S3014-095-85 (s3014-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S3014-095-85 (s3014-il) Reynolds number: 50,000 Max Cl/Cd: 32.54 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3014-il-50000.txt Download as CSV file: xf-s3014-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S3014-095-85
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4390 0.11761 0.11089 -0.0106 1.0000 0.2110
-9.250 -0.4142 0.11166 0.10491 -0.0093 1.0000 0.2196
-9.000 -0.4324 0.11100 0.10441 -0.0121 1.0000 0.2261
-8.750 -0.4097 0.10580 0.09918 -0.0108 1.0000 0.2375
-8.500 -0.4024 0.10210 0.09553 -0.0111 1.0000 0.2456
-8.250 -0.4229 0.10172 0.09531 -0.0134 1.0000 0.2547
-8.000 -0.4022 0.09687 0.09045 -0.0121 1.0000 0.2675
-7.750 -0.3903 0.09297 0.08659 -0.0116 1.0000 0.2786
-7.500 -0.3862 0.08992 0.08361 -0.0114 1.0000 0.2908
-7.250 -0.3826 0.08709 0.08086 -0.0109 1.0000 0.3060
-7.000 -0.3815 0.08452 0.07838 -0.0100 1.0000 0.3231
-6.750 -0.3892 0.08259 0.07659 -0.0087 1.0000 0.3404
-6.500 -0.4045 0.08119 0.07535 -0.0073 1.0000 0.3565
-6.250 -0.3757 0.07658 0.07070 -0.0049 1.0000 0.3777
-6.000 -0.3799 0.07448 0.06872 -0.0023 1.0000 0.3958
-4.750 -0.4132 0.04566 0.03837 -0.0318 1.0000 0.1371
-4.500 -0.3987 0.04187 0.03420 -0.0313 1.0000 0.1300
-4.250 -0.3806 0.03837 0.02998 -0.0306 1.0000 0.1230
-4.000 -0.3619 0.03555 0.02677 -0.0297 1.0000 0.1205
-3.750 -0.3413 0.03302 0.02375 -0.0287 1.0000 0.1192
-3.500 -0.3193 0.03087 0.02115 -0.0277 1.0000 0.1198
-3.250 -0.2967 0.02919 0.01897 -0.0267 1.0000 0.1240
-3.000 -0.2748 0.02770 0.01741 -0.0258 1.0000 0.1322
-2.750 -0.2510 0.02635 0.01578 -0.0248 1.0000 0.1412
-2.500 -0.2265 0.02500 0.01441 -0.0239 1.0000 0.1566
-2.250 -0.2024 0.02371 0.01323 -0.0230 1.0000 0.1979
-2.000 -0.1465 0.01875 0.01190 -0.0243 1.0000 1.0000
-1.750 -0.1288 0.01893 0.01146 -0.0234 1.0000 1.0000
-1.500 -0.1114 0.01918 0.01124 -0.0225 1.0000 1.0000
-1.250 -0.0939 0.01947 0.01112 -0.0217 1.0000 1.0000
-1.000 -0.0763 0.01981 0.01113 -0.0209 1.0000 1.0000
-0.750 -0.0587 0.02019 0.01121 -0.0202 1.0000 1.0000
-0.500 -0.0410 0.02061 0.01138 -0.0196 1.0000 1.0000
-0.250 -0.0235 0.02108 0.01162 -0.0190 1.0000 1.0000
0.000 -0.0060 0.02159 0.01191 -0.0185 1.0000 1.0000
0.250 0.0114 0.02215 0.01228 -0.0181 1.0000 1.0000
0.500 0.0349 0.02288 0.01284 -0.0189 0.9973 1.0000
0.750 0.0880 0.02425 0.01399 -0.0253 0.9822 1.0000
1.000 0.1349 0.02540 0.01498 -0.0303 0.9657 1.0000
1.250 0.1811 0.02650 0.01598 -0.0350 0.9486 1.0000
