HQ 3.0/12 AIRFOIL (hq3012-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/12 AIRFOIL (hq3012-il) Reynolds number: 50,000 Max Cl/Cd: 34.39 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3012-il-50000.txt Download as CSV file: xf-hq3012-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3403 0.10661 0.09996 -0.0296 1.0000 0.2743
-8.750 -0.3538 0.10574 0.09922 -0.0286 1.0000 0.2863
-8.500 -0.3523 0.10313 0.09669 -0.0269 1.0000 0.3013
-8.250 -0.3516 0.10064 0.09429 -0.0249 1.0000 0.3162
-8.000 -0.3499 0.09805 0.09178 -0.0227 1.0000 0.3310
-7.750 -0.3488 0.09556 0.08938 -0.0203 1.0000 0.3454
-7.500 -0.3525 0.09355 0.08746 -0.0175 1.0000 0.3601
-7.250 -0.3620 0.09211 0.08614 -0.0141 1.0000 0.3753
-6.750 -0.3537 0.08734 0.08147 -0.0076 1.0000 0.4178
-6.500 -0.3763 0.08711 0.08139 -0.0026 1.0000 0.4348
-5.750 -0.5154 0.06108 0.05477 -0.0385 1.0000 0.1673
-5.500 -0.5125 0.06916 0.06382 -0.0193 1.0000 0.2727
-5.250 -0.4836 0.04946 0.04215 -0.0422 1.0000 0.1362
-5.000 -0.4649 0.04547 0.03780 -0.0427 1.0000 0.1324
-4.750 -0.4432 0.04201 0.03375 -0.0434 1.0000 0.1337
-4.500 -0.4188 0.03899 0.02998 -0.0439 1.0000 0.1369
-4.250 -0.3967 0.03645 0.02728 -0.0437 1.0000 0.1433
-4.000 -0.3719 0.03447 0.02471 -0.0435 1.0000 0.1519
-3.750 -0.3498 0.03272 0.02287 -0.0430 1.0000 0.1638
-3.500 -0.3264 0.03112 0.02104 -0.0424 1.0000 0.1740
-3.250 -0.3041 0.02993 0.01976 -0.0416 1.0000 0.1900
-3.000 -0.2818 0.02883 0.01860 -0.0405 1.0000 0.2048
-2.750 -0.2602 0.02792 0.01771 -0.0396 1.0000 0.2286
-2.500 -0.2378 0.02690 0.01689 -0.0388 1.0000 0.2642
-2.250 -0.2140 0.02469 0.01647 -0.0382 1.0000 0.4601
-2.000 -0.2241 0.02503 0.01771 -0.0269 1.0000 0.7370
-1.750 -0.2288 0.02511 0.01785 -0.0184 1.0000 0.8175
-1.500 -0.2272 0.02487 0.01764 -0.0116 1.0000 0.8885
-1.250 -0.1714 0.02497 0.01747 -0.0167 1.0000 1.0000
-1.000 -0.1561 0.02491 0.01714 -0.0173 1.0000 1.0000
-0.750 -0.1351 0.02511 0.01702 -0.0185 1.0000 1.0000
-0.500 -0.1120 0.02547 0.01710 -0.0200 1.0000 1.0000
-0.250 -0.0884 0.02595 0.01730 -0.0215 1.0000 1.0000
0.000 -0.0649 0.02650 0.01760 -0.0228 1.0000 1.0000
0.250 -0.0420 0.02713 0.01800 -0.0240 1.0000 1.0000
0.500 -0.0197 0.02782 0.01849 -0.0250 1.0000 1.0000
0.750 0.0296 0.02943 0.01984 -0.0310 0.9866 1.0000
1.000 0.0749 0.03090 0.02110 -0.0361 0.9732 1.0000
1.250 0.1163 0.03223 0.02226 -0.0403 0.9597 1.0000
1.500 0.1557 0.03349 0.02337 -0.0440 0.9457 1.0000
1.750 0.1944 0.03471 0.02447 -0.0474 0.9311 1.0000
