HQ 3.0/12 AIRFOIL (hq3012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/12 AIRFOIL (hq3012-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.36 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3012-il-1000000-n5.txt Download as CSV file: xf-hq3012-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/12 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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.8535 0.04445 0.04192 -0.0791 1.0000 0.0042
-13.500 -0.8738 0.03864 0.03594 -0.0831 1.0000 0.0041
-13.250 -0.8936 0.03413 0.03126 -0.0850 1.0000 0.0041
-13.000 -0.9043 0.03169 0.02872 -0.0844 1.0000 0.0041
-12.750 -0.9050 0.02957 0.02648 -0.0846 0.9934 0.0042
-12.500 -0.8858 0.02755 0.02430 -0.0868 0.9867 0.0043
-12.250 -0.8628 0.02569 0.02226 -0.0892 0.9823 0.0044
-12.000 -0.8379 0.02429 0.02074 -0.0910 0.9766 0.0045
-11.750 -0.8107 0.02283 0.01913 -0.0931 0.9716 0.0046
-11.500 -0.7852 0.02183 0.01803 -0.0941 0.9635 0.0048
-11.250 -0.7609 0.02061 0.01665 -0.0950 0.9549 0.0049
-11.000 -0.7381 0.01967 0.01557 -0.0952 0.9437 0.0050
-10.750 -0.7167 0.01882 0.01459 -0.0948 0.9315 0.0051
-10.500 -0.6955 0.01803 0.01366 -0.0944 0.9201 0.0052
-10.250 -0.6736 0.01735 0.01284 -0.0939 0.9104 0.0054
-10.000 -0.6508 0.01681 0.01218 -0.0934 0.9012 0.0055
-9.750 -0.6279 0.01623 0.01149 -0.0929 0.8927 0.0057
-9.500 -0.6041 0.01577 0.01092 -0.0925 0.8846 0.0058
-9.250 -0.5802 0.01525 0.01031 -0.0921 0.8768 0.0059
-9.000 -0.5577 0.01451 0.00943 -0.0916 0.8692 0.0060
-8.750 -0.5348 0.01375 0.00854 -0.0911 0.8616 0.0062
-8.500 -0.5108 0.01317 0.00785 -0.0907 0.8551 0.0064
-8.250 -0.4858 0.01267 0.00728 -0.0904 0.8485 0.0066
-8.000 -0.4606 0.01224 0.00677 -0.0901 0.8421 0.0068
-7.750 -0.4349 0.01184 0.00630 -0.0899 0.8359 0.0070
-7.500 -0.4089 0.01148 0.00587 -0.0897 0.8295 0.0072
-7.250 -0.3828 0.01114 0.00546 -0.0895 0.8236 0.0075
-7.000 -0.3563 0.01083 0.00509 -0.0894 0.8172 0.0079
-6.750 -0.3298 0.01055 0.00475 -0.0892 0.8113 0.0082
-6.500 -0.3029 0.01027 0.00441 -0.0891 0.8052 0.0084
-6.250 -0.2763 0.00997 0.00404 -0.0889 0.7990 0.0089
-6.000 -0.2493 0.00969 0.00372 -0.0888 0.7933 0.0097
-5.750 -0.2222 0.00945 0.00344 -0.0888 0.7872 0.0105
-5.500 -0.1950 0.00925 0.00319 -0.0887 0.7815 0.0116
-5.250 -0.1677 0.00901 0.00295 -0.0886 0.7754 0.0151
-5.000 -0.1406 0.00878 0.00275 -0.0886 0.7696 0.0222
-4.750 -0.1128 0.00863 0.00259 -0.0886 0.7641 0.0269
-4.500 -0.0851 0.00851 0.00243 -0.0886 0.7580 0.0292
-4.250 -0.0575 0.00837 0.00228 -0.0886 0.7525 0.0331
-4.000 -0.0295 0.00825 0.00215 -0.0886 0.7465 0.0365
-3.750 -0.0018 0.00811 0.00201 -0.0886 0.7403 0.0423
-3.500 0.0261 0.00801 0.00189 -0.0886 0.7334 0.0462
-3.250 0.0538 0.00792 0.00177 -0.0886 0.7252 0.0519
-3.000 0.0817 0.00781 0.00166 -0.0886 0.7173 0.0593
-2.750 0.1094 0.00770 0.00156 -0.0886 0.7103 0.0734
-2.500 0.1373 0.00754 0.00146 -0.0886 0.7044 0.0934
-2.250 0.1651 0.00740 0.00137 -0.0887 0.6981 0.1174
-2.000 0.1927 0.00722 0.00129 -0.0887 0.6924 0.1570
-1.750 0.2202 0.00702 0.00121 -0.0888 0.6849 0.2053
-1.500 0.2476 0.00683 0.00114 -0.0888 0.6763 0.2582
-1.250 0.2744 0.00658 0.00106 -0.0888 0.6667 0.3290
-1.000 0.3011 0.00623 0.00101 -0.0888 0.6576 0.4405
-0.750 0.3284 0.00611 0.00101 -0.0887 0.6487 0.4946
-0.500 0.3560 0.00604 0.00102 -0.0887 0.6400 0.5364
-0.250 0.3837 0.00598 0.00106 -0.0887 0.6323 0.5783
0.000 0.4114 0.00600 0.00109 -0.0886 0.6229 0.5984
0.250 0.4394 0.00603 0.00110 -0.0886 0.6130 0.6082
0.750 0.4941 0.00618 0.00117 -0.0884 0.5814 0.6306
1.000 0.5209 0.00629 0.00122 -0.0881 0.5617 0.6398
