HQ 1.5/9 B AIRFOIL (hq159b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.5/9 B AIRFOIL (hq159b-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.21 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq159b-il-1000000-n5.txt Download as CSV file: xf-hq159b-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/9 B 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.8500 0.02863 0.02579 -0.0479 1.0000 0.0022
-10.000 -0.8495 0.02427 0.02094 -0.0465 1.0000 0.0023
-9.750 -0.8413 0.02107 0.01731 -0.0450 1.0000 0.0024
-9.500 -0.8251 0.01936 0.01538 -0.0439 1.0000 0.0025
-9.250 -0.8065 0.01816 0.01401 -0.0429 1.0000 0.0025
-9.000 -0.7819 0.01714 0.01285 -0.0430 0.9980 0.0027
-8.750 -0.7530 0.01626 0.01187 -0.0439 0.9928 0.0028
-8.500 -0.7232 0.01546 0.01093 -0.0449 0.9882 0.0030
-8.250 -0.6925 0.01457 0.00991 -0.0460 0.9833 0.0031
-8.000 -0.6621 0.01380 0.00903 -0.0470 0.9775 0.0033
-7.750 -0.6309 0.01315 0.00827 -0.0481 0.9713 0.0035
-7.500 -0.6009 0.01249 0.00751 -0.0489 0.9638 0.0037
-7.250 -0.5718 0.01191 0.00682 -0.0495 0.9552 0.0038
-7.000 -0.5451 0.01143 0.00624 -0.0494 0.9440 0.0040
-6.750 -0.5190 0.01101 0.00574 -0.0491 0.9321 0.0041
-6.500 -0.4931 0.01066 0.00527 -0.0488 0.9199 0.0042
-6.250 -0.4681 0.01012 0.00459 -0.0483 0.9070 0.0047
-6.000 -0.4425 0.00973 0.00412 -0.0479 0.8943 0.0056
-5.750 -0.4165 0.00944 0.00376 -0.0475 0.8831 0.0064
-5.500 -0.3902 0.00919 0.00343 -0.0473 0.8733 0.0073
-5.250 -0.3635 0.00893 0.00312 -0.0470 0.8640 0.0098
-5.000 -0.3369 0.00871 0.00287 -0.0468 0.8547 0.0138
-4.750 -0.3101 0.00852 0.00266 -0.0466 0.8451 0.0187
-4.500 -0.2828 0.00838 0.00245 -0.0465 0.8360 0.0212
-4.250 -0.2557 0.00820 0.00227 -0.0464 0.8279 0.0253
-4.000 -0.2283 0.00806 0.00209 -0.0463 0.8193 0.0278
-3.750 -0.2008 0.00793 0.00193 -0.0463 0.8109 0.0311
-3.500 -0.1735 0.00778 0.00178 -0.0462 0.8022 0.0375
-3.250 -0.1459 0.00763 0.00162 -0.0461 0.7935 0.0458
-3.000 -0.1183 0.00752 0.00149 -0.0461 0.7850 0.0535
-2.500 -0.0637 0.00724 0.00124 -0.0459 0.7621 0.0860
-2.000 -0.0096 0.00680 0.00100 -0.0458 0.7383 0.1775
-1.750 0.0178 0.00664 0.00091 -0.0458 0.7276 0.2147
-1.500 0.0442 0.00625 0.00080 -0.0458 0.7169 0.3110
-1.250 0.0704 0.00582 0.00071 -0.0457 0.7061 0.4323
-1.000 0.0977 0.00565 0.00067 -0.0457 0.6952 0.4846
-0.750 0.1247 0.00546 0.00065 -0.0456 0.6839 0.5521
-0.500 0.1520 0.00539 0.00065 -0.0454 0.6709 0.5948
-0.250 0.1793 0.00536 0.00067 -0.0453 0.6547 0.6289
0.000 0.2068 0.00538 0.00068 -0.0452 0.6383 0.6491
0.250 0.2345 0.00540 0.00070 -0.0451 0.6237 0.6661
0.500 0.2622 0.00544 0.00072 -0.0451 0.6094 0.6787
0.750 0.2899 0.00550 0.00074 -0.0450 0.5929 0.6890
1.000 0.3175 0.00556 0.00077 -0.0449 0.5722 0.6983
1.250 0.3434 0.00582 0.00084 -0.0446 0.5144 0.7074
1.500 0.3687 0.00619 0.00095 -0.0443 0.4472 0.7153
1.750 0.3949 0.00645 0.00106 -0.0440 0.4003 0.7244
2.000 0.4198 0.00688 0.00120 -0.0437 0.3198 0.7351
2.250 0.4453 0.00725 0.00137 -0.0434 0.2637 0.7450
2.500 0.4719 0.00745 0.00149 -0.0432 0.2374 0.7530
