S3016-095-87 (s3016-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S3016-095-87 (s3016-il) Reynolds number: 1,000,000 Max Cl/Cd: 99.13 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3016-il-1000000.txt Download as CSV file: xf-s3016-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4257 0.08403 0.08261 -0.0140 1.0000 0.0104
-9.500 -0.4289 0.07874 0.07734 -0.0161 1.0000 0.0105
-9.250 -0.4322 0.07360 0.07221 -0.0183 1.0000 0.0107
-9.000 -0.6699 0.03838 0.03640 -0.0444 1.0000 0.0064
-8.750 -0.6784 0.03193 0.02943 -0.0443 1.0000 0.0065
-8.500 -0.6801 0.02304 0.01957 -0.0454 0.9797 0.0068
-8.250 -0.6574 0.02091 0.01718 -0.0458 0.9647 0.0070
-8.000 -0.6374 0.01979 0.01586 -0.0448 0.9505 0.0072
-7.750 -0.6173 0.01890 0.01481 -0.0436 0.9390 0.0074
-7.250 -0.5748 0.01682 0.01237 -0.0415 0.9199 0.0079
-7.000 -0.5524 0.01581 0.01117 -0.0406 0.9121 0.0081
-6.750 -0.5287 0.01494 0.01015 -0.0398 0.9043 0.0085
-6.500 -0.5040 0.01434 0.00943 -0.0392 0.8976 0.0090
-6.250 -0.4778 0.01401 0.00899 -0.0388 0.8906 0.0094
-6.000 -0.4563 0.01242 0.00721 -0.0378 0.8841 0.0102
-5.750 -0.4306 0.01193 0.00668 -0.0374 0.8773 0.0108
-5.250 -0.3783 0.01113 0.00575 -0.0366 0.8649 0.0123
-5.000 -0.3519 0.01081 0.00535 -0.0362 0.8587 0.0130
-4.750 -0.3267 0.01007 0.00451 -0.0357 0.8524 0.0142
-4.500 -0.3006 0.00964 0.00403 -0.0353 0.8460 0.0156
-4.250 -0.2736 0.00938 0.00373 -0.0350 0.8401 0.0171
-4.000 -0.2464 0.00913 0.00344 -0.0348 0.8336 0.0183
-3.750 -0.2197 0.00879 0.00300 -0.0344 0.8276 0.0194
-3.500 -0.1927 0.00840 0.00256 -0.0342 0.8208 0.0220
-3.250 -0.1655 0.00819 0.00229 -0.0339 0.8144 0.0241
-3.000 -0.1377 0.00801 0.00207 -0.0338 0.8074 0.0259
-2.750 -0.1108 0.00771 0.00181 -0.0334 0.8004 0.0421
-2.500 -0.0846 0.00721 0.00159 -0.0332 0.7929 0.1147
-2.250 -0.0580 0.00691 0.00144 -0.0330 0.7854 0.1698
-2.000 -0.0311 0.00660 0.00133 -0.0328 0.7768 0.2298
-1.750 -0.0043 0.00636 0.00123 -0.0326 0.7673 0.2855
-1.500 0.0224 0.00610 0.00114 -0.0324 0.7570 0.3491
-1.250 0.0494 0.00587 0.00107 -0.0322 0.7467 0.4094
-1.000 0.0759 0.00563 0.00101 -0.0320 0.7365 0.4816
-0.750 0.1018 0.00535 0.00097 -0.0316 0.7256 0.5699
-0.500 0.1266 0.00502 0.00095 -0.0309 0.7137 0.6780
-0.250 0.1518 0.00481 0.00094 -0.0302 0.7009 0.7522
0.000 0.1768 0.00464 0.00094 -0.0294 0.6872 0.8155
0.250 0.2014 0.00449 0.00095 -0.0284 0.6729 0.8847
0.500 0.2366 0.00446 0.00099 -0.0296 0.6573 0.9459