1.500 0.2290 0.02759 0.01698 -0.0397 0.9310 1.0000
1.750 0.2749 0.02857 0.01791 -0.0438 0.9130 1.0000
2.000 0.3121 0.02938 0.01870 -0.0462 0.8934 1.0000
2.250 0.3578 0.03016 0.01948 -0.0498 0.8742 1.0000
2.500 0.3990 0.03083 0.02017 -0.0523 0.8544 1.0000
2.750 0.4372 0.03139 0.02079 -0.0541 0.8336 1.0000
3.000 0.4923 0.03161 0.02111 -0.0580 0.8144 1.0000
3.250 0.5212 0.03205 0.02162 -0.0579 0.7921 1.0000
3.500 0.5697 0.03188 0.02160 -0.0599 0.7725 1.0000
3.750 0.5996 0.03203 0.02184 -0.0592 0.7503 1.0000
4.000 0.6412 0.03153 0.02148 -0.0593 0.7302 1.0000
4.250 0.6712 0.03135 0.02144 -0.0580 0.7077 1.0000
4.500 0.7099 0.03050 0.02071 -0.0569 0.6871 1.0000
4.750 0.7378 0.03017 0.02048 -0.0550 0.6629 1.0000
5.000 0.7737 0.02917 0.01961 -0.0532 0.6408 1.0000
5.250 0.8034 0.02858 0.01909 -0.0511 0.6154 1.0000
5.500 0.8303 0.02825 0.01881 -0.0488 0.5882 1.0000
5.750 0.8569 0.02805 0.01862 -0.0467 0.5603 1.0000
6.000 0.8826 0.02804 0.01865 -0.0447 0.5319 1.0000
6.250 0.9073 0.02824 0.01883 -0.0427 0.5032 1.0000
6.500 0.9309 0.02867 0.01922 -0.0409 0.4748 1.0000
6.750 0.9535 0.02930 0.01984 -0.0392 0.4471 1.0000
7.000 0.9755 0.03007 0.02060 -0.0375 0.4201 1.0000
7.250 0.9975 0.03099 0.02154 -0.0360 0.3944 1.0000
7.500 1.0208 0.03189 0.02235 -0.0346 0.3695 1.0000
7.750 1.0395 0.03322 0.02379 -0.0330 0.3457 1.0000
8.000 1.0591 0.03461 0.02524 -0.0315 0.3233 1.0000
8.250 1.0794 0.03601 0.02667 -0.0301 0.3018 1.0000
8.500 1.0972 0.03772 0.02854 -0.0287 0.2819 1.0000
8.750 1.1130 0.03964 0.03065 -0.0270 0.2632 1.0000
9.000 1.1323 0.04128 0.03231 -0.0257 0.2445 1.0000
9.250 1.1499 0.04334 0.03444 -0.0242 0.2278 1.0000
9.500 1.1593 0.04565 0.03704 -0.0222 0.2120 1.0000
9.750 1.1694 0.04825 0.03988 -0.0203 0.1977 1.0000
10.000 1.1757 0.05070 0.04256 -0.0182 0.1828 1.0000
10.250 1.1809 0.05350 0.04561 -0.0160 0.1692 1.0000
10.500 1.1819 0.05597 0.04827 -0.0136 0.1546 1.0000
10.750 1.1809 0.05845 0.05088 -0.0112 0.1409 1.0000
11.000 1.1774 0.06067 0.05319 -0.0087 0.1273 1.0000
11.250 1.1752 0.06303 0.05557 -0.0065 0.1156 1.0000
11.500 1.1510 0.06721 0.06005 -0.0039 0.1147 1.0000
11.750 1.1252 0.07188 0.06495 -0.0026 0.1150 1.0000
12.000 1.0995 0.07732 0.07057 -0.0027 0.1161 1.0000
12.250 1.0734 0.08357 0.07694 -0.0042 0.1173 1.0000
12.500 1.0496 0.09045 0.08389 -0.0066 0.1182 1.0000
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Polar data table (+)
Polar graphs
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