2.000 0.2333 0.03589 0.02556 -0.0508 0.9157 1.0000
2.250 0.2737 0.03706 0.02665 -0.0541 0.8993 1.0000
2.500 0.3169 0.03820 0.02774 -0.0576 0.8826 1.0000
2.750 0.3489 0.03912 0.02863 -0.0593 0.8651 1.0000
3.000 0.3807 0.04001 0.02951 -0.0608 0.8472 1.0000
3.250 0.4152 0.04090 0.03040 -0.0626 0.8296 1.0000
3.500 0.4528 0.04172 0.03124 -0.0646 0.8121 1.0000
3.750 0.4939 0.04240 0.03197 -0.0668 0.7949 1.0000
4.000 0.5243 0.04311 0.03271 -0.0675 0.7764 1.0000
4.250 0.5533 0.04375 0.03343 -0.0679 0.7569 1.0000
4.500 0.5926 0.04406 0.03382 -0.0692 0.7385 1.0000
4.750 0.6409 0.04384 0.03372 -0.0709 0.7208 1.0000
5.000 0.6613 0.04445 0.03444 -0.0698 0.6990 1.0000
5.250 0.7057 0.04389 0.03402 -0.0705 0.6799 1.0000
5.500 0.7605 0.04243 0.03277 -0.0716 0.6628 1.0000
5.750 0.7857 0.04242 0.03288 -0.0702 0.6409 1.0000
6.000 0.8388 0.04050 0.03117 -0.0705 0.6227 1.0000
6.250 0.9036 0.03758 0.02850 -0.0713 0.6049 1.0000
6.500 0.9393 0.03655 0.02762 -0.0702 0.5816 1.0000
6.750 1.0015 0.03373 0.02494 -0.0709 0.5581 1.0000
7.000 1.0428 0.03251 0.02375 -0.0703 0.5305 1.0000
7.250 1.0752 0.03212 0.02335 -0.0692 0.5016 1.0000
7.500 1.1035 0.03226 0.02347 -0.0680 0.4730 1.0000
7.750 1.1282 0.03281 0.02398 -0.0666 0.4451 1.0000
8.000 1.1504 0.03370 0.02485 -0.0652 0.4190 1.0000
8.250 1.1743 0.03463 0.02572 -0.0640 0.3937 1.0000
8.500 1.2009 0.03558 0.02656 -0.0632 0.3690 1.0000
8.750 1.2138 0.03709 0.02822 -0.0610 0.3471 1.0000
9.000 1.2391 0.03820 0.02917 -0.0602 0.3240 1.0000
9.250 1.2501 0.03992 0.03106 -0.0579 0.3039 1.0000
9.500 1.2733 0.04122 0.03221 -0.0569 0.2817 1.0000
9.750 1.2841 0.04319 0.03433 -0.0547 0.2634 1.0000
10.000 1.2937 0.04518 0.03651 -0.0524 0.2457 1.0000
10.250 1.3048 0.04734 0.03879 -0.0504 0.2295 1.0000
10.500 1.3144 0.04950 0.04107 -0.0483 0.2144 1.0000
10.750 1.3206 0.05201 0.04374 -0.0460 0.2019 1.0000
11.000 1.3299 0.05476 0.04663 -0.0442 0.1911 1.0000
11.250 1.3441 0.05716 0.04903 -0.0428 0.1793 1.0000
11.500 1.3220 0.06082 0.05318 -0.0385 0.1757 1.0000
11.750 1.3413 0.06352 0.05585 -0.0378 0.1655 1.0000
12.000 1.3131 0.06744 0.06015 -0.0336 0.1645 1.0000
12.250 1.2822 0.07178 0.06477 -0.0301 0.1640 1.0000
12.500 1.2485 0.07695 0.07017 -0.0281 0.1642 1.0000
12.750 1.2127 0.08315 0.07655 -0.0276 0.1649 1.0000
13.000 1.1758 0.09057 0.08408 -0.0287 0.1658 1.0000
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Polar data table (+)
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