1.250 0.5482 0.00639 0.00127 -0.0880 0.5454 0.6470
1.500 0.5751 0.00651 0.00133 -0.0879 0.5263 0.6526
1.750 0.6014 0.00667 0.00141 -0.0876 0.5032 0.6584
2.250 0.6537 0.00704 0.00160 -0.0870 0.4560 0.6697
2.500 0.6794 0.00726 0.00173 -0.0867 0.4303 0.6761
2.750 0.7051 0.00747 0.00186 -0.0863 0.4058 0.6820
3.000 0.7307 0.00769 0.00200 -0.0860 0.3828 0.6887
3.250 0.7562 0.00792 0.00215 -0.0856 0.3594 0.6951
3.500 0.7812 0.00817 0.00231 -0.0852 0.3330 0.7020
4.000 0.8318 0.00863 0.00264 -0.0844 0.2936 0.7164
4.500 0.8822 0.00906 0.00300 -0.0836 0.2620 0.7317
4.750 0.9076 0.00927 0.00318 -0.0832 0.2487 0.7399
5.000 0.9323 0.00950 0.00338 -0.0828 0.2336 0.7485
5.250 0.9570 0.00973 0.00358 -0.0823 0.2194 0.7570
5.500 0.9813 0.00998 0.00379 -0.0818 0.2045 0.7666
5.750 1.0043 0.01030 0.00405 -0.0810 0.1847 0.7767
6.000 1.0271 0.01063 0.00432 -0.0803 0.1653 0.7875
6.250 1.0492 0.01098 0.00461 -0.0794 0.1469 0.7998
6.500 1.0717 0.01128 0.00489 -0.0786 0.1327 0.8142
6.750 1.0927 0.01163 0.00520 -0.0775 0.1154 0.8328
7.000 1.1130 0.01193 0.00552 -0.0762 0.1009 0.8604
7.250 1.1386 0.01214 0.00587 -0.0761 0.0863 1.0000
7.500 1.1596 0.01257 0.00622 -0.0751 0.0736 1.0000
7.750 1.1786 0.01312 0.00666 -0.0738 0.0574 1.0000
8.000 1.1981 0.01361 0.00709 -0.0726 0.0461 1.0000
8.250 1.2156 0.01421 0.00760 -0.0710 0.0328 1.0000
8.500 1.2321 0.01482 0.00814 -0.0693 0.0217 1.0000
8.750 1.2483 0.01532 0.00861 -0.0675 0.0163 1.0000
9.000 1.2621 0.01591 0.00916 -0.0653 0.0100 1.0000
9.250 1.2740 0.01662 0.00985 -0.0628 0.0041 1.0000
9.500 1.2901 0.01711 0.01036 -0.0610 0.0035 1.0000
9.750 1.3060 0.01761 0.01092 -0.0593 0.0033 1.0000
10.000 1.3215 0.01815 0.01150 -0.0576 0.0031 1.0000
10.250 1.3362 0.01874 0.01213 -0.0559 0.0029 1.0000
10.500 1.3508 0.01935 0.01279 -0.0542 0.0028 1.0000
10.750 1.3633 0.02011 0.01362 -0.0522 0.0025 1.0000
11.000 1.3753 0.02092 0.01450 -0.0504 0.0024 1.0000
11.250 1.3877 0.02172 0.01535 -0.0486 0.0023 1.0000
11.500 1.4002 0.02254 0.01623 -0.0470 0.0023 1.0000
11.750 1.4122 0.02341 0.01717 -0.0454 0.0022 1.0000
12.000 1.4237 0.02434 0.01816 -0.0438 0.0022 1.0000
12.250 1.4344 0.02535 0.01923 -0.0423 0.0021 1.0000
12.500 1.4441 0.02646 0.02041 -0.0407 0.0021 1.0000
12.750 1.4530 0.02768 0.02170 -0.0392 0.0019 1.0000
13.000 1.4619 0.02892 0.02301 -0.0378 0.0019 1.0000
13.250 1.4693 0.03033 0.02450 -0.0364 0.0018 1.0000
13.500 1.4763 0.03182 0.02605 -0.0351 0.0018 1.0000
13.750 1.4818 0.03348 0.02780 -0.0339 0.0017 1.0000
14.000 1.4863 0.03529 0.02971 -0.0327 0.0017 1.0000
14.250 1.4898 0.03725 0.03176 -0.0317 0.0017 1.0000
14.500 1.4933 0.03928 0.03387 -0.0308 0.0016 1.0000
14.750 1.4954 0.04152 0.03621 -0.0301 0.0016 1.0000
15.000 1.4962 0.04399 0.03877 -0.0295 0.0016 1.0000
15.250 1.4951 0.04678 0.04166 -0.0291 0.0015 1.0000
15.500 1.4946 0.04961 0.04459 -0.0289 0.0015 1.0000
15.750 1.4915 0.05289 0.04798 -0.0290 0.0015 1.0000
16.000 1.4867 0.05654 0.05174 -0.0293 0.0014 1.0000
16.250 1.4792 0.06073 0.05605 -0.0300 0.0015 1.0000
16.500 1.4743 0.06473 0.06017 -0.0309 0.0014 1.0000
16.750 1.4656 0.06951 0.06507 -0.0323 0.0014 1.0000
17.000 1.4521 0.07523 0.07093 -0.0342 0.0014 1.0000
17.250 1.4427 0.08056 0.07639 -0.0363 0.0014 1.0000
17.500 1.4288 0.08690 0.08286 -0.0389 0.0014 1.0000
17.750 1.4136 0.09367 0.08977 -0.0420 0.0014 1.0000
18.000 1.3989 0.10059 0.09682 -0.0453 0.0014 1.0000
18.250 1.3817 0.10818 0.10456 -0.0491 0.0014 1.0000
18.500 1.3615 0.11655 0.11307 -0.0535 0.0014 1.0000
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