HQ 2.0/12 AIRFOIL (hq2012-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.0/12 AIRFOIL (hq2012-il) Reynolds number: 500,000 Max Cl/Cd: 79.48 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2012-il-500000-n5.txt Download as CSV file: xf-hq2012-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/12 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.7488 0.08808 0.08530 -0.0382 1.0000 0.0064
-14.250 -0.7987 0.07340 0.07046 -0.0469 1.0000 0.0063
-14.000 -0.8323 0.06208 0.05897 -0.0545 1.0000 0.0061
-13.750 -0.8532 0.05416 0.05087 -0.0603 1.0000 0.0061
-13.500 -0.8681 0.04832 0.04486 -0.0643 1.0000 0.0062
-13.250 -0.8821 0.04333 0.03969 -0.0672 1.0000 0.0062
-13.000 -0.8908 0.03951 0.03569 -0.0689 1.0000 0.0063
-12.750 -0.9020 0.03592 0.03195 -0.0697 1.0000 0.0062
-12.500 -0.9028 0.03368 0.02956 -0.0697 1.0000 0.0063
-12.250 -0.9083 0.03141 0.02713 -0.0688 1.0000 0.0064
-12.000 -0.9096 0.02991 0.02550 -0.0669 1.0000 0.0065
-11.750 -0.9126 0.02845 0.02390 -0.0639 1.0000 0.0065
-11.500 -0.9117 0.02680 0.02210 -0.0615 1.0000 0.0066
-11.250 -0.9077 0.02533 0.02051 -0.0591 1.0000 0.0068
-11.000 -0.8991 0.02422 0.01930 -0.0570 1.0000 0.0070
-10.750 -0.8778 0.02305 0.01802 -0.0573 0.9955 0.0072
-10.500 -0.8509 0.02198 0.01683 -0.0585 0.9884 0.0075
-10.250 -0.8211 0.02091 0.01565 -0.0601 0.9833 0.0078
-10.000 -0.7926 0.02002 0.01464 -0.0612 0.9760 0.0082
-9.750 -0.7618 0.01916 0.01365 -0.0627 0.9699 0.0086
-9.500 -0.7329 0.01834 0.01269 -0.0637 0.9608 0.0090
-9.250 -0.7046 0.01738 0.01161 -0.0647 0.9514 0.0094
-9.000 -0.6766 0.01652 0.01066 -0.0654 0.9412 0.0099
-8.750 -0.6500 0.01589 0.00994 -0.0657 0.9295 0.0104
-8.500 -0.6244 0.01532 0.00927 -0.0656 0.9185 0.0110
-8.250 -0.5995 0.01480 0.00863 -0.0653 0.9086 0.0115
-8.000 -0.5748 0.01434 0.00806 -0.0649 0.8994 0.0123
-7.750 -0.5511 0.01381 0.00746 -0.0644 0.8904 0.0134
-7.500 -0.5264 0.01340 0.00700 -0.0640 0.8827 0.0148
-7.250 -0.5016 0.01302 0.00654 -0.0635 0.8749 0.0165
-7.000 -0.4767 0.01263 0.00610 -0.0631 0.8680 0.0187
-6.750 -0.4511 0.01232 0.00574 -0.0628 0.8610 0.0218
-6.500 -0.4256 0.01200 0.00539 -0.0625 0.8547 0.0252
-6.250 -0.3994 0.01175 0.00509 -0.0622 0.8482 0.0287
-6.000 -0.3735 0.01147 0.00478 -0.0619 0.8419 0.0325
-5.750 -0.3472 0.01123 0.00452 -0.0617 0.8360 0.0366
-5.500 -0.3207 0.01100 0.00423 -0.0615 0.8295 0.0402
-5.250 -0.2944 0.01076 0.00398 -0.0613 0.8238 0.0458
-5.000 -0.2676 0.01054 0.00374 -0.0611 0.8174 0.0512
