HQ 1.5/9 AIRFOIL (hq159-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.5/9 AIRFOIL (hq159-il) Reynolds number: 1,000,000 Max Cl/Cd: 79.17 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq159-il-1000000-n5.txt Download as CSV file: xf-hq159-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/9 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.7653 0.03198 0.02957 -0.0472 1.0000 0.0024
-9.250 -0.7653 0.02734 0.02450 -0.0458 1.0000 0.0024
-9.000 -0.7590 0.02376 0.02050 -0.0442 1.0000 0.0024
-8.750 -0.7450 0.02098 0.01734 -0.0432 0.9990 0.0025
-8.500 -0.7194 0.01878 0.01482 -0.0441 0.9932 0.0025
-8.250 -0.6915 0.01707 0.01284 -0.0451 0.9884 0.0026
-8.000 -0.6617 0.01568 0.01123 -0.0462 0.9839 0.0026
-7.750 -0.6324 0.01464 0.01002 -0.0471 0.9775 0.0027
-7.500 -0.6010 0.01380 0.00904 -0.0483 0.9716 0.0027
-7.250 -0.5737 0.01236 0.00739 -0.0487 0.9614 0.0032
-7.000 -0.5448 0.01189 0.00684 -0.0492 0.9508 0.0035
-6.750 -0.5174 0.01145 0.00631 -0.0493 0.9380 0.0037
-6.500 -0.4913 0.01104 0.00581 -0.0490 0.9243 0.0041
-6.250 -0.4657 0.01064 0.00531 -0.0486 0.9114 0.0045
-6.000 -0.4400 0.01030 0.00487 -0.0482 0.9000 0.0048
-5.750 -0.4140 0.01002 0.00450 -0.0479 0.8894 0.0051
-5.500 -0.3881 0.00960 0.00398 -0.0475 0.8793 0.0056
-5.250 -0.3620 0.00926 0.00357 -0.0473 0.8701 0.0067
-5.000 -0.3355 0.00902 0.00326 -0.0470 0.8616 0.0076
-4.750 -0.3086 0.00880 0.00297 -0.0468 0.8531 0.0083
-4.500 -0.2817 0.00859 0.00270 -0.0467 0.8455 0.0088
-4.250 -0.2547 0.00836 0.00240 -0.0465 0.8373 0.0109
-4.000 -0.2277 0.00812 0.00218 -0.0463 0.8297 0.0171
-3.750 -0.2006 0.00792 0.00197 -0.0462 0.8217 0.0268
-3.500 -0.1732 0.00776 0.00181 -0.0461 0.8136 0.0344
-3.250 -0.1459 0.00762 0.00166 -0.0460 0.8049 0.0428
-3.000 -0.1188 0.00747 0.00151 -0.0459 0.7945 0.0565
-2.750 -0.0914 0.00733 0.00138 -0.0458 0.7839 0.0720
-2.500 -0.0644 0.00710 0.00124 -0.0457 0.7747 0.1075
-2.000 -0.0104 0.00661 0.00100 -0.0456 0.7555 0.2074
-1.750 0.0161 0.00632 0.00089 -0.0455 0.7421 0.2764
-1.500 0.0424 0.00602 0.00078 -0.0454 0.7275 0.3585
-1.250 0.0690 0.00576 0.00071 -0.0453 0.7146 0.4364
-1.000 0.0957 0.00554 0.00068 -0.0452 0.7024 0.5088
-0.750 0.1228 0.00542 0.00066 -0.0450 0.6896 0.5587
-0.500 0.1497 0.00533 0.00066 -0.0449 0.6759 0.6062
-0.250 0.1771 0.00533 0.00067 -0.0447 0.6614 0.6311
0.000 0.2046 0.00535 0.00067 -0.0446 0.6452 0.6493
0.250 0.2322 0.00537 0.00069 -0.0445 0.6309 0.6653
0.500 0.2597 0.00541 0.00071 -0.0444 0.6151 0.6796
0.750 0.2870 0.00545 0.00074 -0.0443 0.5971 0.6963
1.000 0.3143 0.00552 0.00077 -0.0442 0.5764 0.7096
1.250 0.3416 0.00561 0.00082 -0.0440 0.5534 0.7186
1.500 0.3686 0.00573 0.00087 -0.0439 0.5271 0.7271
1.750 0.3954 0.00590 0.00094 -0.0437 0.4944 0.7364
2.000 0.4217 0.00611 0.00103 -0.0435 0.4543 0.7455
