HQ 3.0/10 AIRFOIL (hq3010-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/10 AIRFOIL (hq3010-il) Reynolds number: 50,000 Max Cl/Cd: 39.77 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3010-il-50000-n5.txt Download as CSV file: xf-hq3010-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/10 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3873 0.11879 0.11177 -0.0363 1.0000 0.0950
-9.750 -0.3919 0.11607 0.10915 -0.0384 1.0000 0.0953
-9.500 -0.3945 0.11300 0.10617 -0.0400 1.0000 0.0955
-9.250 -0.3737 0.10400 0.09707 -0.0403 1.0000 0.0528
-9.000 -0.3681 0.10045 0.09357 -0.0397 1.0000 0.0507
-8.750 -0.3682 0.09709 0.09029 -0.0401 1.0000 0.0494
-8.500 -0.3705 0.09386 0.08716 -0.0406 1.0000 0.0485
-8.250 -0.3754 0.09069 0.08410 -0.0410 1.0000 0.0481
-7.750 -0.4136 0.08176 0.07545 -0.0474 1.0000 0.0410
-7.500 -0.4206 0.07863 0.07239 -0.0471 1.0000 0.0408
-7.250 -0.4273 0.07555 0.06935 -0.0466 1.0000 0.0406
-7.000 -0.4335 0.07242 0.06622 -0.0462 1.0000 0.0404
-6.750 -0.4390 0.06902 0.06278 -0.0463 1.0000 0.0404
-6.500 -0.4420 0.06543 0.05908 -0.0465 1.0000 0.0405
-6.250 -0.4419 0.06165 0.05510 -0.0471 1.0000 0.0407
-6.000 -0.4373 0.05797 0.05118 -0.0474 1.0000 0.0408
-5.750 -0.4290 0.05426 0.04714 -0.0479 1.0000 0.0411
-5.500 -0.4175 0.05059 0.04318 -0.0483 1.0000 0.0412
-5.000 -0.3858 0.04344 0.03526 -0.0490 1.0000 0.0414
-4.750 -0.3629 0.04000 0.03141 -0.0501 0.9987 0.0419
-4.500 -0.3299 0.03680 0.02775 -0.0525 0.9943 0.0432
-4.250 -0.2970 0.03425 0.02479 -0.0544 0.9897 0.0455
-4.000 -0.2619 0.03222 0.02219 -0.0562 0.9853 0.0511
-3.750 -0.2294 0.03023 0.01981 -0.0572 0.9807 0.0562
-3.500 -0.1967 0.02879 0.01813 -0.0582 0.9759 0.0646
-3.250 -0.1634 0.02746 0.01665 -0.0591 0.9718 0.0768
-3.000 -0.1339 0.02644 0.01543 -0.0595 0.9659 0.0953
-2.750 -0.1012 0.02541 0.01442 -0.0609 0.9609 0.1187
-2.500 -0.0678 0.02445 0.01339 -0.0624 0.9557 0.1457
-2.250 -0.0348 0.02294 0.01258 -0.0646 0.9503 0.2640
-2.000 -0.0129 0.02198 0.01313 -0.0626 0.9452 0.6449
-1.750 0.0044 0.02204 0.01325 -0.0594 0.9371 0.7399
-1.500 0.0207 0.02189 0.01325 -0.0551 0.9308 0.8416
-1.250 0.0670 0.02152 0.01285 -0.0573 0.9248 1.0000
-1.000 0.1044 0.02170 0.01266 -0.0603 0.9183 1.0000
-0.750 0.1349 0.02189 0.01255 -0.0618 0.9098 1.0000
-0.500 0.1745 0.02211 0.01246 -0.0648 0.9037 1.0000
-0.250 0.2036 0.02235 0.01247 -0.0659 0.8945 1.0000
0.000 0.2422 0.02258 0.01248 -0.0685 0.8881 1.0000
0.250 0.2722 0.02283 0.01255 -0.0694 0.8788 1.0000
0.500 0.3041 0.02308 0.01265 -0.0707 0.8701 1.0000
0.750 0.3412 0.02328 0.01272 -0.0727 0.8626 1.0000
1.000 0.3694 0.02354 0.01288 -0.0732 0.8524 1.0000
1.250 0.4037 0.02374 0.01300 -0.0745 0.8441 1.0000
