HAM-STD HS1-404 AIRFOIL (hs1404-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: HAM-STD HS1-404 AIRFOIL (hs1404-il) Reynolds number: 50,000 Max Cl/Cd: 42.53 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hs1404-il-50000-n5.txt Download as CSV file: xf-hs1404-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HAM-STD HS1-404 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3770 0.10572 0.09914 -0.0176 1.0000 0.0810
-8.500 -0.3812 0.10369 0.09720 -0.0195 1.0000 0.0815
-8.250 -0.3851 0.10152 0.09511 -0.0214 1.0000 0.0818
-8.000 -0.3666 0.09440 0.08799 -0.0190 1.0000 0.0838
-7.750 -0.3616 0.09063 0.08427 -0.0190 1.0000 0.0855
-7.500 -0.3592 0.08726 0.08082 -0.0193 1.0000 0.0870
-7.250 -0.3585 0.08407 0.07771 -0.0196 1.0000 0.0887
-7.000 -0.3588 0.08102 0.07474 -0.0203 1.0000 0.0905
-6.750 -0.3607 0.07849 0.07231 -0.0241 1.0000 0.0939
-6.500 -0.3582 0.07554 0.06941 -0.0289 1.0000 0.0947
-6.250 -0.3517 0.07172 0.06562 -0.0319 1.0000 0.0949
-6.000 -0.3442 0.06650 0.06047 -0.0261 1.0000 0.0886
-5.750 -0.3339 0.06032 0.05422 -0.0303 1.0000 0.0480
-5.500 -0.3433 0.06752 0.06071 -0.0409 1.0000 0.0412
-5.250 -0.3276 0.06353 0.05672 -0.0426 1.0000 0.0390
-5.000 -0.3063 0.05918 0.05229 -0.0461 1.0000 0.0369
-4.750 -0.2807 0.05446 0.04745 -0.0504 1.0000 0.0349
-4.500 -0.2502 0.04926 0.04201 -0.0553 1.0000 0.0330
-4.000 -0.1819 0.03923 0.03106 -0.0634 1.0000 0.0302
-3.750 -0.1521 0.03525 0.02664 -0.0657 1.0000 0.0299
-3.500 -0.1212 0.03160 0.02244 -0.0675 1.0000 0.0299
-3.250 -0.0905 0.02844 0.01866 -0.0686 1.0000 0.0300
-3.000 -0.0621 0.02596 0.01581 -0.0694 1.0000 0.0331
-2.750 -0.0345 0.02426 0.01369 -0.0694 1.0000 0.0396
-2.500 -0.0062 0.02247 0.01145 -0.0693 1.0000 0.0449
-2.250 0.0222 0.02103 0.00966 -0.0689 1.0000 0.0526
-2.000 0.0521 0.01974 0.00829 -0.0691 1.0000 0.0989
-1.750 0.0793 0.01925 0.00801 -0.0692 1.0000 0.2166
-1.500 0.1059 0.01864 0.00729 -0.0691 1.0000 0.2694
-1.250 0.1327 0.01802 0.00670 -0.0691 1.0000 0.3215
-1.000 0.1603 0.01702 0.00629 -0.0696 1.0000 0.4439
-0.750 0.1718 0.01580 0.00598 -0.0658 1.0000 1.0000
-0.500 0.1971 0.01601 0.00578 -0.0655 1.0000 1.0000
-0.250 0.2220 0.01624 0.00558 -0.0652 1.0000 1.0000
0.000 0.2465 0.01649 0.00559 -0.0650 1.0000 1.0000
0.250 0.2708 0.01677 0.00568 -0.0647 1.0000 1.0000
0.500 0.2949 0.01707 0.00584 -0.0645 1.0000 1.0000
0.750 0.3187 0.01740 0.00607 -0.0642 1.0000 1.0000
1.000 0.3424 0.01775 0.00637 -0.0640 1.0000 1.0000
1.250 0.3658 0.01814 0.00674 -0.0639 1.0000 1.0000
1.500 0.3891 0.01856 0.00720 -0.0637 1.0000 1.0000
1.750 0.4214 0.01900 0.00768 -0.0654 0.9950 1.0000
2.000 0.4680 0.01939 0.00818 -0.0697 0.9808 1.0000
2.250 0.5130 0.01968 0.00864 -0.0735 0.9641 1.0000
2.500 0.5556 0.01993 0.00911 -0.0766 0.9484 1.0000
2.750 0.5967 0.02015 0.00978 -0.0793 0.9333 1.0000
3.000 0.6396 0.02029 0.01027 -0.0821 0.9180 1.0000
3.250 0.6778 0.02038 0.01073 -0.0837 0.8992 1.0000
3.500 0.7179 0.02030 0.01111 -0.0851 0.8781 1.0000
3.750 0.7567 0.01917 0.01037 -0.0830 0.8118 1.0000
4.000 0.7788 0.01831 0.00930 -0.0769 0.6345 1.0000
4.250 0.7904 0.02010 0.00957 -0.0715 0.3385 1.0000
4.500 0.8020 0.02328 0.01121 -0.0697 0.1260 1.0000
4.750 0.8230 0.02535 0.01316 -0.0684 0.0943 1.0000
5.000 0.8447 0.02719 0.01498 -0.0675 0.0712 1.0000
5.250 0.8683 0.02914 0.01717 -0.0661 0.0614 1.0000
5.500 0.8954 0.03163 0.01994 -0.0648 0.0555 1.0000
5.750 0.9212 0.03448 0.02293 -0.0639 0.0475 1.0000
6.000 0.9461 0.03708 0.02609 -0.0627 0.0389 1.0000
6.250 0.9689 0.04080 0.03014 -0.0616 0.0356 1.0000
6.500 0.9886 0.04541 0.03526 -0.0601 0.0340 1.0000
6.750 1.0057 0.04952 0.04015 -0.0581 0.0327 1.0000
7.000 1.0184 0.05366 0.04502 -0.0562 0.0300 1.0000
7.250 1.0275 0.05750 0.04956 -0.0547 0.0263 1.0000
7.500 1.0345 0.06127 0.05357 -0.0536 0.0241 1.0000
7.750 1.0371 0.06602 0.05870 -0.0521 0.0238 1.0000
8.000 1.0362 0.07082 0.06386 -0.0509 0.0237 1.0000
8.250 1.0318 0.07563 0.06899 -0.0499 0.0239 1.0000
8.500 1.0218 0.08063 0.07429 -0.0494 0.0242 1.0000
8.750 1.0073 0.08559 0.07946 -0.0493 0.0247 1.0000
9.000 0.9909 0.09088 0.08487 -0.0506 0.0253 1.0000
|
Polar data table (+)
Polar graphs
<< Back to HAM-STD HS1-404 AIRFOIL (hs1404-il)