HQ 2.5/8 AIRFOIL (hq258-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.5/8 AIRFOIL (hq258-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.76 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq258-il-1000000-n5.txt Download as CSV file: xf-hq258-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/8 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3957 0.09016 0.08857 -0.0272 1.0000 0.0049
-8.250 -0.3928 0.08679 0.08522 -0.0285 1.0000 0.0050
-8.000 -0.3912 0.08350 0.08195 -0.0296 1.0000 0.0050
-7.750 -0.3048 0.06454 0.06311 -0.0363 0.9906 0.0051
-7.500 -0.2969 0.05936 0.05793 -0.0407 0.9839 0.0051
-7.250 -0.2881 0.05388 0.05245 -0.0462 0.9742 0.0051
-7.000 -0.2806 0.04830 0.04685 -0.0529 0.9569 0.0051
-6.750 -0.2762 0.04249 0.04096 -0.0612 0.9354 0.0051
-6.500 -0.2719 0.03758 0.03593 -0.0648 0.9182 0.0051
-6.250 -0.2646 0.03294 0.03115 -0.0673 0.9048 0.0051
-6.000 -0.2543 0.02852 0.02658 -0.0691 0.8939 0.0051
-5.750 -0.2408 0.02423 0.02212 -0.0706 0.8843 0.0051
-5.500 -0.2248 0.02017 0.01786 -0.0716 0.8764 0.0052
-5.250 -0.2118 0.01373 0.01105 -0.0730 0.8684 0.0054
-5.000 -0.1903 0.02293 0.01960 -0.0801 0.8822 0.0058
-4.750 -0.1671 0.02020 0.01658 -0.0800 0.8743 0.0061
-4.500 -0.1425 0.01823 0.01430 -0.0799 0.8669 0.0065
-4.250 -0.1168 0.01647 0.01229 -0.0797 0.8596 0.0068
-4.000 -0.0906 0.01488 0.01046 -0.0793 0.8529 0.0072
-3.750 -0.0636 0.01314 0.00845 -0.0789 0.8459 0.0072
-3.250 -0.0088 0.01043 0.00534 -0.0777 0.8321 0.0044
-3.000 0.0179 0.00932 0.00406 -0.0773 0.8249 0.0040
-2.750 0.0448 0.00855 0.00315 -0.0769 0.8155 0.0038
-2.500 0.0720 0.00798 0.00244 -0.0766 0.8048 0.0036
-2.250 0.0995 0.00757 0.00188 -0.0764 0.7942 0.0034
-2.000 0.1272 0.00731 0.00149 -0.0762 0.7848 0.0033
-1.750 0.1550 0.00715 0.00123 -0.0761 0.7753 0.0033
-1.500 0.1828 0.00704 0.00104 -0.0760 0.7650 0.0034
-1.250 0.2104 0.00698 0.00089 -0.0758 0.7511 0.0038
-1.000 0.2376 0.00689 0.00077 -0.0756 0.7341 0.0252
-0.500 0.2922 0.00676 0.00064 -0.0755 0.7010 0.0755
-0.250 0.3164 0.00534 0.00062 -0.0758 0.6867 0.5727
0.000 0.3425 0.00519 0.00069 -0.0755 0.6702 0.6683
0.250 0.3694 0.00523 0.00071 -0.0753 0.6516 0.6950
0.500 0.3965 0.00529 0.00074 -0.0752 0.6316 0.7101
0.750 0.4238 0.00538 0.00077 -0.0751 0.6125 0.7197
1.000 0.4507 0.00548 0.00081 -0.0749 0.5893 0.7297
1.250 0.4774 0.00562 0.00086 -0.0747 0.5616 0.7393
1.500 0.5036 0.00581 0.00093 -0.0744 0.5240 0.7493
1.750 0.5294 0.00606 0.00103 -0.0741 0.4798 0.7602
