0.0864 0.9001 0.0804
-4.250 -0.1027 0.01963 0.01048 -0.0857 0.8926 0.0891
-4.000 -0.0730 0.01902 0.00983 -0.0862 0.8879 0.0997
-3.750 -0.0441 0.01844 0.00924 -0.0866 0.8831 0.1138
-3.500 -0.0197 0.01791 0.00882 -0.0862 0.8762 0.1402
-3.250 0.0096 0.01707 0.00833 -0.0870 0.8719 0.2199
-3.000 0.0295 0.01603 0.00819 -0.0863 0.8651 0.4132
-2.750 0.0547 0.01581 0.00830 -0.0854 0.8596 0.5412
-2.500 0.0851 0.01577 0.00828 -0.0853 0.8559 0.5991
-2.250 0.1066 0.01591 0.00840 -0.0838 0.8478 0.6351
-2.000 0.1341 0.01597 0.00845 -0.0830 0.8431 0.6722
-1.750 0.1565 0.01612 0.00860 -0.0813 0.8364 0.7064
-1.250 0.2103 0.01612 0.00852 -0.0798 0.8260 0.7482
-1.000 0.2321 0.01618 0.00853 -0.0784 0.8176 0.7622
-0.750 0.2624 0.01606 0.00832 -0.0786 0.8128 0.7727
-0.500 0.2869 0.01608 0.00827 -0.0780 0.8046 0.7822
-0.250 0.3162 0.01595 0.00809 -0.0780 0.7990 0.7903
0.000 0.3417 0.01595 0.00804 -0.0775 0.7914 0.7998
0.250 0.3703 0.01587 0.00791 -0.0774 0.7852 0.8095
0.500 0.3964 0.01584 0.00787 -0.0769 0.7780 0.8191
0.750 0.4240 0.01577 0.00778 -0.0767 0.7711 0.8297
1.000 0.4507 0.01574 0.00774 -0.0764 0.7640 0.8415
1.250 0.4779 0.01563 0.00764 -0.0759 0.7560 0.8534
1.500 0.5034 0.01553 0.00756 -0.0752 0.7457 0.8670
1.750 0.5324 0.01534 0.00737 -0.0750 0.7364 0.8825
2.000 0.5616 0.01522 0.00729 -0.0749 0.7262 0.9015
2.250 0.5951 0.01516 0.00730 -0.0760 0.7159 0.9266
2.500 0.6355 0.01506 0.00722 -0.0785 0.7060 0.9744
2.750 0.6656 0.01506 0.00718 -0.0790 0.6956 1.0000
3.000 0.6916 0.01515 0.00725 -0.0788 0.6832 1.0000
3.250 0.7181 0.01522 0.00729 -0.0786 0.6700 1.0000
3.500 0.7445 0.01528 0.00735 -0.0783 0.6556 1.0000
3.750 0.7707 0.01535 0.00739 -0.0779 0.6398 1.0000
4.000 0.7967 0.01543 0.00745 -0.0774 0.6234 1.0000
4.250 0.8218 0.01556 0.00756 -0.0769 0.6058 1.0000
4.500 0.8461 0.01571 0.00773 -0.0762 0.5862 1.0000
4.750 0.8707 0.01587 0.00785 -0.0755 0.5655 1.0000
5.000 0.8943 0.01608 0.00803 -0.0746 0.5419 1.0000
5.250 0.9176 0.01632 0.00823 -0.0737 0.5165 1.0000
5.500 0.9399 0.01664 0.00844 -0.0727 0.4886 1.0000
5.750 0.9613 0.01703 0.00873 -0.0715 0.4602 1.0000
6.000 0.9817 0.01749 0.00907 -0.0703 0.4316 1.0000
6.250 1.0014 0.01802 0.00952 -0.0690 0.4042 1.0000
6.500 1.0206 0.01858 0.01000 -0.0677 0.3779 1.0000
6.750 1.0392 0.01918 0.01052 -0.0663 0.3530 1.0000
7.000 1.0571 0.01983 0.01108 -0.0648 0.3305 1.0000
7.250 1.0749 0.02048 0.01169 -0.0634 0.3092 1.0000
7.500 1.0920 0.02118 0.01236 -0.0619 0.2903 1.0000
7.750 1.1085 0.02191 0.01304 -0.0604 0.2728 1.0000
8.000 1.1248 0.02264 0.01375 -0.0588 0.2563 1.0000
8.250 1.1406 0.02337 0.01450 -0.0573 0.2404 1.0000
8.500 1.1546 0.02411 0.01525 -0.0554 0.2252 1.0000
8.750 1.1679 0.02490 0.01607 -0.0535 0.2111 1.0000
9.000 1.1806 0.02573 0.01692 -0.0516 0.1977 1.0000
9.250 1.1925 0.02662 0.01782 -0.0497 0.1850 1.0000
9.500 1.2041 0.02756 0.01878 -0.0478 0.1726 1.0000
9.750 1.2161 0.02852 0.01982 -0.0461 0.1609 1.0000
10.000 1.2272 0.02955 0.02092 -0.0444 0.1497 1.0000
10.250 1.2374 0.03068 0.02210 -0.0426 0.1396 1.0000
10.500 1.2455 0.03194 0.02342 -0.0409 0.1301 1.0000
10.750 1.2549 0.03319 0.02478 -0.0393 0.1194 1.0000
11.000 1.2631 0.03456 0.02623 -0.0377 0.1094 1.0000
11.250 1.2693 0.03610 0.02781 -0.0362 0.1005 1.0000
11.500 1.2742 0.03778 0.02953 -0.0348 0.0920 1.0000
11.750 1.2808 0.03944 0.03131 -0.0335 0.0836 1.0000
12.000 1.2838 0.04141 0.03329 -0.0323 0.0772 1.0000
12.250 1.2889 0.04331 0.03534 -0.0313 0.0704 1.0000
12.500 1.2897 0.04562 0.03768 -0.0303 0.0656 1.0000
12.750 1.2938 0.04776 0.04001 -0.0295 0.0606 1.0000
13.000 1.2936 0.05034 0.04272 -0.0288 0.0567 1.0000
13.250 1.2927 0.05311 0.04560 -0.0283 0.0532 1.0000
13.500 1.2932 0.05585 0.04853 -0.0281 0.0487 1.0000
13.750 1.2883 0.05925 0.05202 -0.0282 0.0453 1.0000
14.000 1.2852 0.06266 0.05558 -0.0285 0.0415 1.0000
14.250 1.2807 0.06640 0.05949 -0.0291 0.0375 1.0000
14.500 1.2710 0.07100 0.06418 -0.0303 0.0351 1.0000
14.750 1.2638 0.07552 0.06888 -0.0315 0.0325 1.0000
15.000 1.2553 0.08046 0.07403 -0.0331 0.0303 1.0000
15.250 1.2437 0.08614 0.07988 -0.0353 0.0286 1.0000
15.500 1.2305 0.09234 0.08624 -0.0381 0.0274 1.0000
15.750 1.2157 0.09912 0.09315 -0.0413 0.0266 1.0000
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