USA 46 AIRFOIL (usa46-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 46 AIRFOIL (usa46-il) Reynolds number: 200,000 Max Cl/Cd: 63.61 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa46-il-200000-n5.txt Download as CSV file: xf-usa46-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 46 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5155 0.08659 0.08310 -0.0136 1.0000 0.0118
-8.500 -0.5185 0.08200 0.07856 -0.0157 1.0000 0.0117
-8.250 -0.5232 0.07755 0.07417 -0.0178 1.0000 0.0116
-8.000 -0.5298 0.07270 0.06940 -0.0205 1.0000 0.0116
-7.750 -0.5322 0.06620 0.06295 -0.0267 1.0000 0.0116
-7.500 -0.5312 0.05741 0.05415 -0.0364 1.0000 0.0114
-7.250 -0.5326 0.04071 0.03714 -0.0500 1.0000 0.0109
-7.000 -0.5229 0.03022 0.02576 -0.0555 1.0000 0.0109
-6.750 -0.5045 0.02550 0.02035 -0.0566 1.0000 0.0113
-6.500 -0.4833 0.02239 0.01663 -0.0567 1.0000 0.0119
-6.250 -0.4601 0.02078 0.01465 -0.0563 1.0000 0.0128
-6.000 -0.4382 0.01792 0.01134 -0.0560 1.0000 0.0149
-5.750 -0.4145 0.01657 0.00976 -0.0554 1.0000 0.0167
-5.500 -0.3903 0.01553 0.00853 -0.0548 1.0000 0.0193
-5.250 -0.3659 0.01477 0.00758 -0.0541 1.0000 0.0234
-5.000 -0.3415 0.01405 0.00681 -0.0536 1.0000 0.0310
-4.750 -0.3171 0.01361 0.00628 -0.0530 1.0000 0.0406
-4.500 -0.2928 0.01321 0.00582 -0.0524 1.0000 0.0494
-4.250 -0.2687 0.01292 0.00546 -0.0517 1.0000 0.0589
-4.000 -0.2447 0.01257 0.00505 -0.0511 1.0000 0.0660
-3.750 -0.2207 0.01221 0.00459 -0.0504 1.0000 0.0707
-3.500 -0.1932 0.01183 0.00419 -0.0505 0.9985 0.0796
-3.250 -0.1581 0.01147 0.00382 -0.0522 0.9933 0.0902
-3.000 -0.1231 0.01118 0.00356 -0.0538 0.9877 0.1062
-2.750 -0.0889 0.01097 0.00334 -0.0552 0.9813 0.1265
-2.500 -0.0541 0.01080 0.00316 -0.0567 0.9750 0.1448
-2.250 -0.0201 0.01062 0.00299 -0.0580 0.9676 0.1624
-2.000 0.0132 0.01044 0.00280 -0.0592 0.9596 0.1781
-1.750 0.0486 0.01024 0.00264 -0.0608 0.9519 0.1951
-1.500 0.0834 0.01000 0.00247 -0.0622 0.9405 0.2147
-1.250 0.1192 0.00971 0.00229 -0.0638 0.9272 0.2466
-1.000 0.1543 0.00926 0.00215 -0.0654 0.9123 0.3281
-0.750 0.1859 0.00867 0.00210 -0.0662 0.8955 0.4929
-0.500 0.2139 0.00825 0.00212 -0.0659 0.8758 0.6314
-0.250 0.2411 0.00805 0.00212 -0.0651 0.8548 0.7296
0.000 0.2672 0.00797 0.00207 -0.0643 0.8305 0.7835
0.250 0.2935 0.00786 0.00200 -0.0634 0.8073 0.8257
0.500 0.3292 0.00765 0.00191 -0.0645 0.7850 0.9069
0.750 0.3622 0.00771 0.00188 -0.0654 0.7602 1.0000
1.000 0.3887 0.00784 0.00189 -0.0648 0.7349 1.0000
1.250 0.4149 0.00798 0.00192 -0.0643 0.7090 1.0000
1.500 0.4411 0.00814 0.00197 -0.0637 0.6837 1.0000
1.750 0.4672 0.00832 0.00206 -0.0631 0.6575 1.0000
2.000 0.4932 0.00851 0.00215 -0.0626 0.6302 1.0000
2.250 0.5189 0.00873 0.00226 -0.0620 0.6015 1.0000
2.500 0.5446 0.00897 0.00242 -0.0614 0.5735 1.0000
2.750 0.5704 0.00921 0.00259 -0.0608 0.5466 1.0000
3.000 0.5959 0.00948 0.00278 -0.0603 0.5170 1.0000
3.250 0.6212 0.00978 0.00301 -0.0597 0.4818 1.0000
3.500 0.6456 0.01015 0.00322 -0.0589 0.4274 1.0000
3.750 0.6672 0.01087 0.00347 -0.0579 0.3368 1.0000
4.000 0.6912 0.01142 0.00383 -0.0573 0.2896 1.0000
4.250 0.7150 0.01202 0.00422 -0.0567 0.2292 1.0000
4.500 0.7340 0.01351 0.00491 -0.0558 0.0769 1.0000
4.750 0.7559 0.01465 0.00575 -0.0549 0.0263 1.0000
5.000 0.7801 0.01541 0.00658 -0.0541 0.0202 1.0000
5.250 0.8045 0.01607 0.00739 -0.0534 0.0171 1.0000
5.500 0.8279 0.01692 0.00839 -0.0526 0.0152 1.0000
5.750 0.8500 0.01796 0.00960 -0.0516 0.0140 1.0000
6.000 0.8702 0.01939 0.01115 -0.0503 0.0127 1.0000
6.250 0.8891 0.02134 0.01322 -0.0489 0.0113 1.0000
6.500 0.9116 0.02263 0.01464 -0.0479 0.0107 1.0000
6.750 0.9336 0.02427 0.01646 -0.0468 0.0103 1.0000
7.000 0.9554 0.02618 0.01859 -0.0456 0.0099 1.0000
7.250 0.9766 0.02833 0.02101 -0.0445 0.0097 1.0000
7.500 0.9963 0.03078 0.02379 -0.0432 0.0095 1.0000
7.750 1.0144 0.03330 0.02672 -0.0418 0.0091 1.0000
8.000 1.0312 0.03553 0.02926 -0.0405 0.0086 1.0000
8.250 1.0472 0.03727 0.03117 -0.0395 0.0079 1.0000
8.500 1.0598 0.03957 0.03371 -0.0383 0.0075 1.0000
8.750 1.0678 0.04281 0.03726 -0.0367 0.0073 1.0000
9.000 1.0717 0.04638 0.04119 -0.0349 0.0072 1.0000
9.250 1.0710 0.05011 0.04526 -0.0330 0.0072 1.0000
9.500 1.0654 0.05387 0.04934 -0.0311 0.0072 1.0000
9.750 1.0537 0.05733 0.05305 -0.0288 0.0072 1.0000
10.000 1.0390 0.06073 0.05667 -0.0271 0.0073 1.0000
10.250 1.0210 0.06505 0.06119 -0.0274 0.0073 1.0000
10.500 1.0033 0.07033 0.06666 -0.0298 0.0074 1.0000
10.750 0.9819 0.07784 0.07438 -0.0351 0.0075 1.0000
11.000 0.9491 0.09127 0.08806 -0.0456 0.0079 1.0000
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Polar data table (+)
Polar graphs
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