HQ 2.5/9 B AIRFOIL (hq259b-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.5/9 B AIRFOIL (hq259b-il) Reynolds number: 50,000 Max Cl/Cd: 39.05 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq259b-il-50000.txt Download as CSV file: xf-hq259b-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/9 B 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 -0.4123 0.10678 0.09970 -0.0194 1.0000 0.2418
-8.750 -0.4351 0.10672 0.09982 -0.0211 1.0000 0.2506
-8.500 -0.4269 0.10321 0.09635 -0.0201 1.0000 0.2651
-8.250 -0.4219 0.10015 0.09333 -0.0191 1.0000 0.2798
-8.000 -0.3975 0.09538 0.08853 -0.0168 1.0000 0.3008
-7.750 -0.3981 0.09331 0.08655 -0.0154 1.0000 0.3218
-7.500 -0.3912 0.09031 0.08361 -0.0136 1.0000 0.3429
-7.250 -0.3916 0.08842 0.08181 -0.0115 1.0000 0.3668
-7.000 -0.3757 0.08493 0.07834 -0.0094 1.0000 0.3914
-6.750 -0.3733 0.08260 0.07610 -0.0069 1.0000 0.4163
-6.500 -0.3853 0.08184 0.07548 -0.0033 1.0000 0.4414
-6.250 -0.3769 0.07926 0.07294 -0.0003 1.0000 0.4709
-6.000 -0.3461 0.07482 0.06847 0.0011 1.0000 0.5059
-5.750 -0.3353 0.07234 0.06603 0.0040 1.0000 0.5415
-4.750 -0.3962 0.04437 0.03643 -0.0465 1.0000 0.1626
-4.500 -0.3699 0.04042 0.03191 -0.0474 1.0000 0.1456
-4.250 -0.3466 0.03729 0.02846 -0.0476 1.0000 0.1416
-4.000 -0.3209 0.03463 0.02530 -0.0479 1.0000 0.1400
-3.750 -0.2939 0.03222 0.02234 -0.0479 1.0000 0.1373
-3.500 -0.2669 0.03019 0.01983 -0.0476 1.0000 0.1361
-3.250 -0.2413 0.02850 0.01786 -0.0471 1.0000 0.1385
-3.000 -0.2156 0.02726 0.01626 -0.0464 1.0000 0.1462
-2.750 -0.1915 0.02579 0.01480 -0.0454 1.0000 0.1537
-2.500 -0.1680 0.02469 0.01357 -0.0441 1.0000 0.1634
-2.250 -0.1449 0.02356 0.01252 -0.0430 1.0000 0.1850
-2.000 -0.1187 0.02224 0.01140 -0.0427 1.0000 0.2248
-1.750 -0.1121 0.01943 0.01149 -0.0361 1.0000 0.7449
-1.500 -0.1107 0.01862 0.01095 -0.0269 1.0000 1.0000
-1.250 -0.0847 0.01873 0.01051 -0.0278 1.0000 1.0000
-1.000 -0.0586 0.01889 0.01025 -0.0288 1.0000 1.0000
-0.750 -0.0328 0.01912 0.01012 -0.0296 1.0000 1.0000
-0.500 -0.0075 0.01939 0.01009 -0.0303 1.0000 1.0000
-0.250 0.0172 0.01969 0.01013 -0.0308 1.0000 1.0000
0.000 0.0413 0.02004 0.01025 -0.0312 1.0000 1.0000
0.250 0.0650 0.02042 0.01045 -0.0316 1.0000 1.0000
0.500 0.0881 0.02084 0.01071 -0.0318 1.0000 1.0000
0.750 0.1108 0.02130 0.01102 -0.0320 1.0000 1.0000
1.000 0.1330 0.02180 0.01141 -0.0322 1.0000 1.0000
1.250 0.1547 0.02235 0.01187 -0.0324 1.0000 1.0000
1.500 0.1759 0.02295 0.01240 -0.0325 1.0000 1.0000
1.750 0.1964 0.02361 0.01302 -0.0327 1.0000 1.0000
2.000 0.2162 0.02435 0.01373 -0.0329 1.0000 1.0000
2.250 0.2351 0.02518 0.01456 -0.0331 1.0000 1.0000
2.500 0.2945 0.02684 0.01627 -0.0409 0.9779 1.0000
2.750 0.3556 0.02830 0.01781 -0.0484 0.9530 1.0000
3.000 0.4167 0.02946 0.01910 -0.0554 0.9270 1.0000
3.250 0.4710 0.03024 0.02005 -0.0606 0.8988 1.0000
3.500 0.5246 0.03076 0.02076 -0.0651 0.8699 1.0000
3.750 0.5781 0.03096 0.02121 -0.0689 0.8407 1.0000
4.000 0.6319 0.03082 0.02132 -0.0721 0.8117 1.0000
4.250 0.6854 0.03029 0.02111 -0.0745 0.7832 1.0000
4.500 0.7339 0.02948 0.02056 -0.0754 0.7545 1.0000
4.750 0.7799 0.02836 0.01969 -0.0753 0.7250 1.0000
5.000 0.8249 0.02681 0.01840 -0.0743 0.6932 1.0000
5.250 0.8569 0.02573 0.01746 -0.0718 0.6545 1.0000
5.500 0.8884 0.02461 0.01638 -0.0691 0.6118 1.0000
5.750 0.9172 0.02389 0.01558 -0.0663 0.5637 1.0000
6.000 0.9407 0.02409 0.01556 -0.0636 0.5089 1.0000
6.250 0.9614 0.02500 0.01611 -0.0609 0.4471 1.0000
6.500 0.9768 0.02648 0.01720 -0.0579 0.3761 1.0000
6.750 0.9909 0.02828 0.01856 -0.0550 0.3065 1.0000
7.000 1.0064 0.02994 0.01985 -0.0526 0.2535 1.0000
7.250 1.0232 0.03161 0.02126 -0.0507 0.2128 1.0000
7.500 1.0435 0.03369 0.02319 -0.0493 0.1817 1.0000
7.750 1.0663 0.03610 0.02562 -0.0483 0.1591 1.0000
8.000 1.0909 0.03889 0.02837 -0.0477 0.1431 1.0000
8.250 1.1113 0.04213 0.03214 -0.0463 0.1340 1.0000
8.500 1.1300 0.04539 0.03562 -0.0452 0.1256 1.0000
8.750 1.1434 0.04883 0.03957 -0.0435 0.1200 1.0000
9.000 1.1598 0.05272 0.04371 -0.0423 0.1168 1.0000
9.250 1.1706 0.05735 0.04863 -0.0410 0.1145 1.0000
9.500 1.1676 0.06168 0.05357 -0.0385 0.1135 1.0000
9.750 1.1599 0.06626 0.05865 -0.0362 0.1129 1.0000
10.000 1.1478 0.07104 0.06382 -0.0341 0.1128 1.0000
10.250 1.1331 0.07594 0.06901 -0.0325 0.1132 1.0000
10.500 1.1172 0.08088 0.07415 -0.0311 0.1139 1.0000
10.750 1.1048 0.08603 0.07942 -0.0302 0.1146 1.0000
11.000 1.0152 0.09638 0.09002 -0.0350 0.1267 1.0000
11.250 1.0060 0.10317 0.09683 -0.0372 0.1281 1.0000
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Polar data table (+)
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