-4.750 -0.2411 0.01030 0.00350 -0.0609 0.8114 0.0596
-4.500 -0.2144 0.01007 0.00327 -0.0608 0.8052 0.0691
-4.250 -0.1875 0.00986 0.00306 -0.0606 0.7989 0.0796
-4.000 -0.1607 0.00963 0.00285 -0.0605 0.7930 0.0944
-3.750 -0.1338 0.00940 0.00267 -0.0604 0.7865 0.1151
-3.500 -0.1073 0.00915 0.00248 -0.0602 0.7805 0.1450
-3.250 -0.0806 0.00887 0.00232 -0.0601 0.7738 0.1804
-3.000 -0.0538 0.00864 0.00217 -0.0600 0.7674 0.2156
-2.750 -0.0270 0.00838 0.00202 -0.0599 0.7607 0.2569
-2.500 -0.0015 0.00795 0.00184 -0.0597 0.7536 0.3353
-2.250 0.0236 0.00748 0.00172 -0.0595 0.7462 0.4451
-2.000 0.0504 0.00732 0.00166 -0.0592 0.7387 0.4925
-1.750 0.0775 0.00720 0.00163 -0.0591 0.7305 0.5314
-1.500 0.1045 0.00714 0.00161 -0.0588 0.7212 0.5632
-1.250 0.1320 0.00712 0.00159 -0.0586 0.7105 0.5854
-1.000 0.1595 0.00711 0.00158 -0.0585 0.7013 0.6040
-0.500 0.2149 0.00712 0.00157 -0.0582 0.6833 0.6335
-0.250 0.2426 0.00714 0.00157 -0.0581 0.6746 0.6446
0.000 0.2701 0.00716 0.00158 -0.0579 0.6648 0.6564
0.250 0.2976 0.00718 0.00160 -0.0578 0.6539 0.6693
0.500 0.3252 0.00722 0.00162 -0.0576 0.6434 0.6786
0.750 0.3527 0.00727 0.00164 -0.0575 0.6315 0.6846
1.000 0.3803 0.00733 0.00166 -0.0574 0.6199 0.6912
1.250 0.4078 0.00737 0.00169 -0.0573 0.6080 0.6973
1.500 0.4353 0.00742 0.00173 -0.0571 0.5963 0.7039
1.750 0.4626 0.00749 0.00178 -0.0570 0.5827 0.7101
2.000 0.4894 0.00758 0.00184 -0.0567 0.5659 0.7170
2.250 0.5160 0.00769 0.00190 -0.0565 0.5475 0.7239
2.500 0.5425 0.00781 0.00199 -0.0562 0.5283 0.7309
2.750 0.5684 0.00797 0.00209 -0.0558 0.5038 0.7383
3.000 0.5937 0.00817 0.00221 -0.0553 0.4760 0.7457
3.250 0.6187 0.00840 0.00235 -0.0548 0.4467 0.7533
3.500 0.6431 0.00867 0.00252 -0.0542 0.4148 0.7613
3.750 0.6673 0.00897 0.00271 -0.0536 0.3805 0.7693
4.000 0.6906 0.00933 0.00293 -0.0529 0.3409 0.7781
4.250 0.7140 0.00968 0.00316 -0.0522 0.3062 0.7869
4.500 0.7377 0.01000 0.00340 -0.0516 0.2814 0.7967
4.750 0.7613 0.01031 0.00364 -0.0509 0.2595 0.8073
5.000 0.7848 0.01059 0.00389 -0.0502 0.2408 0.8186
5.250 0.8090 0.01081 0.00412 -0.0496 0.2272 0.8316
5.500 0.8333 0.01097 0.00433 -0.0490 0.2175 0.8469
5.750 0.8568 0.01114 0.00455 -0.0482 0.2077 0.8664
6.000 0.8796 0.01130 0.00478 -0.0472 0.1951 0.9015
6.250 0.9188 0.01156 0.00508 -0.0500 0.1775 1.0000
6.500 0.9425 0.01189 0.00536 -0.0494 0.1623 1.0000
6.750 0.9655 0.01227 0.00566 -0.0487 0.1442 1.0000
