HQ 1.5/12 AIRFOIL (hq1512-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.5/12 AIRFOIL (hq1512-il) Reynolds number: 50,000 Max Cl/Cd: 33.63 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq1512-il-50000-n5.txt Download as CSV file: xf-hq1512-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/12 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5312 0.10621 0.09890 -0.0317 1.0000 0.0504
-11.250 -0.5354 0.10029 0.09303 -0.0345 1.0000 0.0502
-11.000 -0.5419 0.09393 0.08671 -0.0378 1.0000 0.0500
-10.750 -0.5533 0.08695 0.07977 -0.0420 1.0000 0.0497
-10.500 -0.5681 0.08030 0.07313 -0.0463 1.0000 0.0494
-10.250 -0.5868 0.07416 0.06697 -0.0502 1.0000 0.0490
-10.000 -0.6078 0.06892 0.06172 -0.0529 1.0000 0.0487
-9.750 -0.6290 0.06474 0.05746 -0.0536 1.0000 0.0485
-9.500 -0.6471 0.06097 0.05356 -0.0529 1.0000 0.0484
-9.250 -0.6604 0.05716 0.04951 -0.0519 1.0000 0.0486
-9.000 -0.6697 0.05348 0.04551 -0.0505 1.0000 0.0491
-8.750 -0.6748 0.05005 0.04166 -0.0487 1.0000 0.0500
-8.500 -0.6724 0.04716 0.03854 -0.0470 1.0000 0.0515
-8.250 -0.6644 0.04515 0.03646 -0.0454 1.0000 0.0538
-8.000 -0.6568 0.04288 0.03397 -0.0435 1.0000 0.0559
-7.750 -0.6479 0.04039 0.03117 -0.0415 1.0000 0.0577
-7.500 -0.6368 0.03799 0.02840 -0.0395 1.0000 0.0599
-7.250 -0.6243 0.03593 0.02594 -0.0374 1.0000 0.0632
-7.000 -0.6116 0.03452 0.02459 -0.0357 1.0000 0.0674
-6.750 -0.5972 0.03300 0.02286 -0.0337 1.0000 0.0722
-6.500 -0.5813 0.03147 0.02109 -0.0317 1.0000 0.0770
-6.250 -0.5678 0.03037 0.02001 -0.0298 1.0000 0.0840
-6.000 -0.5532 0.02922 0.01878 -0.0277 1.0000 0.0923
-5.750 -0.5387 0.02824 0.01768 -0.0257 1.0000 0.1034
-5.500 -0.5249 0.02726 0.01669 -0.0238 1.0000 0.1166
-5.250 -0.5114 0.02629 0.01580 -0.0220 1.0000 0.1329
-5.000 -0.4976 0.02535 0.01495 -0.0202 1.0000 0.1538
-4.750 -0.4833 0.02442 0.01413 -0.0187 1.0000 0.1835
-4.500 -0.4591 0.02335 0.01329 -0.0193 0.9960 0.2344
-4.250 -0.4302 0.02212 0.01256 -0.0208 0.9888 0.3176
-4.000 -0.4035 0.02139 0.01256 -0.0211 0.9816 0.4442
-3.750 -0.3770 0.02142 0.01286 -0.0203 0.9736 0.5467
-3.500 -0.3491 0.02169 0.01310 -0.0197 0.9658 0.6106
-3.250 -0.3202 0.02200 0.01329 -0.0193 0.9582 0.6574
-3.000 -0.2940 0.02226 0.01343 -0.0184 0.9502 0.6935
-2.750 -0.2646 0.02253 0.01355 -0.0179 0.9432 0.7248
-2.500 -0.2396 0.02267 0.01356 -0.0170 0.9350 0.7513
-2.250 -0.2086 0.02283 0.01359 -0.0169 0.9285 0.7745
-2.000 -0.1835 0.02289 0.01353 -0.0162 0.9203 0.7965
-1.750 -0.1514 0.02300 0.01353 -0.0163 0.9142 0.8198
-1.500 -0.1251 0.02306 0.01351 -0.0156 0.9063 0.8426
-1.250 -0.0881 0.02312 0.01345 -0.0170 0.9004 0.8618
-1.000 -0.0544 0.02313 0.01335 -0.0183 0.8930 0.8760
-0.750 -0.0145 0.02314 0.01327 -0.0208 0.8867 0.8889
-0.500 0.0249 0.02318 0.01320 -0.0234 0.8800 0.9015
-0.250 0.0657 0.02321 0.01317 -0.0262 0.8728 0.9139
0.000 0.1122 0.02325 0.01313 -0.0300 0.8669 0.9249
