GOE 746 AIRFOIL (goe746-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 746 AIRFOIL (goe746-il) Reynolds number: 100,000 Max Cl/Cd: 49.14 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe746-il-100000-n5.txt Download as CSV file: xf-goe746-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 746 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3801 0.10460 0.09973 0.0119 0.6640 0.0406
-8.000 -0.3838 0.10261 0.09780 0.0074 0.6582 0.0413
-7.750 -0.3857 0.10028 0.09547 0.0038 0.6532 0.0415
-7.500 -0.3805 0.09731 0.09243 0.0002 0.6490 0.0417
-7.250 -0.3724 0.09250 0.08764 -0.0010 0.6433 0.0421
-7.000 -0.3607 0.08779 0.08291 0.0020 0.6378 0.0434
-6.750 -0.3512 0.08451 0.07957 0.0016 0.6335 0.0447
-6.500 -0.3410 0.08131 0.07636 -0.0002 0.6281 0.0463
-6.250 -0.3300 0.07817 0.07315 -0.0027 0.6235 0.0494
-6.000 -0.3096 0.07588 0.07053 -0.0119 0.6202 0.0529
-5.750 -0.3018 0.07086 0.06560 -0.0102 0.6159 0.0543
-5.500 -0.2884 0.06770 0.06241 -0.0099 0.6109 0.0563
-5.250 -0.2719 0.06465 0.05925 -0.0111 0.6067 0.0591
-5.000 -0.2406 0.06261 0.05657 -0.0170 0.6036 0.0650
-4.750 -0.2293 0.05763 0.05178 -0.0164 0.5989 0.0665
-4.500 -0.2136 0.05503 0.04918 -0.0158 0.5945 0.0705
-4.250 -0.1855 0.05234 0.04596 -0.0185 0.5911 0.0788
-4.000 -0.1691 0.04900 0.04261 -0.0180 0.5880 0.0806
-3.750 -0.1477 0.04642 0.03993 -0.0182 0.5832 0.0834
-3.250 -0.0932 0.03938 0.03199 -0.0185 0.5760 0.0629
-3.000 -0.0662 0.03559 0.02753 -0.0176 0.5734 0.0521
-2.750 -0.0418 0.03333 0.02505 -0.0174 0.5695 0.0510
-2.500 -0.0153 0.03150 0.02275 -0.0168 0.5654 0.0520
-2.250 0.0108 0.02987 0.02071 -0.0162 0.5617 0.0523
-2.000 0.0366 0.02822 0.01875 -0.0157 0.5586 0.0517
-1.750 0.0636 0.02685 0.01709 -0.0154 0.5549 0.0513
-1.500 0.0912 0.02569 0.01566 -0.0151 0.5509 0.0512
-1.250 0.1189 0.02467 0.01436 -0.0148 0.5473 0.0512
-1.000 0.1467 0.02399 0.01336 -0.0143 0.5441 0.0525
-0.750 0.1743 0.02311 0.01231 -0.0141 0.5409 0.0540
-0.500 0.2027 0.02244 0.01156 -0.0142 0.5365 0.0542
-0.250 0.2307 0.02184 0.01088 -0.0141 0.5329 0.0544
0.000 0.2582 0.02130 0.01026 -0.0138 0.5297 0.0549
0.250 0.2854 0.02082 0.00970 -0.0135 0.5270 0.0556
0.500 0.3128 0.02054 0.00948 -0.0135 0.5225 0.0566
0.750 0.3400 0.02030 0.00924 -0.0134 0.5186 0.0579
1.000 0.3681 0.02011 0.00898 -0.0133 0.5153 0.0599
1.250 0.3964 0.02000 0.00874 -0.0131 0.5124 0.0644
1.500 0.4249 0.01996 0.00871 -0.0134 0.5083 0.0693
1.750 0.4528 0.02000 0.00873 -0.0135 0.5040 0.0743
