HQ 3.0/13 AIRFOIL (hq3013-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/13 AIRFOIL (hq3013-il) Reynolds number: 50,000 Max Cl/Cd: 32.5 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3013-il-50000.txt Download as CSV file: xf-hq3013-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/13 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3557 0.13004 0.12292 -0.0349 1.0000 0.2230
-10.750 -0.3297 0.12421 0.11707 -0.0335 1.0000 0.2319
-10.500 -0.3581 0.12490 0.11793 -0.0350 1.0000 0.2386
-10.250 -0.3282 0.11887 0.11187 -0.0332 1.0000 0.2502
-10.000 -0.3241 0.11568 0.10874 -0.0326 1.0000 0.2597
-9.750 -0.3449 0.11544 0.10865 -0.0328 1.0000 0.2689
-9.500 -0.3334 0.11180 0.10505 -0.0313 1.0000 0.2834
-9.250 -0.3263 0.10863 0.10193 -0.0298 1.0000 0.2979
-9.000 -0.3180 0.10528 0.09863 -0.0285 1.0000 0.3094
-8.750 -0.3210 0.10291 0.09636 -0.0271 1.0000 0.3204
-8.500 -0.3290 0.10113 0.09470 -0.0252 1.0000 0.3335
-8.250 -0.3241 0.09853 0.09215 -0.0229 1.0000 0.3504
-8.000 -0.3221 0.09632 0.09001 -0.0203 1.0000 0.3680
-7.750 -0.3266 0.09449 0.08828 -0.0174 1.0000 0.3822
-7.500 -0.3352 0.09292 0.08681 -0.0143 1.0000 0.3955
-7.250 -0.3424 0.09133 0.08530 -0.0109 1.0000 0.4101
-7.000 -0.3418 0.08933 0.08336 -0.0077 1.0000 0.4285
-6.750 -0.3494 0.08772 0.08184 -0.0043 1.0000 0.4426
-6.500 -0.3630 0.08643 0.08065 -0.0006 1.0000 0.4551
-6.250 -0.5624 0.06095 0.05450 -0.0391 1.0000 0.1484
-6.000 -0.5526 0.05685 0.05023 -0.0388 1.0000 0.1455
-5.750 -0.5417 0.05237 0.04542 -0.0393 1.0000 0.1420
-5.500 -0.5271 0.04795 0.04048 -0.0402 1.0000 0.1400
-5.250 -0.5092 0.04445 0.03643 -0.0407 1.0000 0.1433
-5.000 -0.4879 0.04119 0.03244 -0.0411 1.0000 0.1462
-4.750 -0.4682 0.03883 0.02995 -0.0407 1.0000 0.1539
-4.500 -0.4451 0.03664 0.02721 -0.0406 1.0000 0.1607
-4.250 -0.4238 0.03484 0.02528 -0.0401 1.0000 0.1700
-4.000 -0.4002 0.03325 0.02320 -0.0396 1.0000 0.1787
-3.750 -0.3789 0.03202 0.02190 -0.0389 1.0000 0.1910
-3.500 -0.3572 0.03081 0.02068 -0.0380 1.0000 0.2023
-3.250 -0.3359 0.02988 0.01971 -0.0371 1.0000 0.2197
-3.000 -0.3147 0.02895 0.01887 -0.0361 1.0000 0.2420
-2.750 -0.2935 0.02797 0.01807 -0.0352 1.0000 0.2782
-2.500 -0.2709 0.02609 0.01762 -0.0347 1.0000 0.4164
-2.250 -0.2763 0.02653 0.01919 -0.0247 1.0000 0.6851
-2.000 -0.2780 0.02704 0.01973 -0.0169 1.0000 0.7597
-1.750 -0.2781 0.02717 0.01985 -0.0100 1.0000 0.8122
-1.500 -0.2756 0.02707 0.01971 -0.0040 1.0000 0.8630
-1.250 -0.2546 0.02708 0.01969 -0.0014 1.0000 0.9284
-1.000 -0.1681 0.02823 0.02041 -0.0133 1.0000 1.0000
-0.750 -0.1679 0.02773 0.01977 -0.0117 1.0000 1.0000
-0.500 -0.1555 0.02765 0.01949 -0.0120 1.0000 1.0000
-0.250 -0.1363 0.02789 0.01950 -0.0132 1.0000 1.0000
0.000 -0.1144 0.02833 0.01972 -0.0148 1.0000 1.0000
0.250 -0.0693 0.02969 0.02079 -0.0206 0.9898 1.0000
