HAM-STD HS1-430 AIRFOIL (hs1430-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: HAM-STD HS1-430 AIRFOIL (hs1430-il) Reynolds number: 50,000 Max Cl/Cd: 16.38 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hs1430-il-50000.txt Download as CSV file: xf-hs1430-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HAM-STD HS1-430 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.750 -0.7424 0.11747 0.10954 0.0199 1.0000 0.3502
-6.500 -0.7716 0.11161 0.10360 0.0233 1.0000 0.3472
-6.250 -0.8149 0.10448 0.09635 0.0280 1.0000 0.3450
-6.000 -0.8686 0.09644 0.08807 0.0339 1.0000 0.3431
-5.750 -0.9041 0.09016 0.08149 0.0388 1.0000 0.3430
-5.500 -0.9237 0.08542 0.07647 0.0426 1.0000 0.3439
-5.250 -0.9348 0.08162 0.07236 0.0457 1.0000 0.3454
-5.000 -0.9402 0.07856 0.06895 0.0484 1.0000 0.3475
-4.750 -0.9401 0.07611 0.06620 0.0506 1.0000 0.3497
-4.500 -0.9301 0.07417 0.06429 0.0517 1.0000 0.3527
-4.250 -0.9186 0.07300 0.06312 0.0529 1.0000 0.3557
-4.000 -0.9063 0.07212 0.06224 0.0539 1.0000 0.3592
-3.750 -0.8950 0.07119 0.06124 0.0549 1.0000 0.3628
-3.500 -0.8840 0.07024 0.06017 0.0560 1.0000 0.3667
-3.250 -0.8707 0.06942 0.05916 0.0565 0.9994 0.3706
-3.000 -0.8423 0.06950 0.05894 0.0543 0.9939 0.3752
-2.750 -0.8127 0.06996 0.05922 0.0519 0.9890 0.3799
-2.500 -0.7863 0.06981 0.05917 0.0503 0.9811 0.3850
-2.250 -0.7511 0.07126 0.06061 0.0472 0.9744 0.3913
-2.000 -0.7204 0.07157 0.06085 0.0449 0.9632 0.3975
-1.750 -0.6908 0.07199 0.06110 0.0427 0.9509 0.4040
-1.500 -0.5784 0.07199 0.06111 0.0289 0.8758 0.4181
-1.250 -0.5058 0.07092 0.05993 0.0222 0.8348 0.4314
-1.000 -0.4531 0.07005 0.05902 0.0184 0.8103 0.4427
-0.750 -0.3970 0.06945 0.05854 0.0141 0.7919 0.4564
-0.500 -0.3729 0.06911 0.05810 0.0141 0.7746 0.4672
-0.250 -0.3471 0.06905 0.05829 0.0139 0.7585 0.4788
0.000 -0.2836 0.06852 0.05786 0.0086 0.7479 0.5011
0.250 -0.2711 0.06873 0.05829 0.0103 0.7292 0.5156
0.500 -0.1995 0.06760 0.05747 0.0046 0.7212 0.5540
0.750 -0.1958 0.06787 0.05809 0.0080 0.7003 0.5812
1.000 -0.1746 0.06779 0.05858 0.0097 0.6830 0.6388
1.250 -0.0644 0.06877 0.06062 0.0023 0.6709 0.8202
1.500 0.0747 0.07299 0.06471 -0.0121 0.6471 0.8939
1.750 0.3199 0.07165 0.06299 -0.0425 0.6404 0.9423
2.000 0.4181 0.07085 0.06207 -0.0537 0.6191 0.9669
2.250 0.6850 0.06135 0.05218 -0.0901 0.6165 0.9976
2.500 0.6875 0.06158 0.05231 -0.0868 0.5948 1.0000
2.750 0.8196 0.05466 0.04491 -0.1031 0.5891 1.0000
3.000 0.7607 0.05755 0.04785 -0.0898 0.5691 1.0000
3.250 0.7616 0.05788 0.04807 -0.0861 0.5554 1.0000
3.500 0.8018 0.05622 0.04619 -0.0883 0.5447 1.0000
3.750 0.8432 0.05494 0.04466 -0.0910 0.5350 1.0000
4.000 0.7800 0.05853 0.04838 -0.0779 0.5240 1.0000
4.250 0.8892 0.05429 0.04367 -0.0907 0.5168 1.0000
4.500 0.8149 0.05829 0.04786 -0.0758 0.5094 1.0000
4.750 0.5986 0.07387 0.06395 -0.0474 0.4957 1.0000
5.000 0.6966 0.06698 0.05674 -0.0539 0.4941 1.0000
5.250 0.9167 0.05660 0.04560 -0.0801 0.4904 1.0000
5.500 0.2842 0.11176 0.10227 -0.0235 0.4831 1.0000
5.750 0.1110 0.13142 0.12237 -0.0182 0.5741 1.0000
6.000 0.1408 0.13255 0.12335 -0.0184 0.5666 1.0000
6.250 0.1708 0.13528 0.12593 -0.0192 0.5635 1.0000
6.500 0.2346 0.12489 0.11519 -0.0151 0.4871 1.0000
6.750 0.2417 0.12742 0.11766 -0.0144 0.4889 1.0000
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Polar data table (+)
Polar graphs
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