A18 (original) (a18-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: A18 (original) (a18-il) Reynolds number: 50,000 Max Cl/Cd: 44.62 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-a18-il-50000-n5.txt Download as CSV file: xf-a18-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: A18 (original)
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4071 0.09802 0.09099 -0.0289 1.0000 0.0592
-8.750 -0.4102 0.09505 0.08811 -0.0290 1.0000 0.0593
-8.500 -0.4116 0.09188 0.08503 -0.0299 1.0000 0.0602
-8.250 -0.4115 0.08845 0.08169 -0.0316 1.0000 0.0612
-8.000 -0.4099 0.08470 0.07801 -0.0339 1.0000 0.0620
-7.750 -0.4063 0.08056 0.07392 -0.0369 1.0000 0.0626
-7.500 -0.4002 0.07601 0.06941 -0.0404 1.0000 0.0627
-7.250 -0.3908 0.07090 0.06429 -0.0449 1.0000 0.0629
-7.000 -0.3763 0.06468 0.05799 -0.0514 1.0000 0.0638
-6.750 -0.3539 0.05674 0.04982 -0.0607 1.0000 0.0674
-6.500 -0.3406 0.05568 0.04875 -0.0592 1.0000 0.0729
-6.250 -0.3105 0.04826 0.04089 -0.0674 1.0000 0.0761
-6.000 -0.2827 0.04384 0.03607 -0.0720 1.0000 0.0844
-5.750 -0.2518 0.03932 0.03099 -0.0762 1.0000 0.0892
-5.500 -0.2160 0.03458 0.02532 -0.0809 1.0000 0.0950
-5.250 -0.1943 0.03373 0.02442 -0.0805 1.0000 0.1019
-5.000 -0.1630 0.03102 0.02104 -0.0825 1.0000 0.1057
-4.750 -0.1328 0.02887 0.01828 -0.0838 1.0000 0.1088
-4.500 -0.1070 0.02768 0.01693 -0.0840 1.0000 0.1122
-4.250 -0.0806 0.02674 0.01573 -0.0842 1.0000 0.1190
-4.000 -0.0548 0.02590 0.01464 -0.0842 1.0000 0.1261
-3.750 -0.0286 0.02513 0.01369 -0.0843 1.0000 0.1319
-3.500 -0.0016 0.02439 0.01267 -0.0843 1.0000 0.1383
-3.250 0.0245 0.02388 0.01209 -0.0844 1.0000 0.1465
-3.000 0.0511 0.02355 0.01167 -0.0845 1.0000 0.1609
-2.750 0.0778 0.02324 0.01129 -0.0847 1.0000 0.1787
-2.500 0.1048 0.02293 0.01101 -0.0850 1.0000 0.2006
-2.250 0.1317 0.02272 0.01081 -0.0853 1.0000 0.2380
-2.000 0.1632 0.02244 0.01082 -0.0868 0.9975 0.2925
-1.750 0.2030 0.02223 0.01088 -0.0897 0.9904 0.3841
-1.500 0.2417 0.02162 0.01089 -0.0923 0.9840 0.5131
-1.250 0.2670 0.02038 0.01064 -0.0913 0.9711 1.0000
-1.000 0.3075 0.02063 0.01054 -0.0942 0.9611 1.0000
-0.750 0.3487 0.02087 0.01052 -0.0971 0.9516 1.0000
-0.500 0.3849 0.02107 0.01056 -0.0991 0.9401 1.0000
-0.250 0.4207 0.02127 0.01062 -0.1009 0.9284 1.0000
0.000 0.4573 0.02143 0.01069 -0.1028 0.9169 1.0000
0.250 0.4954 0.02156 0.01077 -0.1049 0.9063 1.0000
0.500 0.5336 0.02166 0.01085 -0.1069 0.8960 1.0000
1.000 0.5996 0.02199 0.01123 -0.1090 0.8723 1.0000
1.250 0.6326 0.02214 0.01143 -0.1100 0.8610 1.0000
1.500 0.6664 0.02226 0.01161 -0.1110 0.8500 1.0000
1.750 0.7008 0.02233 0.01181 -0.1120 0.8391 1.0000
2.000 0.7313 0.02251 0.01210 -0.1123 0.8262 1.0000
2.250 0.7625 0.02261 0.01232 -0.1126 0.8123 1.0000
2.500 0.7955 0.02249 0.01236 -0.1128 0.7962 1.0000
2.750 0.8231 0.02246 0.01247 -0.1119 0.7748 1.0000
3.000 0.8547 0.02222 0.01236 -0.1114 0.7537 1.0000
3.250 0.8817 0.02224 0.01255 -0.1103 0.7305 1.0000
3.500 0.9104 0.02218 0.01263 -0.1094 0.7067 1.0000
3.750 0.9367 0.02223 0.01283 -0.1082 0.6802 1.0000
4.000 0.9616 0.02243 0.01320 -0.1069 0.6535 1.0000
4.250 0.9866 0.02262 0.01360 -0.1056 0.6240 1.0000
4.500 1.0105 0.02284 0.01395 -0.1039 0.5892 1.0000
4.750 1.0324 0.02314 0.01427 -0.1018 0.5429 1.0000
5.000 1.0494 0.02369 0.01478 -0.0990 0.4771 1.0000
5.250 1.0632 0.02458 0.01526 -0.0959 0.3944 1.0000
5.500 1.0745 0.02598 0.01632 -0.0931 0.2924 1.0000
5.750 1.0810 0.02823 0.01777 -0.0904 0.2119 1.0000
6.000 1.0911 0.03036 0.01950 -0.0884 0.1428 1.0000
6.250 1.1017 0.03253 0.02129 -0.0863 0.0921 1.0000
6.500 1.1125 0.03480 0.02344 -0.0839 0.0702 1.0000
6.750 1.1250 0.03691 0.02560 -0.0817 0.0585 1.0000
7.000 1.1382 0.03909 0.02782 -0.0797 0.0513 1.0000
7.250 1.1571 0.04122 0.03022 -0.0779 0.0467 1.0000
7.500 1.1744 0.04346 0.03252 -0.0765 0.0425 1.0000
7.750 1.1953 0.04601 0.03544 -0.0754 0.0388 1.0000
8.000 1.2160 0.04882 0.03861 -0.0742 0.0364 1.0000
8.250 1.2334 0.05193 0.04206 -0.0729 0.0350 1.0000
8.500 1.2462 0.05511 0.04553 -0.0713 0.0337 1.0000
8.750 1.2549 0.05844 0.04906 -0.0697 0.0324 1.0000
9.000 1.2566 0.06214 0.05319 -0.0672 0.0316 1.0000
9.250 1.2519 0.06587 0.05741 -0.0642 0.0310 1.0000
9.500 1.2410 0.06949 0.06142 -0.0610 0.0306 1.0000
9.750 1.2269 0.07336 0.06564 -0.0582 0.0304 1.0000
10.000 1.2106 0.07758 0.07017 -0.0563 0.0303 1.0000
10.250 1.1925 0.08227 0.07514 -0.0554 0.0303 1.0000
10.500 1.1731 0.08749 0.08060 -0.0556 0.0304 1.0000
10.750 1.1528 0.09337 0.08670 -0.0571 0.0305 1.0000
11.000 1.1327 0.09993 0.09343 -0.0598 0.0308 1.0000
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Polar data table (+)
Polar graphs
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