2.000 0.5553 0.00629 0.00114 -0.0738 0.4409 0.7720
2.250 0.5815 0.00648 0.00125 -0.0736 0.4110 0.7847
2.500 0.6073 0.00669 0.00137 -0.0733 0.3770 0.7990
2.750 0.6329 0.00691 0.00150 -0.0730 0.3428 0.8150
3.000 0.6579 0.00716 0.00165 -0.0726 0.3037 0.8342
3.250 0.6823 0.00739 0.00182 -0.0720 0.2685 0.8596
3.500 0.7058 0.00738 0.00200 -0.0710 0.2490 0.9383
3.750 0.7373 0.00762 0.00216 -0.0721 0.2237 1.0000
4.000 0.7620 0.00806 0.00239 -0.0717 0.1783 1.0000
4.250 0.7844 0.00880 0.00273 -0.0711 0.1055 1.0000
4.500 0.8077 0.00944 0.00309 -0.0705 0.0542 1.0000
4.750 0.8296 0.01030 0.00367 -0.0697 0.0019 1.0000
5.000 0.8557 0.01056 0.00399 -0.0694 0.0015 1.0000
5.250 0.8816 0.01083 0.00430 -0.0692 0.0014 1.0000
5.500 0.9073 0.01114 0.00466 -0.0688 0.0013 1.0000
5.750 0.9327 0.01148 0.00506 -0.0684 0.0013 1.0000
6.000 0.9576 0.01190 0.00555 -0.0679 0.0013 1.0000
6.250 0.9821 0.01236 0.00610 -0.0674 0.0013 1.0000
6.500 1.0059 0.01295 0.00679 -0.0667 0.0013 1.0000
6.750 1.0290 0.01362 0.00756 -0.0659 0.0013 1.0000
7.000 1.0509 0.01445 0.00852 -0.0648 0.0014 1.0000
7.250 1.0721 0.01535 0.00959 -0.0637 0.0014 1.0000
7.500 1.0916 0.01649 0.01089 -0.0623 0.0014 1.0000
7.750 1.1103 0.01777 0.01232 -0.0608 0.0015 1.0000
8.000 1.1281 0.01924 0.01396 -0.0592 0.0015 1.0000
8.250 1.1449 0.02099 0.01589 -0.0575 0.0016 1.0000
8.500 1.1612 0.02291 0.01803 -0.0557 0.0016 1.0000
8.750 1.1763 0.02504 0.02038 -0.0539 0.0017 1.0000
9.000 1.1898 0.02729 0.02287 -0.0520 0.0017 1.0000
9.250 1.2023 0.02938 0.02519 -0.0500 0.0016 1.0000
9.500 1.2120 0.03163 0.02767 -0.0478 0.0016 1.0000
9.750 1.2220 0.03334 0.02956 -0.0458 0.0015 1.0000
10.000 1.2273 0.03543 0.03185 -0.0433 0.0014 1.0000
10.250 1.2244 0.03781 0.03445 -0.0398 0.0013 1.0000
10.500 1.2189 0.03982 0.03663 -0.0361 0.0013 1.0000
10.750 1.2190 0.04110 0.03801 -0.0337 0.0012 1.0000
11.000 1.2076 0.04401 0.04110 -0.0309 0.0012 1.0000
11.250 1.1855 0.04858 0.04594 -0.0286 0.0012 1.0000
11.500 1.1795 0.05131 0.04878 -0.0280 0.0012 1.0000
11.750 1.1593 0.05647 0.05414 -0.0283 0.0012 1.0000
12.000 1.1461 0.06117 0.05899 -0.0297 0.0012 1.0000
12.250 1.1254 0.06793 0.06591 -0.0328 0.0012 1.0000
12.500 1.1163 0.07337 0.07146 -0.0362 0.0011 1.0000
12.750 1.0903 0.08368 0.08195 -0.0431 0.0012 1.0000
13.000 1.0625 0.09655 0.09499 -0.0518 0.0013 1.0000
13.250 1.0262 0.11369 0.11229 -0.0621 0.0014 1.0000
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Polar data table (+)
Polar graphs
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