HAM-STD HS1-620 AIRFOIL (hs1620-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HAM-STD HS1-620 AIRFOIL (hs1620-il) Reynolds number: 50,000 Max Cl/Cd: 16.01 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hs1620-il-50000.txt Download as CSV file: xf-hs1620-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HAM-STD HS1-620 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 -0.4450 0.13533 0.12833 -0.0052 1.0000 0.3456
-8.000 -0.3760 0.12931 0.12223 -0.0051 1.0000 0.3557
-7.750 -0.4266 0.12968 0.12275 -0.0012 1.0000 0.3680
-7.500 -0.3961 0.12540 0.11847 -0.0003 1.0000 0.3759
-7.250 -0.4194 0.12468 0.11784 0.0032 1.0000 0.3902
-7.000 -0.4084 0.12153 0.11473 0.0049 1.0000 0.4000
-6.750 -0.4521 0.12147 0.11480 0.0100 1.0000 0.4155
-6.500 -0.4121 0.11777 0.11107 0.0102 1.0000 0.4286
-6.250 -0.6433 0.08789 0.08062 -0.0110 1.0000 0.2560
-6.000 -0.6359 0.08408 0.07675 -0.0104 1.0000 0.2532
-5.750 -0.6311 0.07969 0.07223 -0.0107 1.0000 0.2510
-5.500 -0.6256 0.07494 0.06724 -0.0118 1.0000 0.2501
-5.250 -0.6168 0.07050 0.06245 -0.0131 1.0000 0.2510
-5.000 -0.6044 0.06643 0.05790 -0.0146 1.0000 0.2533
-4.750 -0.5898 0.06347 0.05467 -0.0151 1.0000 0.2574
-4.500 -0.5746 0.06222 0.05348 -0.0141 1.0000 0.2624
-4.250 -0.5577 0.06049 0.05154 -0.0142 1.0000 0.2684
-4.000 -0.5380 0.05844 0.04900 -0.0152 1.0000 0.2748
-3.750 -0.5202 0.05696 0.04745 -0.0151 1.0000 0.2811
-3.500 -0.5023 0.05615 0.04661 -0.0146 1.0000 0.2882
-3.250 -0.4814 0.05514 0.04524 -0.0151 1.0000 0.2966
-3.000 -0.4618 0.05418 0.04417 -0.0152 1.0000 0.3041
-2.750 -0.4428 0.05375 0.04372 -0.0150 1.0000 0.3125
-2.500 -0.4203 0.05340 0.04296 -0.0156 1.0000 0.3223
-2.250 -0.4016 0.05293 0.04264 -0.0153 1.0000 0.3308
-2.000 -0.3809 0.05286 0.04243 -0.0155 1.0000 0.3413
-1.750 -0.3603 0.05274 0.04226 -0.0156 1.0000 0.3511
-1.500 -0.3403 0.05290 0.04240 -0.0157 1.0000 0.3623
-1.250 -0.3194 0.05308 0.04251 -0.0160 1.0000 0.3733
-1.000 -0.2996 0.05345 0.04289 -0.0161 1.0000 0.3855
-0.750 -0.2793 0.05387 0.04330 -0.0163 1.0000 0.3978
-0.500 -0.2598 0.05446 0.04391 -0.0164 1.0000 0.4116
-0.250 -0.1342 0.05729 0.04678 -0.0344 0.9483 0.4559
0.000 -0.0620 0.05753 0.04718 -0.0421 0.9147 0.4968
0.250 -0.0054 0.05762 0.04771 -0.0470 0.8948 0.5539
0.500 0.0308 0.05700 0.04819 -0.0472 0.8792 0.6984
0.750 0.0747 0.05675 0.04821 -0.0499 0.8583 1.0000
1.000 0.1145 0.05731 0.04834 -0.0526 0.8413 1.0000
1.250 0.1558 0.05780 0.04853 -0.0553 0.8251 1.0000
1.500 0.2050 0.05811 0.04858 -0.0589 0.8102 1.0000
1.750 0.2359 0.05842 0.04872 -0.0597 0.7926 1.0000
2.000 0.2652 0.05878 0.04895 -0.0603 0.7749 1.0000
2.250 0.2951 0.05911 0.04916 -0.0608 0.7570 1.0000
2.500 0.3254 0.05941 0.04935 -0.0613 0.7392 1.0000
2.750 0.3573 0.05966 0.04949 -0.0619 0.7222 1.0000
3.000 0.4189 0.05853 0.04821 -0.0657 0.7117 1.0000
3.250 0.4408 0.05894 0.04856 -0.0648 0.6928 1.0000
3.500 0.4618 0.05953 0.04909 -0.0639 0.6744 1.0000
3.750 0.4839 0.06013 0.04963 -0.0632 0.6570 1.0000
4.000 0.5482 0.05795 0.04734 -0.0663 0.6496 1.0000
4.250 0.5592 0.05921 0.04856 -0.0644 0.6311 1.0000
4.500 0.5705 0.06063 0.04995 -0.0626 0.6141 1.0000
4.750 0.6356 0.05774 0.04697 -0.0651 0.6085 1.0000
5.000 0.6339 0.06030 0.04951 -0.0624 0.5905 1.0000
5.250 0.7088 0.05621 0.04533 -0.0654 0.5873 1.0000
5.500 0.6928 0.06017 0.04929 -0.0617 0.5689 1.0000
5.750 0.7789 0.05509 0.04410 -0.0656 0.5664 1.0000
6.000 0.7436 0.06081 0.04986 -0.0604 0.5481 1.0000
6.250 0.8425 0.05475 0.04367 -0.0656 0.5459 1.0000
6.500 0.7783 0.06321 0.05222 -0.0584 0.5274 1.0000
6.750 0.8922 0.05573 0.04460 -0.0645 0.5257 1.0000
7.000 0.7853 0.06888 0.05789 -0.0553 0.5066 1.0000
7.250 0.9024 0.06022 0.04910 -0.0602 0.5053 1.0000
7.500 0.7588 0.07923 0.06831 -0.0523 0.4858 1.0000
7.750 0.6452 0.09603 0.08524 -0.0499 0.4753 1.0000
8.000 0.6678 0.09746 0.08666 -0.0498 0.4688 1.0000
8.250 0.6813 0.10007 0.08927 -0.0497 0.4632 1.0000
8.500 0.6433 0.10836 0.09762 -0.0496 0.4606 1.0000
8.750 0.6268 0.11422 0.10353 -0.0499 0.4591 1.0000
9.000 0.6192 0.11942 0.10876 -0.0505 0.4597 1.0000
9.250 0.6196 0.12416 0.11354 -0.0514 0.4618 1.0000
9.500 0.6307 0.12841 0.11782 -0.0525 0.4639 1.0000
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Polar data table (+)
Polar graphs
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