HAM-STD HS1-404 AIRFOIL (hs1404-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HAM-STD HS1-404 AIRFOIL (hs1404-il) Reynolds number: 500,000 Max Cl/Cd: 102.2 at α=1.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hs1404-il-500000-n5.txt Download as CSV file: xf-hs1404-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4565 0.09530 0.09303 -0.0086 1.0000 0.0036
-7.750 -0.4511 0.09203 0.08979 -0.0101 1.0000 0.0037
-7.500 -0.4463 0.08883 0.08662 -0.0117 1.0000 0.0037
-7.250 -0.4385 0.08530 0.08311 -0.0144 1.0000 0.0037
-7.000 -0.4283 0.08156 0.07938 -0.0178 1.0000 0.0037
-6.750 -0.4168 0.07766 0.07551 -0.0215 1.0000 0.0037
-6.500 -0.4043 0.07359 0.07145 -0.0255 1.0000 0.0037
-6.250 -0.3908 0.06942 0.06729 -0.0294 1.0000 0.0036
-5.250 -0.2701 0.04959 0.04718 -0.0565 0.9889 0.0029
-5.000 -0.2282 0.04279 0.04022 -0.0655 0.9854 0.0028
-4.750 -0.1842 0.03574 0.03294 -0.0734 0.9827 0.0027
-4.500 -0.1423 0.02813 0.02498 -0.0794 0.9782 0.0027
-4.250 -0.1007 0.02013 0.01633 -0.0838 0.9746 0.0028
-3.750 -0.0304 0.01339 0.00838 -0.0877 0.9667 0.0039
-3.500 0.0004 0.01248 0.00730 -0.0885 0.9610 0.0047
-3.250 0.0310 0.01240 0.00718 -0.0893 0.9558 0.0070
-3.000 0.0613 0.01117 0.00570 -0.0896 0.9487 0.0072
-2.750 0.0919 0.01000 0.00431 -0.0900 0.9426 0.0070
-2.500 0.1211 0.00917 0.00329 -0.0901 0.9352 0.0069
-2.250 0.1503 0.00855 0.00254 -0.0901 0.9285 0.0069
-2.000 0.1788 0.00815 0.00199 -0.0900 0.9208 0.0070
-1.750 0.2070 0.00789 0.00158 -0.0899 0.9129 0.0073
-1.500 0.2345 0.00771 0.00129 -0.0895 0.9028 0.0139
-1.250 0.2616 0.00718 0.00120 -0.0895 0.8900 0.1462
-1.000 0.2883 0.00725 0.00101 -0.0890 0.8764 0.1196
-0.250 0.3698 0.00699 0.00099 -0.0885 0.8405 0.2417
0.000 0.3974 0.00694 0.00098 -0.0884 0.8314 0.2615
0.250 0.4251 0.00683 0.00099 -0.0885 0.8234 0.3107
0.750 0.4734 0.00527 0.00108 -0.0869 0.8054 1.0000
1.000 0.5009 0.00534 0.00111 -0.0868 0.7948 1.0000
1.250 0.5284 0.00542 0.00115 -0.0866 0.7822 1.0000
1.500 0.5556 0.00551 0.00119 -0.0864 0.7647 1.0000
1.750 0.5815 0.00569 0.00121 -0.0858 0.7204 1.0000
2.000 0.6046 0.00623 0.00126 -0.0848 0.6017 1.0000
2.250 0.6265 0.00727 0.00161 -0.0839 0.4387 1.0000
2.500 0.6508 0.00801 0.00189 -0.0836 0.3322 1.0000
2.750 0.6767 0.00844 0.00211 -0.0834 0.2784 1.0000
3.000 0.7018 0.00903 0.00239 -0.0832 0.2014 1.0000
3.250 0.7252 0.01001 0.00283 -0.0828 0.0841 1.0000
3.500 0.7510 0.01046 0.00316 -0.0826 0.0535 1.0000
3.750 0.7772 0.01082 0.00349 -0.0823 0.0395 1.0000
4.000 0.8033 0.01120 0.00397 -0.0820 0.0300 1.0000
4.250 0.8291 0.01166 0.00444 -0.0817 0.0222 1.0000
4.500 0.8552 0.01200 0.00486 -0.0814 0.0185 1.0000
4.750 0.8808 0.01240 0.00521 -0.0812 0.0113 1.0000
5.000 0.9061 0.01283 0.00558 -0.0809 0.0046 1.0000
5.250 0.9309 0.01349 0.00628 -0.0804 0.0022 1.0000
5.500 0.9545 0.01451 0.00750 -0.0794 0.0015 1.0000
5.750 0.9776 0.01563 0.00883 -0.0784 0.0014 1.0000
6.000 0.9994 0.01719 0.01071 -0.0771 0.0012 1.0000
6.250 1.0205 0.01918 0.01301 -0.0757 0.0012 1.0000
6.500 1.0410 0.02182 0.01604 -0.0740 0.0012 1.0000
6.750 1.0597 0.02546 0.02021 -0.0719 0.0012 1.0000
7.000 1.0740 0.03058 0.02599 -0.0692 0.0012 1.0000
7.250 1.0817 0.03765 0.03371 -0.0657 0.0013 1.0000
7.500 1.0859 0.04464 0.04120 -0.0624 0.0013 1.0000
7.750 1.0871 0.05108 0.04802 -0.0597 0.0014 1.0000
8.000 1.0850 0.05723 0.05449 -0.0574 0.0014 1.0000
8.250 1.0794 0.06312 0.06064 -0.0557 0.0014 1.0000
8.500 1.0701 0.06879 0.06651 -0.0544 0.0015 1.0000
8.750 1.0559 0.07398 0.07185 -0.0534 0.0015 1.0000
9.000 1.0381 0.07885 0.07683 -0.0532 0.0015 1.0000
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Polar data table (+)
Polar graphs
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