HQ 1.0/12 AIRFOIL (hq1012-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.0/12 AIRFOIL (hq1012-il) Reynolds number: 100,000 Max Cl/Cd: 47.11 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq1012-il-100000.txt Download as CSV file: xf-hq1012-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.0/12 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5648 0.09039 0.08551 -0.0283 1.0000 0.1039
-10.000 -0.5656 0.08772 0.08289 -0.0292 1.0000 0.1174
-9.750 -0.7473 0.05952 0.05379 -0.0455 1.0000 0.0600
-9.500 -0.7551 0.05553 0.04952 -0.0440 1.0000 0.0600
-9.250 -0.7613 0.05147 0.04513 -0.0422 1.0000 0.0603
-9.000 -0.7616 0.04729 0.04061 -0.0404 1.0000 0.0604
-8.750 -0.7590 0.04292 0.03590 -0.0386 1.0000 0.0609
-8.500 -0.7507 0.03944 0.03222 -0.0369 1.0000 0.0623
-8.250 -0.7367 0.03742 0.03016 -0.0355 1.0000 0.0655
-8.000 -0.7268 0.03530 0.02770 -0.0332 1.0000 0.0695
-7.750 -0.7176 0.03333 0.02510 -0.0303 1.0000 0.0726
-7.500 -0.7034 0.03053 0.02231 -0.0288 1.0000 0.0769
-7.250 -0.6900 0.02925 0.02084 -0.0266 1.0000 0.0835
-7.000 -0.6761 0.02733 0.01878 -0.0245 1.0000 0.0893
-6.750 -0.6626 0.02631 0.01764 -0.0223 1.0000 0.0971
-6.500 -0.6480 0.02487 0.01618 -0.0203 1.0000 0.1044
-6.250 -0.6338 0.02406 0.01514 -0.0182 1.0000 0.1131
-6.000 -0.6179 0.02278 0.01400 -0.0165 1.0000 0.1218
-5.750 -0.6024 0.02181 0.01302 -0.0147 1.0000 0.1320
-5.500 -0.5864 0.02095 0.01213 -0.0129 1.0000 0.1433
-5.250 -0.5707 0.02012 0.01141 -0.0112 1.0000 0.1581
-5.000 -0.5552 0.01934 0.01080 -0.0096 1.0000 0.1781
-4.750 -0.5398 0.01849 0.01014 -0.0079 1.0000 0.2084
-4.500 -0.5259 0.01739 0.00947 -0.0062 1.0000 0.2666
-4.250 -0.5143 0.01614 0.00903 -0.0042 1.0000 0.3799
-4.000 -0.5023 0.01564 0.00920 -0.0015 1.0000 0.5106
-3.750 -0.4823 0.01584 0.00960 0.0001 0.9980 0.5902
-3.500 -0.4478 0.01639 0.01012 -0.0008 0.9906 0.6467
-3.250 -0.4130 0.01696 0.01063 -0.0018 0.9834 0.6877
-3.000 -0.3827 0.01744 0.01108 -0.0017 0.9756 0.7188
-2.750 -0.3474 0.01798 0.01155 -0.0024 0.9691 0.7481
-2.500 -0.3223 0.01831 0.01188 -0.0011 0.9606 0.7714
-2.250 -0.2892 0.01869 0.01220 -0.0013 0.9541 0.7959
-2.000 -0.2647 0.01886 0.01232 -0.0002 0.9454 0.8156
-1.750 -0.2303 0.01903 0.01241 -0.0011 0.9390 0.8336
-1.500 -0.2043 0.01908 0.01240 -0.0007 0.9303 0.8499
-1.250 -0.1685 0.01919 0.01243 -0.0020 0.9240 0.8655
-1.000 -0.1403 0.01929 0.01249 -0.0017 0.9155 0.8823
-0.750 -0.0903 0.01955 0.01271 -0.0050 0.9112 0.8997
-0.500 -0.0530 0.01975 0.01287 -0.0066 0.9031 0.9151
-0.250 0.0021 0.01985 0.01291 -0.0119 0.8983 0.9256
0.000 0.0656 0.01995 0.01296 -0.0188 0.8937 0.9313
0.250 0.1118 0.01999 0.01297 -0.0227 0.8861 0.9408
0.500 0.1842 0.01981 0.01277 -0.0311 0.8823 0.9441
0.750 0.2367 0.01961 0.01258 -0.0357 0.8716 0.9510
