HAM-STD HS1-404 AIRFOIL (hs1404-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HAM-STD HS1-404 AIRFOIL (hs1404-il) Reynolds number: 50,000 Max Cl/Cd: 42.11 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hs1404-il-50000.txt Download as CSV file: xf-hs1404-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4658 0.11061 0.10377 -0.0062 1.0000 0.1287
-8.000 -0.4672 0.10911 0.10236 -0.0086 1.0000 0.1330
-7.750 -0.4698 0.10794 0.10133 -0.0129 1.0000 0.1347
-7.500 -0.4530 0.10148 0.09485 -0.0092 1.0000 0.1416
-7.250 -0.4522 0.10023 0.09370 -0.0144 1.0000 0.1468
-7.000 -0.4418 0.09524 0.08861 -0.0132 1.0000 0.1512
-6.750 -0.4342 0.09258 0.08601 -0.0163 1.0000 0.1590
-6.250 -0.4148 0.08640 0.07993 -0.0231 1.0000 0.1735
-6.000 -0.4052 0.08171 0.07531 -0.0205 1.0000 0.1797
-5.500 -0.3787 0.07561 0.06926 -0.0290 1.0000 0.2011
-5.250 -0.3642 0.07226 0.06592 -0.0314 1.0000 0.2140
-5.000 -0.3503 0.06862 0.06230 -0.0324 1.0000 0.2272
-4.750 -0.3370 0.06483 0.05856 -0.0324 1.0000 0.2411
-4.500 -0.3236 0.06116 0.05492 -0.0320 1.0000 0.2559
-4.250 -0.3083 0.05777 0.05156 -0.0322 1.0000 0.2746
-4.000 -0.2915 0.05437 0.04816 -0.0330 1.0000 0.2979
-3.750 -0.2753 0.05114 0.04495 -0.0329 1.0000 0.3270
-3.500 -0.1481 0.03958 0.03152 -0.0643 1.0000 0.1086
-3.250 -0.1201 0.03597 0.02770 -0.0654 1.0000 0.1036
-3.000 -0.0866 0.03247 0.02370 -0.0674 1.0000 0.1029
-2.750 -0.0528 0.02928 0.01993 -0.0689 1.0000 0.1040
-2.500 -0.0191 0.02630 0.01630 -0.0698 1.0000 0.1052
-2.250 0.0121 0.02387 0.01342 -0.0699 1.0000 0.1129
-2.000 0.0407 0.02248 0.01187 -0.0697 1.0000 0.1663
-1.750 0.0711 0.02035 0.00978 -0.0696 1.0000 0.3053
-1.500 0.1005 0.01875 0.00824 -0.0695 1.0000 0.3883
-1.250 0.1296 0.01705 0.00719 -0.0695 1.0000 0.5141
-1.000 0.1451 0.01561 0.00641 -0.0660 1.0000 1.0000
-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 0.4120 0.01901 0.00769 -0.0635 1.0000 1.0000
2.000 0.4347 0.01951 0.00824 -0.0634 1.0000 1.0000
2.250 0.4571 0.02005 0.00887 -0.0633 1.0000 1.0000
2.500 0.4792 0.02064 0.00959 -0.0633 1.0000 1.0000
2.750 0.5008 0.02130 0.01040 -0.0633 1.0000 1.0000
3.000 0.5218 0.02204 0.01133 -0.0633 1.0000 1.0000
3.250 0.5423 0.02288 0.01255 -0.0634 1.0000 1.0000
3.500 0.5619 0.02384 0.01376 -0.0637 1.0000 1.0000
3.750 0.5804 0.02498 0.01516 -0.0641 1.0000 1.0000
4.000 0.6239 0.02636 0.01701 -0.0696 0.9857 1.0000
4.250 0.8110 0.01926 0.01209 -0.0796 0.7393 1.0000
4.500 0.8074 0.02315 0.01218 -0.0682 0.2154 1.0000
4.750 0.8310 0.02592 0.01449 -0.0666 0.1588 1.0000
5.000 0.8596 0.02842 0.01687 -0.0656 0.1279 1.0000
5.250 0.8931 0.03152 0.02013 -0.0647 0.1163 1.0000
5.500 0.9243 0.03541 0.02422 -0.0638 0.1102 1.0000
5.750 0.9475 0.03856 0.02786 -0.0625 0.0957 1.0000
6.000 0.9722 0.04275 0.03275 -0.0607 0.0943 1.0000
6.250 0.9939 0.04765 0.03823 -0.0591 0.0964 1.0000
6.500 1.0116 0.05264 0.04424 -0.0570 0.1043 1.0000
6.750 1.0260 0.05859 0.05095 -0.0556 0.1169 1.0000
7.000 1.0404 0.06577 0.05860 -0.0551 0.1361 1.0000
7.250 1.0444 0.07677 0.07066 -0.0596 0.2021 1.0000
7.500 0.9457 0.06885 0.06323 -0.0474 0.1678 1.0000
7.750 0.9215 0.07632 0.07088 -0.0493 0.1828 1.0000
8.000 0.8942 0.08385 0.07850 -0.0525 0.2055 1.0000
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Polar data table (+)
Polar graphs
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