HAM-STD HS1-404 AIRFOIL (hs1404-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HAM-STD HS1-404 AIRFOIL (hs1404-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.34 at α=1.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hs1404-il-1000000-n5.txt Download as CSV file: xf-hs1404-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4500 0.09662 0.09499 -0.0075 1.0000 0.0031
-7.750 -0.4442 0.09327 0.09166 -0.0091 1.0000 0.0031
-7.500 -0.4391 0.09001 0.08841 -0.0107 1.0000 0.0031
-7.250 -0.4319 0.08654 0.08497 -0.0131 1.0000 0.0031
-7.000 -0.4214 0.08277 0.08121 -0.0165 1.0000 0.0031
-6.750 -0.4101 0.07895 0.07741 -0.0201 1.0000 0.0031
-6.500 -0.3989 0.07517 0.07363 -0.0234 1.0000 0.0030
-6.250 -0.3736 0.07001 0.06842 -0.0308 0.9964 0.0030
-6.000 -0.3446 0.06437 0.06276 -0.0391 0.9918 0.0030
-5.750 -0.3124 0.05747 0.05580 -0.0493 0.9856 0.0025
-5.500 -0.2762 0.05124 0.04950 -0.0583 0.9800 0.0022
-5.250 -0.2379 0.04484 0.04297 -0.0668 0.9727 0.0020
-5.000 -0.1980 0.03803 0.03599 -0.0744 0.9653 0.0018
-4.750 -0.1574 0.03019 0.02787 -0.0808 0.9570 0.0017
-4.500 -0.1165 0.01915 0.01614 -0.0858 0.9483 0.0015
-4.250 -0.0837 0.01394 0.01019 -0.0871 0.9399 0.0016
-4.000 -0.0544 0.01182 0.00765 -0.0873 0.9307 0.0019
-3.750 -0.0263 0.01091 0.00653 -0.0873 0.9210 0.0025
-3.500 0.0010 0.01059 0.00610 -0.0871 0.9119 0.0029
-3.250 0.0288 0.00996 0.00529 -0.0871 0.9038 0.0033
-3.000 0.0574 0.00872 0.00385 -0.0873 0.8962 0.0044
-2.750 0.0848 0.00852 0.00360 -0.0873 0.8888 0.0057
-2.500 0.1135 0.00780 0.00272 -0.0872 0.8799 0.0055
-2.250 0.1419 0.00728 0.00201 -0.0871 0.8688 0.0053
-2.000 0.1701 0.00696 0.00153 -0.0870 0.8560 0.0052
-1.750 0.1982 0.00676 0.00120 -0.0868 0.8438 0.0051
-1.500 0.2262 0.00665 0.00097 -0.0867 0.8329 0.0053
-1.250 0.2542 0.00658 0.00079 -0.0866 0.8214 0.0065
-1.000 0.2819 0.00656 0.00066 -0.0866 0.8099 0.0063
-0.750 0.3102 0.00632 0.00059 -0.0867 0.8000 0.0643
-0.500 0.3385 0.00609 0.00058 -0.0870 0.7927 0.1397
0.000 0.3946 0.00595 0.00062 -0.0871 0.7764 0.2141
0.250 0.4225 0.00595 0.00062 -0.0872 0.7667 0.2259
0.500 0.4503 0.00595 0.00065 -0.0872 0.7547 0.2391
0.750 0.4782 0.00593 0.00067 -0.0872 0.7404 0.2640
1.000 0.5061 0.00568 0.00074 -0.0875 0.7181 0.4229
1.250 0.5259 0.00464 0.00081 -0.0859 0.6452 1.0000
1.500 0.5502 0.00542 0.00099 -0.0855 0.5055 1.0000
1.750 0.5754 0.00608 0.00118 -0.0853 0.3906 1.0000
2.000 0.6010 0.00665 0.00137 -0.0851 0.2994 1.0000
2.250 0.6276 0.00699 0.00156 -0.0850 0.2508 1.0000
2.500 0.6540 0.00738 0.00173 -0.0849 0.1969 1.0000
2.750 0.6797 0.00790 0.00198 -0.0848 0.1282 1.0000
3.000 0.7053 0.00846 0.00226 -0.0846 0.0642 1.0000
3.250 0.7320 0.00874 0.00247 -0.0844 0.0465 1.0000
3.500 0.7584 0.00906 0.00270 -0.0843 0.0289 1.0000
3.750 0.7852 0.00931 0.00299 -0.0841 0.0224 1.0000
4.000 0.8117 0.00960 0.00325 -0.0840 0.0154 1.0000
4.250 0.8382 0.00988 0.00352 -0.0838 0.0099 1.0000
4.500 0.8644 0.01021 0.00383 -0.0836 0.0059 1.0000
4.750 0.8901 0.01063 0.00421 -0.0833 0.0017 1.0000
5.000 0.9162 0.01099 0.00462 -0.0830 0.0011 1.0000
5.250 0.9419 0.01144 0.00515 -0.0826 0.0009 1.0000
5.500 0.9672 0.01201 0.00583 -0.0821 0.0007 1.0000
5.750 0.9917 0.01273 0.00673 -0.0815 0.0007 1.0000
6.000 1.0155 0.01365 0.00782 -0.0807 0.0006 1.0000
6.250 1.0384 0.01483 0.00919 -0.0796 0.0006 1.0000
6.500 1.0600 0.01644 0.01106 -0.0783 0.0007 1.0000
6.750 1.0799 0.01893 0.01394 -0.0766 0.0007 1.0000
7.000 1.0956 0.02356 0.01920 -0.0738 0.0008 1.0000
7.250 1.0967 0.03424 0.03087 -0.0681 0.0009 1.0000
7.500 1.0964 0.04352 0.04073 -0.0637 0.0010 1.0000
7.750 1.0963 0.05061 0.04820 -0.0606 0.0011 1.0000
8.000 1.0934 0.05712 0.05500 -0.0582 0.0012 1.0000
8.250 1.0875 0.06321 0.06133 -0.0564 0.0012 1.0000
8.500 1.0781 0.06904 0.06734 -0.0551 0.0013 1.0000
8.750 1.0646 0.07445 0.07289 -0.0542 0.0013 1.0000
9.000 1.0465 0.07904 0.07758 -0.0535 0.0013 1.0000
9.250 1.0291 0.08488 0.08351 -0.0562 0.0012 1.0000
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Polar data table (+)
Polar graphs
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