1.000 0.2917 0.01917 0.01215 -0.0403 0.8604 0.9569
1.250 0.3478 0.01861 0.01160 -0.0449 0.8494 0.9623
1.500 0.3910 0.01827 0.01130 -0.0475 0.8379 0.9704
1.750 0.4349 0.01803 0.01111 -0.0507 0.8256 0.9785
2.000 0.4772 0.01775 0.01087 -0.0535 0.8129 0.9867
2.250 0.5190 0.01743 0.01063 -0.0562 0.7998 0.9953
2.500 0.5491 0.01718 0.01042 -0.0567 0.7857 1.0000
2.750 0.5639 0.01706 0.01032 -0.0543 0.7714 1.0000
3.000 0.5782 0.01693 0.01024 -0.0519 0.7565 1.0000
3.250 0.5921 0.01678 0.01012 -0.0492 0.7408 1.0000
3.500 0.6056 0.01662 0.00998 -0.0464 0.7245 1.0000
3.750 0.6192 0.01641 0.00978 -0.0435 0.7073 1.0000
4.000 0.6341 0.01616 0.00952 -0.0406 0.6893 1.0000
4.250 0.6477 0.01600 0.00938 -0.0376 0.6677 1.0000
4.500 0.6657 0.01575 0.00909 -0.0351 0.6445 1.0000
4.750 0.6836 0.01560 0.00890 -0.0327 0.6158 1.0000
5.000 0.7025 0.01549 0.00874 -0.0304 0.5811 1.0000
5.250 0.7220 0.01549 0.00862 -0.0283 0.5394 1.0000
5.500 0.7406 0.01572 0.00866 -0.0262 0.4912 1.0000
5.750 0.7591 0.01619 0.00886 -0.0243 0.4445 1.0000
6.000 0.7777 0.01681 0.00923 -0.0226 0.4029 1.0000
6.250 0.7964 0.01751 0.00973 -0.0210 0.3664 1.0000
6.500 0.8151 0.01827 0.01030 -0.0196 0.3330 1.0000
6.750 0.8336 0.01910 0.01098 -0.0182 0.3008 1.0000
7.000 0.8517 0.02006 0.01178 -0.0168 0.2697 1.0000
7.250 0.8694 0.02110 0.01266 -0.0154 0.2394 1.0000
7.500 0.8872 0.02213 0.01361 -0.0140 0.2122 1.0000
7.750 0.9050 0.02315 0.01447 -0.0126 0.1891 1.0000
8.000 0.9235 0.02420 0.01554 -0.0113 0.1689 1.0000
8.250 0.9422 0.02529 0.01659 -0.0101 0.1520 1.0000
8.500 0.9615 0.02650 0.01778 -0.0090 0.1379 1.0000
8.750 0.9808 0.02782 0.01911 -0.0079 0.1252 1.0000
9.000 1.0003 0.02929 0.02062 -0.0070 0.1139 1.0000
9.250 1.0205 0.03094 0.02220 -0.0062 0.1036 1.0000
9.500 1.0383 0.03241 0.02380 -0.0050 0.0946 1.0000
9.750 1.0548 0.03437 0.02598 -0.0037 0.0861 1.0000
10.000 1.0748 0.03675 0.02826 -0.0032 0.0785 1.0000
10.250 1.0839 0.03838 0.03031 -0.0009 0.0721 1.0000
10.500 1.1010 0.04123 0.03313 -0.0004 0.0662 1.0000
10.750 1.1027 0.04322 0.03564 0.0025 0.0623 1.0000
11.000 1.1103 0.04537 0.03797 0.0044 0.0583 1.0000
11.250 1.1198 0.04907 0.04167 0.0052 0.0547 1.0000
11.500 1.1086 0.05144 0.04449 0.0087 0.0534 1.0000
11.750 1.0927 0.05407 0.04749 0.0123 0.0521 1.0000
12.000 1.0770 0.05730 0.05102 0.0147 0.0515 1.0000
12.250 1.0581 0.06093 0.05493 0.0162 0.0508 1.0000
12.500 1.0366 0.06529 0.05956 0.0167 0.0509 1.0000
12.750 1.0133 0.07027 0.06477 0.0160 0.0512 1.0000
13.000 0.9860 0.07620 0.07092 0.0140 0.0516 1.0000
13.250 0.9561 0.08326 0.07817 0.0105 0.0521 1.0000
13.500 0.9314 0.09083 0.08586 0.0064 0.0534 1.0000
13.750 0.9064 0.09933 0.09444 0.0014 0.0543 1.0000
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