7.000 0.9867 0.01278 0.00604 -0.0478 0.1205 1.0000
7.250 1.0069 0.01336 0.00649 -0.0468 0.0976 1.0000
7.500 1.0270 0.01393 0.00696 -0.0457 0.0782 1.0000
7.750 1.0469 0.01450 0.00743 -0.0447 0.0635 1.0000
8.000 1.0680 0.01496 0.00786 -0.0437 0.0554 1.0000
8.250 1.0886 0.01543 0.00832 -0.0427 0.0491 1.0000
8.500 1.1090 0.01589 0.00879 -0.0417 0.0437 1.0000
8.750 1.1288 0.01638 0.00927 -0.0406 0.0395 1.0000
9.000 1.1488 0.01682 0.00973 -0.0395 0.0364 1.0000
9.250 1.1671 0.01735 0.01025 -0.0382 0.0325 1.0000
9.500 1.1846 0.01783 0.01076 -0.0367 0.0300 1.0000
9.750 1.2014 0.01828 0.01126 -0.0351 0.0280 1.0000
10.000 1.2172 0.01879 0.01182 -0.0334 0.0259 1.0000
10.250 1.2315 0.01941 0.01243 -0.0315 0.0232 1.0000
10.500 1.2468 0.01996 0.01304 -0.0299 0.0215 1.0000
10.750 1.2600 0.02067 0.01374 -0.0281 0.0177 1.0000
11.000 1.2720 0.02147 0.01454 -0.0262 0.0138 1.0000
11.250 1.2839 0.02229 0.01540 -0.0244 0.0113 1.0000
11.500 1.2907 0.02349 0.01658 -0.0222 0.0062 1.0000
11.750 1.2997 0.02457 0.01771 -0.0204 0.0053 1.0000
12.000 1.3075 0.02579 0.01901 -0.0186 0.0045 1.0000
12.250 1.3165 0.02696 0.02026 -0.0170 0.0042 1.0000
12.500 1.3248 0.02822 0.02161 -0.0155 0.0040 1.0000
12.750 1.3325 0.02956 0.02305 -0.0142 0.0039 1.0000
13.000 1.3388 0.03108 0.02466 -0.0128 0.0037 1.0000
13.250 1.3436 0.03278 0.02647 -0.0115 0.0035 1.0000
13.500 1.3489 0.03449 0.02828 -0.0105 0.0034 1.0000
13.750 1.3518 0.03649 0.03040 -0.0095 0.0033 1.0000
14.000 1.3540 0.03862 0.03265 -0.0087 0.0032 1.0000
14.250 1.3566 0.04080 0.03494 -0.0081 0.0032 1.0000
14.500 1.3539 0.04364 0.03791 -0.0076 0.0031 1.0000
14.750 1.3547 0.04620 0.04060 -0.0074 0.0031 1.0000
15.000 1.3524 0.04922 0.04376 -0.0075 0.0031 1.0000
15.250 1.3488 0.05255 0.04722 -0.0078 0.0030 1.0000
15.500 1.3455 0.05601 0.05081 -0.0084 0.0030 1.0000
15.750 1.3400 0.05996 0.05489 -0.0094 0.0030 1.0000
16.000 1.3322 0.06442 0.05950 -0.0108 0.0030 1.0000
16.250 1.3249 0.06904 0.06425 -0.0125 0.0030 1.0000
16.500 1.3140 0.07449 0.06985 -0.0147 0.0029 1.0000
16.750 1.3010 0.08052 0.07604 -0.0174 0.0029 1.0000
17.000 1.2879 0.08684 0.08251 -0.0205 0.0029 1.0000
17.250 1.2722 0.09390 0.08972 -0.0241 0.0029 1.0000
17.500 1.2540 0.10165 0.09763 -0.0281 0.0029 1.0000
17.750 1.2354 0.10974 0.10587 -0.0324 0.0029 1.0000
18.000 1.2178 0.11777 0.11404 -0.0368 0.0029 1.0000
18.250 1.1986 0.12622 0.12262 -0.0415 0.0030 1.0000
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