S9033 (7.5%) (s9033-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9033 (7.5%) (s9033-il) Reynolds number: 50,000 Max Cl/Cd: 23.46 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9033-il-50000-n5.txt Download as CSV file: xf-s9033-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S9033 (7.5%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.7350 0.08850 0.08142 0.0049 1.0000 0.0591
-9.500 -0.7493 0.08019 0.07315 -0.0014 1.0000 0.0587
-9.250 -0.7692 0.07310 0.06607 -0.0067 1.0000 0.0582
-9.000 -0.7867 0.06674 0.05958 -0.0099 1.0000 0.0579
-8.750 -0.7989 0.06066 0.05323 -0.0122 1.0000 0.0579
-8.500 -0.8047 0.05495 0.04711 -0.0134 1.0000 0.0584
-8.250 -0.8044 0.04966 0.04125 -0.0140 1.0000 0.0598
-8.000 -0.7964 0.04555 0.03664 -0.0139 1.0000 0.0623
-7.750 -0.7796 0.04350 0.03451 -0.0135 1.0000 0.0659
-7.500 -0.7640 0.04037 0.03095 -0.0130 1.0000 0.0692
-7.250 -0.7465 0.03695 0.02692 -0.0124 1.0000 0.0723
-7.000 -0.7265 0.03447 0.02415 -0.0117 1.0000 0.0765
-6.750 -0.7052 0.03280 0.02226 -0.0112 1.0000 0.0840
-6.500 -0.6832 0.03090 0.02010 -0.0105 1.0000 0.0910
-6.250 -0.6598 0.02912 0.01800 -0.0097 1.0000 0.0995
-6.000 -0.6372 0.02784 0.01668 -0.0091 1.0000 0.1112
-5.750 -0.6136 0.02645 0.01521 -0.0084 1.0000 0.1224
-5.500 -0.5900 0.02531 0.01397 -0.0077 1.0000 0.1382
-5.250 -0.5657 0.02414 0.01266 -0.0070 1.0000 0.1540
-5.000 -0.5417 0.02309 0.01164 -0.0064 1.0000 0.1729
-4.750 -0.5174 0.02215 0.01068 -0.0057 1.0000 0.1966
-4.500 -0.4930 0.02124 0.00984 -0.0052 1.0000 0.2228
-4.250 -0.4683 0.02041 0.00909 -0.0047 1.0000 0.2555
-4.000 -0.4441 0.01964 0.00841 -0.0041 1.0000 0.2933
-3.750 -0.4206 0.01892 0.00785 -0.0033 1.0000 0.3369
-3.500 -0.3975 0.01825 0.00737 -0.0023 1.0000 0.3852
-3.250 -0.3747 0.01763 0.00696 -0.0012 1.0000 0.4394
-3.000 -0.3524 0.01705 0.00663 0.0003 1.0000 0.4984
-2.750 -0.3308 0.01651 0.00634 0.0020 1.0000 0.5621
-2.500 -0.3095 0.01603 0.00612 0.0040 1.0000 0.6297
-2.250 -0.2878 0.01561 0.00595 0.0062 1.0000 0.6996
-2.000 -0.2626 0.01527 0.00581 0.0080 1.0000 0.7728
-1.750 -0.2256 0.01505 0.00566 0.0076 1.0000 0.8508
-1.500 -0.1725 0.01491 0.00545 0.0035 1.0000 0.9235
-1.250 -0.1131 0.01475 0.00511 -0.0026 1.0000 0.9813
-1.000 -0.0775 0.01456 0.00480 -0.0048 1.0000 1.0000
-0.750 -0.0586 0.01445 0.00461 -0.0036 1.0000 1.0000
-0.500 -0.0392 0.01438 0.00448 -0.0025 1.0000 1.0000
-0.250 -0.0197 0.01434 0.00440 -0.0012 1.0000 1.0000
0.000 0.0000 0.01432 0.00438 0.0000 1.0000 1.0000
0.250 0.0197 0.01434 0.00440 0.0012 1.0000 1.0000
0.500 0.0392 0.01438 0.00448 0.0025 1.0000 1.0000
0.750 0.0586 0.01445 0.00461 0.0036 1.0000 1.0000
1.000 0.0775 0.01456 0.00480 0.0048 1.0000 1.0000
1.250 0.1132 0.01475 0.00511 0.0026 0.9812 1.0000
1.500 0.1725 0.01491 0.00545 -0.0035 0.9234 1.0000
1.750 0.2256 0.01505 0.00566 -0.0076 0.8509 1.0000
2.000 0.2626 0.01527 0.00579 -0.0080 0.7728 1.0000
2.250 0.2878 0.01561 0.00595 -0.0062 0.6996 1.0000
2.500 0.3095 0.01603 0.00612 -0.0040 0.6297 1.0000
2.750 0.3308 0.01651 0.00634 -0.0020 0.5621 1.0000
3.250 0.3747 0.01763 0.00696 0.0012 0.4395 1.0000
3.500 0.3975 0.01825 0.00737 0.0023 0.3851 1.0000
3.750 0.4206 0.01892 0.00786 0.0032 0.3368 1.0000
4.000 0.4441 0.01964 0.00841 0.0041 0.2933 1.0000
4.250 0.4683 0.02041 0.00909 0.0047 0.2556 1.0000
4.500 0.4930 0.02124 0.00984 0.0052 0.2228 1.0000
4.750 0.5174 0.02214 0.01068 0.0057 0.1967 1.0000
5.000 0.5417 0.02309 0.01163 0.0064 0.1729 1.0000
5.250 0.5657 0.02413 0.01266 0.0070 0.1540 1.0000
5.500 0.5899 0.02531 0.01397 0.0078 0.1381 1.0000
5.750 0.6135 0.02645 0.01521 0.0084 0.1224 1.0000
6.000 0.6371 0.02784 0.01667 0.0091 0.1111 1.0000
6.250 0.6598 0.02912 0.01800 0.0098 0.0996 1.0000
6.500 0.6831 0.03089 0.02009 0.0105 0.0910 1.0000
6.750 0.7052 0.03280 0.02225 0.0112 0.0840 1.0000
7.000 0.7264 0.03446 0.02414 0.0118 0.0764 1.0000
7.250 0.7465 0.03694 0.02691 0.0124 0.0724 1.0000
7.500 0.7639 0.04036 0.03094 0.0130 0.0692 1.0000
7.750 0.7795 0.04350 0.03450 0.0135 0.0659 1.0000
8.000 0.7963 0.04555 0.03665 0.0139 0.0623 1.0000
8.250 0.8044 0.04965 0.04123 0.0140 0.0598 1.0000
8.500 0.8046 0.05495 0.04711 0.0135 0.0584 1.0000
8.750 0.7988 0.06067 0.05323 0.0122 0.0579 1.0000
9.000 0.7867 0.06676 0.05959 0.0099 0.0579 1.0000
9.250 0.7693 0.07311 0.06608 0.0066 0.0581 1.0000
9.500 0.7492 0.08027 0.07323 0.0013 0.0586 1.0000
9.750 0.7352 0.08855 0.08147 -0.0050 0.0591 1.0000
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Polar data table (+)
Polar graphs
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