HAM-STD HS1-404 AIRFOIL (hs1404-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HAM-STD HS1-404 AIRFOIL (hs1404-il) Reynolds number: 1,000,000 Max Cl/Cd: 134.6 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hs1404-il-1000000.txt Download as CSV file: xf-hs1404-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4489 0.09689 0.09526 -0.0081 1.0000 0.0031
-7.750 -0.4431 0.09354 0.09193 -0.0098 1.0000 0.0031
-7.500 -0.4378 0.09027 0.08868 -0.0114 1.0000 0.0031
-7.250 -0.4296 0.08671 0.08513 -0.0141 1.0000 0.0031
-7.000 -0.4187 0.08291 0.08135 -0.0175 1.0000 0.0031
-6.750 -0.4070 0.07907 0.07752 -0.0210 1.0000 0.0031
-6.500 -0.3955 0.07528 0.07374 -0.0243 1.0000 0.0031
-6.250 -0.3843 0.07141 0.06989 -0.0274 1.0000 0.0031
-6.000 -0.3769 0.06644 0.06493 -0.0308 1.0000 0.0032
-5.750 -0.3479 0.05975 0.05820 -0.0397 0.9984 0.0034
-5.500 -0.3093 0.05314 0.05148 -0.0498 0.9964 0.0036
-5.250 -0.2684 0.04702 0.04526 -0.0589 0.9948 0.0037
-5.000 -0.2288 0.04151 0.03963 -0.0663 0.9926 0.0039
-4.750 -0.1884 0.03605 0.03402 -0.0728 0.9902 0.0042
-4.500 -0.1468 0.03026 0.02801 -0.0787 0.9882 0.0045
-4.250 -0.1049 0.02379 0.02121 -0.0835 0.9865 0.0048
-4.000 -0.0667 0.01926 0.01629 -0.0866 0.9845 0.0057
-3.500 0.0038 0.01289 0.00903 -0.0897 0.9766 0.0066
-2.750 0.0944 0.00987 0.00545 -0.0912 0.9571 0.0170
-2.500 0.1234 0.00799 0.00327 -0.0908 0.9474 0.0122
-2.250 0.1509 0.00732 0.00244 -0.0902 0.9358 0.0098
-2.000 0.1776 0.00699 0.00201 -0.0896 0.9230 0.0089
-1.750 0.2049 0.00667 0.00157 -0.0892 0.9111 0.0084
-1.500 0.2325 0.00642 0.00114 -0.0888 0.9002 0.0084
-1.250 0.2604 0.00615 0.00085 -0.0886 0.8896 0.0500
-1.000 0.2879 0.00598 0.00073 -0.0885 0.8790 0.0962
-0.750 0.3158 0.00578 0.00074 -0.0886 0.8701 0.1714
-0.500 0.3435 0.00570 0.00076 -0.0886 0.8630 0.2163
-0.250 0.3715 0.00559 0.00078 -0.0887 0.8553 0.2616
0.000 0.3994 0.00550 0.00078 -0.0888 0.8481 0.3048
0.250 0.4211 0.00386 0.00084 -0.0877 0.8402 1.0000
0.500 0.4490 0.00391 0.00086 -0.0877 0.8318 1.0000
0.750 0.4767 0.00397 0.00087 -0.0876 0.8233 1.0000
1.000 0.5044 0.00403 0.00089 -0.0875 0.8127 1.0000
1.250 0.5316 0.00411 0.00091 -0.0873 0.7942 1.0000
1.500 0.5587 0.00421 0.00092 -0.0870 0.7705 1.0000
1.750 0.5855 0.00435 0.00095 -0.0868 0.7358 1.0000
2.000 0.6112 0.00466 0.00100 -0.0863 0.6611 1.0000
2.250 0.6356 0.00531 0.00121 -0.0857 0.5450 1.0000
2.500 0.6609 0.00589 0.00142 -0.0855 0.4501 1.0000
2.750 0.6858 0.00656 0.00166 -0.0852 0.3465 1.0000
3.000 0.7109 0.00720 0.00191 -0.0850 0.2538 1.0000
3.250 0.7349 0.00807 0.00227 -0.0847 0.1346 1.0000
3.500 0.7594 0.00886 0.00266 -0.0843 0.0511 1.0000
3.750 0.7858 0.00922 0.00302 -0.0841 0.0339 1.0000
4.000 0.8120 0.00958 0.00335 -0.0839 0.0226 1.0000
4.250 0.8387 0.00980 0.00355 -0.0838 0.0176 1.0000
4.500 0.8646 0.01029 0.00410 -0.0834 0.0119 1.0000
4.750 0.8914 0.01039 0.00416 -0.0834 0.0093 1.0000
5.000 0.9158 0.01135 0.00517 -0.0825 0.0020 1.0000
5.250 0.9380 0.01292 0.00707 -0.0811 0.0018 1.0000
5.500 0.9595 0.01470 0.00909 -0.0796 0.0018 1.0000
5.750 0.9823 0.01625 0.01083 -0.0784 0.0018 1.0000
6.000 1.0057 0.01781 0.01264 -0.0773 0.0020 1.0000
13.250 0.7500 0.16298 0.16159 -0.0768 0.0048 1.0000
13.500 0.7498 0.16638 0.16498 -0.0779 0.0048 1.0000
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Polar data table (+)
Polar graphs
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