0.500 -0.0226 0.03114 0.02198 -0.0263 0.9769 1.0000
0.750 0.0206 0.03247 0.02309 -0.0313 0.9639 1.0000
1.000 0.0618 0.03377 0.02418 -0.0356 0.9509 1.0000
1.250 0.1021 0.03505 0.02529 -0.0396 0.9376 1.0000
1.500 0.1419 0.03631 0.02640 -0.0434 0.9241 1.0000
1.750 0.1803 0.03751 0.02747 -0.0468 0.9097 1.0000
2.000 0.2172 0.03863 0.02848 -0.0497 0.8947 1.0000
2.250 0.2514 0.03967 0.02944 -0.0520 0.8788 1.0000
2.500 0.2843 0.04065 0.03036 -0.0540 0.8623 1.0000
2.750 0.3169 0.04162 0.03128 -0.0557 0.8454 1.0000
3.000 0.3497 0.04257 0.03219 -0.0574 0.8285 1.0000
3.250 0.3828 0.04349 0.03309 -0.0590 0.8116 1.0000
3.500 0.4162 0.04438 0.03398 -0.0605 0.7950 1.0000
3.750 0.4507 0.04520 0.03481 -0.0620 0.7784 1.0000
4.000 0.4870 0.04591 0.03554 -0.0634 0.7617 1.0000
4.250 0.5248 0.04649 0.03617 -0.0648 0.7451 1.0000
4.500 0.5520 0.04717 0.03689 -0.0649 0.7270 1.0000
4.750 0.5761 0.04788 0.03765 -0.0647 0.7080 1.0000
5.000 0.6097 0.04820 0.03806 -0.0650 0.6897 1.0000
5.250 0.6500 0.04807 0.03802 -0.0657 0.6722 1.0000
5.500 0.6938 0.04755 0.03762 -0.0663 0.6555 1.0000
5.750 0.7192 0.04781 0.03798 -0.0654 0.6360 1.0000
6.000 0.7471 0.04788 0.03815 -0.0646 0.6169 1.0000
6.250 0.7887 0.04682 0.03726 -0.0642 0.5998 1.0000
6.500 0.8381 0.04489 0.03549 -0.0639 0.5840 1.0000
6.750 0.9028 0.04183 0.03267 -0.0646 0.5679 1.0000
7.000 0.9815 0.03785 0.02886 -0.0665 0.5502 1.0000
7.250 1.0043 0.03786 0.02899 -0.0647 0.5273 1.0000
7.500 1.0675 0.03535 0.02649 -0.0660 0.5035 1.0000
7.750 1.0926 0.03555 0.02672 -0.0646 0.4792 1.0000
8.000 1.1246 0.03555 0.02673 -0.0639 0.4552 1.0000
8.250 1.1591 0.03566 0.02674 -0.0636 0.4311 1.0000
8.500 1.1764 0.03680 0.02793 -0.0619 0.4096 1.0000
8.750 1.2006 0.03769 0.02880 -0.0609 0.3882 1.0000
9.000 1.2254 0.03868 0.02977 -0.0600 0.3676 1.0000
9.250 1.2387 0.04020 0.03140 -0.0580 0.3493 1.0000
9.500 1.2555 0.04157 0.03282 -0.0564 0.3310 1.0000
9.750 1.2787 0.04275 0.03395 -0.0555 0.3122 1.0000
10.000 1.3001 0.04420 0.03534 -0.0544 0.2943 1.0000
10.250 1.3113 0.04604 0.03732 -0.0524 0.2786 1.0000
10.500 1.3222 0.04795 0.03933 -0.0504 0.2634 1.0000
10.750 1.3338 0.04995 0.04142 -0.0485 0.2488 1.0000
11.000 1.3460 0.05194 0.04346 -0.0468 0.2348 1.0000
11.250 1.3280 0.05512 0.04707 -0.0424 0.2277 1.0000
11.500 1.3330 0.05760 0.04965 -0.0403 0.2171 1.0000
11.750 1.3474 0.05967 0.05172 -0.0390 0.2050 1.0000
12.000 1.3149 0.06346 0.05587 -0.0341 0.2029 1.0000
12.250 1.2795 0.06799 0.06066 -0.0304 0.2017 1.0000
12.500 1.2356 0.07401 0.06691 -0.0282 0.2022 1.0000
12.750 1.1842 0.08215 0.07520 -0.0283 0.2041 1.0000
13.000 1.1311 0.09264 0.08574 -0.0310 0.2061 1.0000
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Polar data table (+)
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