2.750 0.4988 0.00762 0.00161 -0.0431 0.2187 0.7613
3.000 0.5257 0.00777 0.00174 -0.0430 0.2018 0.7709
3.250 0.5525 0.00791 0.00187 -0.0428 0.1862 0.7812
3.500 0.5782 0.00820 0.00203 -0.0425 0.1490 0.7936
3.750 0.6029 0.00858 0.00227 -0.0421 0.1047 0.8096
4.000 0.6280 0.00886 0.00251 -0.0417 0.0790 0.8287
4.250 0.6527 0.00912 0.00276 -0.0411 0.0546 0.8508
4.500 0.6759 0.00947 0.00305 -0.0403 0.0280 0.8798
4.750 0.6996 0.00953 0.00326 -0.0393 0.0252 0.9318
5.000 0.7362 0.00973 0.00351 -0.0414 0.0239 1.0000
5.250 0.7626 0.00997 0.00377 -0.0412 0.0231 1.0000
5.500 0.7887 0.01024 0.00407 -0.0409 0.0219 1.0000
5.750 0.8145 0.01054 0.00439 -0.0407 0.0202 1.0000
6.000 0.8400 0.01089 0.00478 -0.0403 0.0192 1.0000
6.250 0.8663 0.01109 0.00499 -0.0402 0.0189 1.0000
6.500 0.8926 0.01129 0.00520 -0.0400 0.0183 1.0000
6.750 0.9186 0.01152 0.00546 -0.0398 0.0173 1.0000
7.000 0.9443 0.01178 0.00574 -0.0396 0.0155 1.0000
7.250 0.9697 0.01209 0.00604 -0.0393 0.0130 1.0000
7.500 0.9945 0.01245 0.00641 -0.0389 0.0106 1.0000
7.750 1.0192 0.01283 0.00680 -0.0385 0.0081 1.0000
8.000 1.0432 0.01329 0.00725 -0.0380 0.0058 1.0000
8.250 1.0673 0.01372 0.00773 -0.0376 0.0053 1.0000
8.500 1.0910 0.01417 0.00823 -0.0370 0.0048 1.0000
8.750 1.1142 0.01469 0.00878 -0.0365 0.0043 1.0000
9.000 1.1368 0.01526 0.00940 -0.0358 0.0038 1.0000
9.250 1.1586 0.01593 0.01015 -0.0350 0.0034 1.0000
9.500 1.1792 0.01671 0.01105 -0.0340 0.0032 1.0000
9.750 1.2011 0.01728 0.01169 -0.0333 0.0031 1.0000
10.000 1.2219 0.01796 0.01246 -0.0324 0.0030 1.0000
10.250 1.2424 0.01863 0.01322 -0.0315 0.0029 1.0000
10.500 1.2621 0.01936 0.01403 -0.0306 0.0027 1.0000
10.750 1.2812 0.02009 0.01485 -0.0295 0.0025 1.0000
11.000 1.2998 0.02085 0.01570 -0.0285 0.0024 1.0000
11.250 1.3169 0.02169 0.01664 -0.0272 0.0023 1.0000
11.500 1.3341 0.02247 0.01749 -0.0260 0.0021 1.0000
11.750 1.3484 0.02344 0.01856 -0.0244 0.0020 1.0000
12.000 1.3623 0.02436 0.01956 -0.0228 0.0020 1.0000
12.250 1.3693 0.02550 0.02083 -0.0202 0.0019 1.0000
12.500 1.3715 0.02686 0.02232 -0.0170 0.0018 1.0000
12.750 1.3704 0.02850 0.02412 -0.0139 0.0017 1.0000
13.000 1.3681 0.03034 0.02612 -0.0112 0.0017 1.0000
13.250 1.3616 0.03269 0.02865 -0.0087 0.0016 1.0000
13.500 1.3609 0.03471 0.03080 -0.0071 0.0016 1.0000
13.750 1.3598 0.03693 0.03317 -0.0059 0.0016 1.0000
14.000 1.3578 0.03938 0.03576 -0.0051 0.0016 1.0000
14.250 1.3526 0.04238 0.03890 -0.0048 0.0016 1.0000
14.500 1.3449 0.04594 0.04262 -0.0050 0.0016 1.0000
14.750 1.3262 0.05126 0.04814 -0.0062 0.0016 1.0000
15.000 1.3175 0.05572 0.05273 -0.0079 0.0016 1.0000
15.250 1.3011 0.06184 0.05901 -0.0109 0.0016 1.0000
15.500 1.2864 0.06836 0.06568 -0.0145 0.0016 1.0000
15.750 1.2671 0.07640 0.07388 -0.0194 0.0016 1.0000
16.000 1.2325 0.08844 0.08612 -0.0268 0.0016 1.0000
16.250 1.1808 0.10508 0.10296 -0.0367 0.0016 1.0000
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Polar data table (+)
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