HQ 2.5/12 AIRFOIL (hq2512-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.5/12 AIRFOIL (hq2512-il) Reynolds number: 50,000 Max Cl/Cd: 36.06 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2512-il-50000-n5.txt Download as CSV file: xf-hq2512-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/12 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4067 0.10211 0.09504 -0.0423 1.0000 0.0522
-10.000 -0.4100 0.09768 0.09070 -0.0442 1.0000 0.0522
-9.500 -0.4544 0.08057 0.07378 -0.0566 1.0000 0.0472
-9.250 -0.4689 0.07616 0.06944 -0.0583 1.0000 0.0470
-9.000 -0.4873 0.07262 0.06597 -0.0586 1.0000 0.0468
-8.750 -0.5055 0.06946 0.06286 -0.0577 1.0000 0.0466
-8.500 -0.5236 0.06622 0.05959 -0.0566 1.0000 0.0465
-8.250 -0.5413 0.06307 0.05635 -0.0549 1.0000 0.0466
-8.000 -0.5561 0.05993 0.05304 -0.0529 1.0000 0.0468
-7.750 -0.5678 0.05668 0.04952 -0.0508 1.0000 0.0471
-7.500 -0.5722 0.05357 0.04626 -0.0490 1.0000 0.0478
-7.250 -0.5715 0.05081 0.04333 -0.0473 1.0000 0.0487
-7.000 -0.5680 0.04808 0.04038 -0.0457 1.0000 0.0496
-6.750 -0.5615 0.04547 0.03752 -0.0442 1.0000 0.0509
-6.500 -0.5523 0.04312 0.03487 -0.0429 1.0000 0.0535
-6.250 -0.5409 0.04051 0.03175 -0.0418 1.0000 0.0574
-6.000 -0.5221 0.03764 0.02828 -0.0415 0.9985 0.0608
-5.750 -0.4920 0.03562 0.02612 -0.0432 0.9932 0.0664
-5.500 -0.4603 0.03350 0.02335 -0.0445 0.9876 0.0740
-5.250 -0.4290 0.03193 0.02172 -0.0459 0.9827 0.0819
-5.000 -0.3989 0.03047 0.02004 -0.0466 0.9770 0.0905
-4.750 -0.3656 0.02939 0.01868 -0.0477 0.9720 0.1013
-4.500 -0.3375 0.02834 0.01765 -0.0481 0.9661 0.1115
-4.250 -0.3071 0.02737 0.01657 -0.0488 0.9604 0.1221
-4.000 -0.2764 0.02655 0.01570 -0.0499 0.9547 0.1417
-3.750 -0.2480 0.02565 0.01490 -0.0508 0.9482 0.1671
-3.500 -0.2154 0.02448 0.01408 -0.0527 0.9431 0.2308
-3.250 -0.1948 0.02311 0.01380 -0.0525 0.9360 0.3984
-3.000 -0.1703 0.02306 0.01427 -0.0509 0.9299 0.5681
-2.750 -0.1493 0.02333 0.01453 -0.0489 0.9221 0.6412
-2.500 -0.1241 0.02367 0.01481 -0.0473 0.9158 0.6988
-2.250 -0.1075 0.02394 0.01506 -0.0439 0.9079 0.7449
-2.000 -0.0842 0.02412 0.01514 -0.0418 0.9017 0.7856
-1.750 -0.0655 0.02417 0.01511 -0.0393 0.8940 0.8160
-1.500 -0.0384 0.02417 0.01501 -0.0384 0.8879 0.8458
-1.250 -0.0129 0.02416 0.01489 -0.0376 0.8807 0.8715
-1.000 0.0235 0.02416 0.01472 -0.0393 0.8746 0.8896
-0.750 0.0635 0.02418 0.01459 -0.0419 0.8690 0.9058
-0.500 0.1037 0.02425 0.01452 -0.0447 0.8620 0.9222
-0.250 0.1561 0.02427 0.01440 -0.0497 0.8577 0.9374
0.000 0.1975 0.02439 0.01444 -0.0531 0.8497 0.9563
0.250 0.2504 0.02439 0.01431 -0.0584 0.8443 0.9730
0.500 0.2918 0.02449 0.01435 -0.0620 0.8360 1.0000
0.750 0.3191 0.02447 0.01424 -0.0625 0.8286 1.0000
1.000 0.3327 0.02469 0.01437 -0.0609 0.8172 1.0000
1.250 0.3554 0.02489 0.01450 -0.0607 0.8077 1.0000
1.500 0.3884 0.02495 0.01450 -0.0619 0.8003 1.0000
1.750 0.4100 0.02524 0.01474 -0.0614 0.7894 1.0000
2.000 0.4380 0.02539 0.01485 -0.0616 0.7796 1.0000
