S3016-095-87 (s3016-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S3016-095-87 (s3016-il) Reynolds number: 50,000 Max Cl/Cd: 31.76 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3016-il-50000.txt Download as CSV file: xf-s3016-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S3016-095-87
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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.4339 0.08759 0.08143 -0.0047 1.0000 0.3273
-7.000 -0.4339 0.08471 0.07864 -0.0040 1.0000 0.3420
-6.750 -0.4112 0.08021 0.07414 -0.0025 1.0000 0.3604
-6.000 -0.4733 0.05461 0.04792 -0.0359 1.0000 0.1389
-5.750 -0.4709 0.04933 0.04210 -0.0357 1.0000 0.1254
-5.500 -0.4612 0.04569 0.03834 -0.0341 1.0000 0.1214
-5.250 -0.4523 0.04194 0.03415 -0.0327 1.0000 0.1179
-5.000 -0.4403 0.03887 0.03064 -0.0312 1.0000 0.1183
-4.750 -0.4258 0.03611 0.02745 -0.0296 1.0000 0.1201
-4.500 -0.4085 0.03340 0.02427 -0.0281 1.0000 0.1207
-4.250 -0.3889 0.03098 0.02136 -0.0266 1.0000 0.1224
-4.000 -0.3680 0.02887 0.01878 -0.0252 1.0000 0.1277
-3.750 -0.3474 0.02733 0.01708 -0.0238 1.0000 0.1390
-3.500 -0.3251 0.02563 0.01529 -0.0225 1.0000 0.1513
-3.250 -0.3023 0.02407 0.01378 -0.0212 1.0000 0.1740
-3.000 -0.2787 0.02229 0.01233 -0.0201 1.0000 0.2423
-2.750 -0.2640 0.02004 0.01154 -0.0174 1.0000 0.4511
-2.500 -0.2581 0.01867 0.01145 -0.0112 1.0000 0.6699
-2.250 -0.1510 0.01805 0.01065 -0.0227 1.0000 1.0000
-2.000 -0.1439 0.01802 0.01022 -0.0207 1.0000 1.0000
-1.750 -0.1317 0.01812 0.00996 -0.0191 1.0000 1.0000
-1.500 -0.1174 0.01829 0.00980 -0.0178 1.0000 1.0000
-1.250 -0.1020 0.01851 0.00970 -0.0166 1.0000 1.0000
-1.000 -0.0859 0.01877 0.00971 -0.0156 1.0000 1.0000
-0.750 -0.0694 0.01909 0.00979 -0.0147 1.0000 1.0000
-0.500 -0.0526 0.01945 0.00994 -0.0139 1.0000 1.0000
-0.250 -0.0357 0.01985 0.01013 -0.0132 1.0000 1.0000
0.000 -0.0188 0.02030 0.01041 -0.0126 1.0000 1.0000
0.250 -0.0019 0.02080 0.01076 -0.0121 1.0000 1.0000
0.500 0.0149 0.02135 0.01118 -0.0116 1.0000 1.0000
0.750 0.0341 0.02200 0.01171 -0.0117 0.9989 1.0000
1.000 0.0914 0.02338 0.01294 -0.0190 0.9817 1.0000
1.250 0.1428 0.02453 0.01401 -0.0249 0.9628 1.0000
1.500 0.1981 0.02569 0.01511 -0.0311 0.9438 1.0000
1.750 0.2438 0.02660 0.01600 -0.0353 0.9229 1.0000
2.000 0.2963 0.02745 0.01688 -0.0404 0.9019 1.0000
2.250 0.3389 0.02814 0.01760 -0.0434 0.8798 1.0000
2.500 0.3935 0.02864 0.01818 -0.0480 0.8583 1.0000
2.750 0.4340 0.02906 0.01870 -0.0500 0.8348 1.0000
3.000 0.4932 0.02899 0.01878 -0.0541 0.8139 1.0000
3.250 0.5245 0.02919 0.01907 -0.0539 0.7894 1.0000
3.500 0.5641 0.02900 0.01904 -0.0541 0.7666 1.0000
3.750 0.6025 0.02856 0.01871 -0.0536 0.7435 1.0000
4.000 0.6318 0.02832 0.01858 -0.0520 0.7182 1.0000
4.250 0.6633 0.02782 0.01821 -0.0502 0.6934 1.0000
4.500 0.6971 0.02699 0.01746 -0.0482 0.6693 1.0000
4.750 0.7252 0.02648 0.01699 -0.0457 0.6420 1.0000
5.000 0.7519 0.02611 0.01668 -0.0432 0.6132 1.0000
5.250 0.7767 0.02599 0.01655 -0.0408 0.5827 1.0000
5.500 0.8000 0.02613 0.01668 -0.0385 0.5509 1.0000
5.750 0.8237 0.02639 0.01690 -0.0365 0.5196 1.0000
6.000 0.8471 0.02681 0.01731 -0.0345 0.4891 1.0000
6.250 0.8700 0.02739 0.01783 -0.0327 0.4592 1.0000
6.500 0.8923 0.02817 0.01858 -0.0311 0.4307 1.0000
6.750 0.9140 0.02908 0.01947 -0.0295 0.4030 1.0000
7.000 0.9355 0.03015 0.02057 -0.0280 0.3769 1.0000
7.250 0.9577 0.03124 0.02161 -0.0266 0.3522 1.0000
7.500 0.9784 0.03250 0.02290 -0.0252 0.3282 1.0000
7.750 0.9973 0.03409 0.02461 -0.0238 0.3061 1.0000
8.000 1.0188 0.03544 0.02592 -0.0225 0.2845 1.0000
8.250 1.0358 0.03742 0.02810 -0.0211 0.2656 1.0000
8.500 1.0520 0.03935 0.03027 -0.0196 0.2469 1.0000
8.750 1.0698 0.04131 0.03233 -0.0182 0.2297 1.0000
9.000 1.0879 0.04336 0.03444 -0.0168 0.2134 1.0000
9.250 1.1025 0.04562 0.03683 -0.0153 0.1977 1.0000
9.500 1.1150 0.04821 0.03962 -0.0136 0.1840 1.0000
9.750 1.1244 0.05070 0.04231 -0.0118 0.1700 1.0000
10.000 1.1116 0.05516 0.04745 -0.0092 0.1646 1.0000
10.250 1.1164 0.05800 0.05043 -0.0074 0.1533 1.0000
10.500 1.1017 0.06226 0.05506 -0.0053 0.1487 1.0000
10.750 1.1029 0.06568 0.05856 -0.0038 0.1407 1.0000
11.000 1.0775 0.07066 0.06380 -0.0022 0.1407 1.0000
11.250 1.0510 0.07575 0.06901 -0.0013 0.1416 1.0000
11.500 1.0248 0.08168 0.07502 -0.0021 0.1425 1.0000
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Polar data table (+)
Polar graphs
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