S9032 (9%) (s9032-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S9032 (9%) (s9032-il) Reynolds number: 50,000 Max Cl/Cd: 23.49 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9032-il-50000.txt Download as CSV file: xf-s9032-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S9032 (9%)
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.7417 0.07647 0.06948 -0.0083 1.0000 0.1561
-8.500 -0.7470 0.07074 0.06369 -0.0099 1.0000 0.1544
-8.250 -0.7561 0.06463 0.05744 -0.0117 1.0000 0.1524
-8.000 -0.7637 0.05855 0.05108 -0.0130 1.0000 0.1512
-7.750 -0.7657 0.05295 0.04508 -0.0136 1.0000 0.1512
-7.500 -0.7620 0.04781 0.03944 -0.0134 1.0000 0.1523
-7.250 -0.7542 0.04319 0.03416 -0.0128 1.0000 0.1552
-7.000 -0.7362 0.04062 0.03150 -0.0118 1.0000 0.1649
-6.750 -0.7206 0.03745 0.02788 -0.0108 1.0000 0.1744
-6.500 -0.7023 0.03468 0.02457 -0.0097 1.0000 0.1854
-6.250 -0.6812 0.03274 0.02264 -0.0087 1.0000 0.2017
-6.000 -0.6591 0.03073 0.02053 -0.0076 1.0000 0.2177
-5.750 -0.6374 0.02914 0.01883 -0.0065 1.0000 0.2395
-5.500 -0.6145 0.02734 0.01698 -0.0054 1.0000 0.2609
-5.250 -0.5925 0.02597 0.01564 -0.0041 1.0000 0.2894
-5.000 -0.5701 0.02466 0.01443 -0.0027 1.0000 0.3210
-4.750 -0.5485 0.02350 0.01335 -0.0012 1.0000 0.3596
-4.500 -0.5273 0.02247 0.01249 0.0005 1.0000 0.4027
-4.250 -0.5064 0.02157 0.01184 0.0026 1.0000 0.4494
-4.000 -0.4862 0.02077 0.01126 0.0049 1.0000 0.5011
-3.750 -0.4662 0.02011 0.01086 0.0075 1.0000 0.5538
-3.500 -0.4467 0.01955 0.01049 0.0105 1.0000 0.6087
-3.250 -0.4287 0.01910 0.01023 0.0140 1.0000 0.6644
-3.000 -0.4109 0.01876 0.01006 0.0179 1.0000 0.7192
-2.750 -0.3916 0.01854 0.00997 0.0220 1.0000 0.7739
-2.500 -0.3637 0.01850 0.00995 0.0247 1.0000 0.8304
-2.250 -0.3021 0.01885 0.01010 0.0214 1.0000 0.8896
-2.000 -0.1824 0.01912 0.00985 0.0059 1.0000 0.9460
-1.750 -0.0670 0.01815 0.00850 -0.0117 1.0000 0.9960
-1.500 -0.0492 0.01739 0.00770 -0.0126 1.0000 1.0000
-1.250 -0.0407 0.01684 0.00714 -0.0113 1.0000 1.0000
-1.000 -0.0324 0.01640 0.00670 -0.0096 1.0000 1.0000
-0.750 -0.0245 0.01607 0.00638 -0.0074 1.0000 1.0000
-0.500 -0.0167 0.01584 0.00615 -0.0050 1.0000 1.0000
-0.250 -0.0087 0.01571 0.00602 -0.0025 1.0000 1.0000
0.000 0.0000 0.01566 0.00598 0.0000 1.0000 1.0000
0.250 0.0087 0.01571 0.00602 0.0025 1.0000 1.0000
0.500 0.0167 0.01584 0.00615 0.0050 1.0000 1.0000
0.750 0.0245 0.01607 0.00638 0.0074 1.0000 1.0000
1.000 0.0324 0.01640 0.00670 0.0096 1.0000 1.0000
1.250 0.0407 0.01684 0.00713 0.0113 1.0000 1.0000
1.500 0.0492 0.01739 0.00770 0.0126 1.0000 1.0000
1.750 0.0670 0.01815 0.00850 0.0117 0.9960 1.0000
2.000 0.1822 0.01912 0.00985 -0.0059 0.9460 1.0000
2.250 0.3021 0.01886 0.01010 -0.0214 0.8895 1.0000
2.500 0.3638 0.01850 0.00995 -0.0247 0.8303 1.0000
2.750 0.3918 0.01854 0.00998 -0.0220 0.7737 1.0000
3.000 0.4111 0.01876 0.01006 -0.0179 0.7190 1.0000
3.250 0.4290 0.01910 0.01023 -0.0140 0.6643 1.0000
3.500 0.4470 0.01954 0.01049 -0.0105 0.6085 1.0000
3.750 0.4664 0.02011 0.01086 -0.0076 0.5535 1.0000
4.000 0.4864 0.02078 0.01127 -0.0049 0.5009 1.0000
4.250 0.5066 0.02157 0.01184 -0.0026 0.4492 1.0000
4.500 0.5276 0.02248 0.01249 -0.0006 0.4026 1.0000
4.750 0.5487 0.02349 0.01335 0.0012 0.3595 1.0000
5.000 0.5703 0.02466 0.01443 0.0027 0.3209 1.0000
5.250 0.5926 0.02597 0.01564 0.0041 0.2893 1.0000
5.500 0.6147 0.02734 0.01698 0.0053 0.2609 1.0000
5.750 0.6375 0.02914 0.01883 0.0065 0.2395 1.0000
6.000 0.6591 0.03072 0.02053 0.0076 0.2176 1.0000
6.250 0.6812 0.03274 0.02265 0.0087 0.2016 1.0000
6.500 0.7023 0.03467 0.02457 0.0097 0.1854 1.0000
6.750 0.7205 0.03744 0.02787 0.0109 0.1743 1.0000
7.000 0.7360 0.04061 0.03149 0.0119 0.1649 1.0000
7.250 0.7540 0.04316 0.03413 0.0128 0.1552 1.0000
7.500 0.7617 0.04779 0.03941 0.0135 0.1523 1.0000
7.750 0.7654 0.05290 0.04503 0.0137 0.1513 1.0000
8.000 0.7633 0.05848 0.05101 0.0132 0.1511 1.0000
8.250 0.7558 0.06458 0.05738 0.0119 0.1525 1.0000
8.500 0.7465 0.07068 0.06363 0.0101 0.1544 1.0000
8.750 0.7405 0.07647 0.06948 0.0083 0.1560 1.0000
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Polar data table (+)
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