2.000 0.4798 0.01995 0.00866 -0.0133 0.5004 0.0845
2.500 0.6059 0.01824 0.00891 -0.0279 0.4911 1.0000
2.750 0.6311 0.01848 0.00908 -0.0275 0.4868 1.0000
3.000 0.6561 0.01863 0.00913 -0.0269 0.4833 1.0000
3.250 0.6811 0.01882 0.00924 -0.0263 0.4797 1.0000
3.500 0.7060 0.01918 0.00966 -0.0262 0.4738 1.0000
3.750 0.7309 0.01933 0.00976 -0.0256 0.4694 1.0000
4.000 0.7556 0.01938 0.00970 -0.0249 0.4660 1.0000
4.250 0.7802 0.01982 0.01026 -0.0248 0.4595 1.0000
4.500 0.8048 0.02000 0.01045 -0.0243 0.4548 1.0000
4.750 0.8296 0.02006 0.01044 -0.0235 0.4514 1.0000
5.000 0.8535 0.02053 0.01105 -0.0234 0.4451 1.0000
5.250 0.8778 0.02074 0.01129 -0.0229 0.4401 1.0000
5.500 0.9026 0.02079 0.01132 -0.0222 0.4365 1.0000
5.750 0.9259 0.02131 0.01201 -0.0220 0.4298 1.0000
6.000 0.9500 0.02150 0.01226 -0.0215 0.4248 1.0000
6.250 0.9746 0.02155 0.01231 -0.0208 0.4209 1.0000
6.500 0.9969 0.02214 0.01311 -0.0206 0.4134 1.0000
6.750 1.0211 0.02224 0.01325 -0.0199 0.4085 1.0000
7.000 1.0437 0.02267 0.01383 -0.0195 0.4022 1.0000
7.250 1.0665 0.02300 0.01430 -0.0190 0.3960 1.0000
7.500 1.0907 0.02308 0.01442 -0.0183 0.3914 1.0000
7.750 1.1112 0.02373 0.01530 -0.0179 0.3832 1.0000
8.000 1.1348 0.02372 0.01536 -0.0171 0.3762 1.0000
8.250 1.1560 0.02387 0.01564 -0.0164 0.3642 1.0000
8.500 1.1764 0.02394 0.01576 -0.0156 0.3481 1.0000
8.750 1.1937 0.02446 0.01639 -0.0149 0.3295 1.0000
9.000 1.2105 0.02505 0.01707 -0.0141 0.3132 1.0000
9.250 1.2236 0.02582 0.01783 -0.0131 0.2915 1.0000
9.500 1.2305 0.02716 0.01913 -0.0121 0.2661 1.0000
9.750 1.2323 0.02889 0.02082 -0.0110 0.2460 1.0000
10.000 1.2252 0.03130 0.02322 -0.0099 0.2302 1.0000
10.250 1.2125 0.03428 0.02614 -0.0089 0.2131 1.0000
10.500 1.2018 0.03747 0.02929 -0.0085 0.1957 1.0000
10.750 1.1896 0.04105 0.03279 -0.0083 0.1756 1.0000
11.250 1.1574 0.04943 0.04084 -0.0086 0.1103 1.0000
11.500 1.1363 0.05438 0.04553 -0.0091 0.0846 1.0000
11.750 1.1141 0.05963 0.05054 -0.0097 0.0487 1.0000
12.000 1.0990 0.06435 0.05515 -0.0104 0.0390 1.0000
12.250 1.0900 0.06859 0.05940 -0.0111 0.0349 1.0000
12.500 1.0828 0.07274 0.06363 -0.0119 0.0320 1.0000
12.750 1.0776 0.07675 0.06777 -0.0127 0.0306 1.0000
13.000 1.0714 0.08105 0.07221 -0.0137 0.0293 1.0000
13.250 1.0664 0.08525 0.07654 -0.0148 0.0287 1.0000
13.500 1.0584 0.09005 0.08148 -0.0161 0.0277 1.0000
13.750 1.0506 0.09491 0.08648 -0.0176 0.0269 1.0000
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