1.500 0.4365 0.02392 0.01313 -0.0756 0.8350 1.0000
1.750 0.4641 0.02417 0.01335 -0.0757 0.8242 1.0000
2.000 0.4949 0.02434 0.01350 -0.0763 0.8141 1.0000
2.250 0.5326 0.02429 0.01345 -0.0777 0.8054 1.0000
2.750 0.5909 0.02436 0.01359 -0.0775 0.7796 1.0000
3.250 0.6498 0.02432 0.01365 -0.0772 0.7532 1.0000
3.500 0.6791 0.02428 0.01372 -0.0769 0.7395 1.0000
3.750 0.7085 0.02419 0.01372 -0.0766 0.7251 1.0000
4.000 0.7384 0.02404 0.01366 -0.0762 0.7098 1.0000
4.250 0.7687 0.02381 0.01353 -0.0757 0.6934 1.0000
4.500 0.7924 0.02384 0.01371 -0.0744 0.6726 1.0000
4.750 0.8218 0.02361 0.01358 -0.0737 0.6527 1.0000
5.000 0.8457 0.02363 0.01372 -0.0724 0.6287 1.0000
5.250 0.8711 0.02362 0.01380 -0.0712 0.6033 1.0000
5.500 0.8961 0.02365 0.01396 -0.0700 0.5753 1.0000
5.750 0.9209 0.02375 0.01409 -0.0688 0.5444 1.0000
6.000 0.9455 0.02392 0.01424 -0.0675 0.5115 1.0000
6.250 0.9671 0.02432 0.01463 -0.0660 0.4762 1.0000
6.500 0.9884 0.02485 0.01506 -0.0645 0.4417 1.0000
6.750 1.0075 0.02558 0.01580 -0.0630 0.4077 1.0000
7.000 1.0258 0.02642 0.01658 -0.0614 0.3759 1.0000
7.250 1.0432 0.02736 0.01747 -0.0599 0.3462 1.0000
7.500 1.0598 0.02835 0.01845 -0.0583 0.3184 1.0000
7.750 1.0753 0.02943 0.01951 -0.0567 0.2918 1.0000
8.000 1.0901 0.03056 0.02064 -0.0550 0.2667 1.0000
8.250 1.1037 0.03176 0.02182 -0.0533 0.2431 1.0000
8.500 1.1159 0.03299 0.02319 -0.0515 0.2199 1.0000
8.750 1.1275 0.03429 0.02454 -0.0497 0.1988 1.0000
9.000 1.1371 0.03566 0.02596 -0.0476 0.1792 1.0000
9.250 1.1455 0.03716 0.02745 -0.0456 0.1615 1.0000
9.500 1.1550 0.03878 0.02920 -0.0438 0.1442 1.0000
9.750 1.1660 0.04055 0.03109 -0.0421 0.1298 1.0000
10.000 1.1738 0.04241 0.03305 -0.0403 0.1164 1.0000
10.250 1.1800 0.04438 0.03511 -0.0386 0.1046 1.0000
10.500 1.1876 0.04651 0.03727 -0.0370 0.0951 1.0000
10.750 1.1901 0.04879 0.03975 -0.0354 0.0850 1.0000
11.000 1.1879 0.05128 0.04244 -0.0339 0.0752 1.0000
11.250 1.1859 0.05406 0.04541 -0.0327 0.0672 1.0000
11.500 1.1814 0.05705 0.04850 -0.0319 0.0602 1.0000
11.750 1.1754 0.06054 0.05222 -0.0314 0.0531 1.0000
12.000 1.1669 0.06413 0.05584 -0.0315 0.0480 1.0000
12.250 1.1610 0.06832 0.06030 -0.0315 0.0436 1.0000
12.500 1.1539 0.07277 0.06500 -0.0319 0.0401 1.0000
12.750 1.1464 0.07723 0.06958 -0.0328 0.0379 1.0000
13.000 1.1383 0.08187 0.07421 -0.0339 0.0360 1.0000
13.250 1.1273 0.08775 0.08046 -0.0357 0.0347 1.0000
13.500 1.1144 0.09411 0.08713 -0.0382 0.0339 1.0000
13.750 1.0999 0.10114 0.09444 -0.0416 0.0334 1.0000
14.000 1.0845 0.10877 0.10230 -0.0455 0.0334 1.0000
14.250 1.0681 0.11718 0.11092 -0.0502 0.0336 1.0000
14.500 1.0510 0.12633 0.12023 -0.0555 0.0342 1.0000
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