2.250 0.4475 0.00639 0.00115 -0.0432 0.4058 0.7550
2.750 0.4980 0.00708 0.00146 -0.0425 0.2927 0.7763
3.000 0.5235 0.00739 0.00163 -0.0422 0.2508 0.7878
3.250 0.5499 0.00756 0.00177 -0.0420 0.2301 0.7998
3.500 0.5764 0.00770 0.00191 -0.0418 0.2152 0.8123
3.750 0.6028 0.00784 0.00205 -0.0415 0.1997 0.8256
4.000 0.6282 0.00809 0.00223 -0.0411 0.1686 0.8402
4.250 0.6528 0.00839 0.00243 -0.0406 0.1346 0.8578
4.500 0.6753 0.00881 0.00272 -0.0398 0.0871 0.8838
4.750 0.7017 0.00900 0.00298 -0.0395 0.0650 0.9490
5.000 0.7366 0.00932 0.00324 -0.0413 0.0491 1.0000
5.250 0.7621 0.00964 0.00349 -0.0410 0.0371 1.0000
5.500 0.7877 0.00995 0.00375 -0.0408 0.0275 1.0000
5.750 0.8131 0.01027 0.00403 -0.0404 0.0199 1.0000
6.000 0.8384 0.01061 0.00435 -0.0401 0.0145 1.0000
6.250 0.8628 0.01106 0.00475 -0.0396 0.0056 1.0000
6.500 0.8877 0.01145 0.00514 -0.0392 0.0040 1.0000
6.750 0.9126 0.01184 0.00556 -0.0388 0.0032 1.0000
7.000 0.9373 0.01225 0.00603 -0.0383 0.0028 1.0000
7.250 0.9617 0.01269 0.00653 -0.0378 0.0025 1.0000
7.500 0.9862 0.01308 0.00697 -0.0374 0.0023 1.0000
7.750 1.0104 0.01351 0.00747 -0.0369 0.0022 1.0000
8.000 1.0341 0.01400 0.00802 -0.0363 0.0021 1.0000
8.250 1.0573 0.01453 0.00862 -0.0357 0.0020 1.0000
8.500 1.0801 0.01511 0.00928 -0.0350 0.0019 1.0000
8.750 1.1027 0.01568 0.00992 -0.0343 0.0018 1.0000
9.000 1.1246 0.01633 0.01064 -0.0335 0.0017 1.0000
9.250 1.1460 0.01700 0.01139 -0.0327 0.0016 1.0000
9.500 1.1668 0.01772 0.01220 -0.0318 0.0015 1.0000
9.750 1.1874 0.01842 0.01297 -0.0310 0.0014 1.0000
10.000 1.2062 0.01931 0.01399 -0.0298 0.0014 1.0000
10.250 1.2245 0.02020 0.01498 -0.0287 0.0013 1.0000
10.500 1.2400 0.02136 0.01626 -0.0272 0.0012 1.0000
10.750 1.2429 0.02377 0.01896 -0.0241 0.0010 1.0000
11.000 1.2546 0.02507 0.02040 -0.0222 0.0010 1.0000
11.250 1.2674 0.02611 0.02156 -0.0205 0.0010 1.0000
11.500 1.2769 0.02710 0.02266 -0.0182 0.0010 1.0000
11.750 1.2784 0.02854 0.02425 -0.0150 0.0010 1.0000
12.000 1.2817 0.02990 0.02573 -0.0124 0.0010 1.0000
12.250 1.2810 0.03165 0.02764 -0.0099 0.0010 1.0000
12.500 1.2811 0.03346 0.02959 -0.0078 0.0009 1.0000
12.750 1.2750 0.03597 0.03227 -0.0060 0.0010 1.0000
13.000 1.2703 0.03857 0.03503 -0.0048 0.0009 1.0000
13.250 1.2646 0.04152 0.03813 -0.0041 0.0009 1.0000
13.500 1.2514 0.04560 0.04238 -0.0043 0.0009 1.0000
13.750 1.2426 0.04960 0.04654 -0.0051 0.0009 1.0000
14.000 1.2273 0.05495 0.05207 -0.0071 0.0009 1.0000
14.250 1.2110 0.06112 0.05840 -0.0102 0.0009 1.0000
14.500 1.1889 0.06924 0.06670 -0.0150 0.0009 1.0000
14.750 1.1707 0.07751 0.07510 -0.0202 0.0009 1.0000
15.000 1.1421 0.08894 0.08672 -0.0273 0.0009 1.0000
15.250 1.1127 0.10080 0.09872 -0.0342 0.0010 1.0000
15.500 1.0775 0.11410 0.11214 -0.0415 0.0010 1.0000
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