2.250 0.4751 0.02522 0.01466 -0.0628 0.7707 1.0000
2.500 0.5019 0.02523 0.01466 -0.0625 0.7576 1.0000
2.750 0.5296 0.02519 0.01462 -0.0621 0.7444 1.0000
3.000 0.5570 0.02518 0.01461 -0.0617 0.7314 1.0000
3.250 0.5844 0.02518 0.01466 -0.0613 0.7186 1.0000
3.500 0.6122 0.02517 0.01468 -0.0610 0.7059 1.0000
3.750 0.6403 0.02513 0.01468 -0.0606 0.6929 1.0000
4.000 0.6680 0.02507 0.01467 -0.0601 0.6791 1.0000
4.250 0.6949 0.02502 0.01472 -0.0594 0.6642 1.0000
4.500 0.7211 0.02498 0.01474 -0.0586 0.6481 1.0000
4.750 0.7476 0.02490 0.01473 -0.0578 0.6310 1.0000
5.000 0.7754 0.02474 0.01467 -0.0570 0.6131 1.0000
5.250 0.7973 0.02484 0.01485 -0.0557 0.5915 1.0000
5.500 0.8239 0.02474 0.01479 -0.0547 0.5698 1.0000
5.750 0.8461 0.02486 0.01496 -0.0533 0.5445 1.0000
6.000 0.8696 0.02496 0.01511 -0.0521 0.5178 1.0000
6.250 0.8927 0.02515 0.01527 -0.0508 0.4895 1.0000
6.500 0.9148 0.02547 0.01553 -0.0494 0.4603 1.0000
6.750 0.9354 0.02594 0.01592 -0.0480 0.4317 1.0000
7.000 0.9549 0.02656 0.01646 -0.0466 0.4047 1.0000
7.250 0.9737 0.02728 0.01713 -0.0452 0.3797 1.0000
7.500 0.9913 0.02811 0.01793 -0.0438 0.3564 1.0000
7.750 1.0088 0.02899 0.01878 -0.0424 0.3349 1.0000
8.000 1.0258 0.02992 0.01971 -0.0410 0.3148 1.0000
8.250 1.0430 0.03089 0.02064 -0.0397 0.2965 1.0000
8.500 1.0594 0.03194 0.02176 -0.0384 0.2786 1.0000
8.750 1.0756 0.03303 0.02292 -0.0371 0.2619 1.0000
9.000 1.0910 0.03416 0.02412 -0.0357 0.2459 1.0000
9.250 1.1059 0.03532 0.02536 -0.0343 0.2314 1.0000
9.500 1.1199 0.03652 0.02667 -0.0328 0.2177 1.0000
9.750 1.1345 0.03779 0.02803 -0.0314 0.2053 1.0000
10.000 1.1479 0.03908 0.02940 -0.0300 0.1936 1.0000
10.250 1.1593 0.04043 0.03090 -0.0284 0.1823 1.0000
10.500 1.1686 0.04197 0.03265 -0.0267 0.1715 1.0000
10.750 1.1786 0.04358 0.03443 -0.0252 0.1616 1.0000
11.000 1.1876 0.04512 0.03601 -0.0237 0.1525 1.0000
11.250 1.1931 0.04698 0.03811 -0.0221 0.1435 1.0000
11.500 1.1986 0.04900 0.04033 -0.0206 0.1352 1.0000
11.750 1.2031 0.05074 0.04207 -0.0192 0.1270 1.0000
12.000 1.1993 0.05343 0.04510 -0.0178 0.1190 1.0000
12.250 1.1975 0.05577 0.04749 -0.0167 0.1113 1.0000
12.500 1.1888 0.05870 0.05063 -0.0158 0.1036 1.0000
12.750 1.1784 0.06201 0.05407 -0.0155 0.0961 1.0000
13.000 1.1685 0.06535 0.05747 -0.0156 0.0891 1.0000
13.250 1.1549 0.06980 0.06214 -0.0164 0.0826 1.0000
13.500 1.1440 0.07387 0.06624 -0.0174 0.0765 1.0000
13.750 1.1301 0.07913 0.07172 -0.0191 0.0712 1.0000
14.000 1.1176 0.08437 0.07711 -0.0211 0.0663 1.0000
14.250 1.1061 0.08959 0.08239 -0.0233 0.0617 1.0000
14.500 1.0897 0.09659 0.08964 -0.0265 0.0585 1.0000
14.750 1.0753 0.10339 0.09662 -0.0298 0.0556 1.0000
15.000 1.0694 0.10806 0.10119 -0.0322 0.0511 1.0000
15.250 1.0524 0.11630 0.10971 -0.0365 0.0501 1.0000
15.500 1.0319 0.12584 0.11942 -0.0417 0.0497 1.0000
15.750 1.0104 0.13622 0.12994 -0.0474 0.0500 1.0000
16.000 0.9874 0.14783 0.14159 -0.0538 0.0505 1.0000
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