0.250 0.1550 0.02331 0.01316 -0.0334 0.8589 0.9365
0.500 0.2045 0.02330 0.01311 -0.0378 0.8530 0.9468
0.750 0.2468 0.02336 0.01317 -0.0412 0.8440 0.9589
1.000 0.2938 0.02335 0.01316 -0.0453 0.8367 0.9700
1.250 0.3387 0.02335 0.01319 -0.0491 0.8278 0.9820
1.500 0.3814 0.02332 0.01320 -0.0525 0.8174 0.9959
1.750 0.4063 0.02324 0.01313 -0.0523 0.8045 1.0000
2.000 0.4232 0.02312 0.01303 -0.0503 0.7892 1.0000
2.250 0.4408 0.02299 0.01289 -0.0484 0.7735 1.0000
2.500 0.4595 0.02289 0.01277 -0.0465 0.7583 1.0000
2.750 0.4797 0.02287 0.01278 -0.0450 0.7443 1.0000
3.000 0.5018 0.02289 0.01281 -0.0438 0.7308 1.0000
3.250 0.5251 0.02290 0.01285 -0.0427 0.7170 1.0000
3.500 0.5487 0.02291 0.01290 -0.0416 0.7023 1.0000
3.750 0.5722 0.02294 0.01300 -0.0405 0.6868 1.0000
4.000 0.5960 0.02295 0.01307 -0.0394 0.6702 1.0000
4.250 0.6204 0.02293 0.01312 -0.0383 0.6526 1.0000
4.500 0.6460 0.02286 0.01311 -0.0372 0.6342 1.0000
4.750 0.6679 0.02294 0.01330 -0.0358 0.6123 1.0000
5.000 0.6929 0.02288 0.01329 -0.0346 0.5897 1.0000
5.250 0.7150 0.02297 0.01345 -0.0331 0.5631 1.0000
5.750 0.7610 0.02318 0.01367 -0.0303 0.5030 1.0000
6.000 0.7828 0.02345 0.01386 -0.0288 0.4697 1.0000
6.250 0.8030 0.02388 0.01420 -0.0272 0.4356 1.0000
6.500 0.8220 0.02445 0.01462 -0.0256 0.4025 1.0000
6.750 0.8395 0.02514 0.01520 -0.0239 0.3707 1.0000
7.000 0.8557 0.02592 0.01587 -0.0223 0.3404 1.0000
7.250 0.8708 0.02680 0.01663 -0.0206 0.3115 1.0000
7.500 0.8852 0.02775 0.01750 -0.0189 0.2842 1.0000
7.750 0.8988 0.02878 0.01849 -0.0172 0.2579 1.0000
8.000 0.9117 0.02987 0.01958 -0.0155 0.2330 1.0000
8.250 0.9232 0.03103 0.02070 -0.0137 0.2092 1.0000
8.500 0.9349 0.03224 0.02195 -0.0120 0.1857 1.0000
8.750 0.9441 0.03351 0.02315 -0.0101 0.1665 1.0000
9.000 0.9540 0.03487 0.02448 -0.0083 0.1492 1.0000
9.250 0.9658 0.03633 0.02591 -0.0068 0.1364 1.0000
9.500 0.9800 0.03785 0.02745 -0.0055 0.1259 1.0000
9.750 0.9956 0.03944 0.02919 -0.0044 0.1161 1.0000
10.000 1.0094 0.04105 0.03082 -0.0033 0.1085 1.0000
10.250 1.0241 0.04275 0.03267 -0.0022 0.1015 1.0000
10.500 1.0437 0.04458 0.03450 -0.0016 0.0968 1.0000
10.750 1.0586 0.04672 0.03700 -0.0007 0.0921 1.0000
11.000 1.0697 0.04868 0.03909 0.0004 0.0877 1.0000
11.500 1.0861 0.05353 0.04442 0.0025 0.0810 1.0000
11.750 1.0887 0.05651 0.04772 0.0036 0.0788 1.0000
12.000 1.0884 0.05958 0.05106 0.0045 0.0768 1.0000
12.250 1.0876 0.06257 0.05423 0.0052 0.0748 1.0000
12.500 1.0964 0.06502 0.05667 0.0057 0.0721 1.0000
12.750 1.0801 0.06931 0.06126 0.0059 0.0712 1.0000
13.000 1.0593 0.07436 0.06662 0.0051 0.0707 1.0000
13.250 1.0351 0.08031 0.07285 0.0032 0.0704 1.0000
13.500 1.0079 0.08734 0.08009 0.0001 0.0704 1.0000
13.750 0.9769 0.09584 0.08877 -0.0045 0.0707 1.0000
14.000 0.9446 0.10586 0.09891 -0.0105 0.0713 1.0000
14.250 0.9112 0.11764 0.11071 -0.0178 0.0718 1.0000
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