0.750 0.2790 0.00455 0.00101 -0.0327 0.6395 0.9707
1.000 0.3158 0.00466 0.00104 -0.0345 0.6205 0.9835
1.250 0.3550 0.00478 0.00105 -0.0370 0.5996 0.9907
1.500 0.3934 0.00489 0.00107 -0.0393 0.5780 0.9960
1.750 0.4338 0.00502 0.00109 -0.0421 0.5533 1.0000
2.000 0.4591 0.00515 0.00112 -0.0416 0.5302 1.0000
2.250 0.4844 0.00529 0.00117 -0.0411 0.5072 1.0000
2.500 0.5096 0.00546 0.00123 -0.0405 0.4826 1.0000
2.750 0.5349 0.00563 0.00130 -0.0400 0.4571 1.0000
3.000 0.5601 0.00581 0.00139 -0.0395 0.4316 1.0000
3.250 0.5852 0.00602 0.00149 -0.0390 0.4042 1.0000
3.500 0.6104 0.00624 0.00160 -0.0385 0.3786 1.0000
3.750 0.6353 0.00648 0.00173 -0.0380 0.3509 1.0000
4.000 0.6602 0.00672 0.00187 -0.0375 0.3255 1.0000
4.250 0.6851 0.00697 0.00201 -0.0370 0.3003 1.0000
4.500 0.7101 0.00721 0.00217 -0.0365 0.2797 1.0000
4.750 0.7351 0.00745 0.00234 -0.0360 0.2598 1.0000
5.000 0.7599 0.00770 0.00251 -0.0355 0.2417 1.0000
5.250 0.7849 0.00794 0.00269 -0.0350 0.2259 1.0000
5.500 0.8098 0.00818 0.00288 -0.0345 0.2096 1.0000
5.750 0.8347 0.00842 0.00308 -0.0340 0.1959 1.0000
6.000 0.8596 0.00868 0.00329 -0.0335 0.1823 1.0000
6.250 0.8842 0.00895 0.00351 -0.0330 0.1678 1.0000
6.500 0.9088 0.00922 0.00374 -0.0325 0.1550 1.0000
6.750 0.9333 0.00952 0.00400 -0.0319 0.1412 1.0000
7.000 0.9575 0.00984 0.00427 -0.0314 0.1268 1.0000
7.250 0.9814 0.01020 0.00456 -0.0308 0.1113 1.0000
7.500 1.0050 0.01059 0.00487 -0.0303 0.0965 1.0000
7.750 1.0286 0.01098 0.00521 -0.0297 0.0835 1.0000
8.000 1.0521 0.01136 0.00555 -0.0291 0.0728 1.0000
8.250 1.0754 0.01176 0.00592 -0.0285 0.0632 1.0000
8.500 1.0982 0.01221 0.00632 -0.0278 0.0535 1.0000
8.750 1.1207 0.01268 0.00674 -0.0271 0.0444 1.0000
9.000 1.1430 0.01316 0.00719 -0.0264 0.0358 1.0000
9.250 1.1642 0.01373 0.00772 -0.0255 0.0265 1.0000
9.500 1.1837 0.01446 0.00839 -0.0245 0.0159 1.0000
9.750 1.2012 0.01539 0.00928 -0.0231 0.0087 1.0000
10.000 1.2214 0.01600 0.00993 -0.0220 0.0073 1.0000
10.250 1.2386 0.01688 0.01088 -0.0206 0.0061 1.0000
10.500 1.2582 0.01747 0.01154 -0.0195 0.0057 1.0000
10.750 1.2765 0.01813 0.01227 -0.0183 0.0054 1.0000
11.000 1.2935 0.01885 0.01308 -0.0169 0.0051 1.0000
11.250 1.3090 0.01963 0.01393 -0.0154 0.0047 1.0000
11.500 1.3200 0.02067 0.01506 -0.0133 0.0044 1.0000
11.750 1.3261 0.02169 0.01619 -0.0103 0.0043 1.0000
12.000 1.3199 0.02340 0.01807 -0.0061 0.0040 1.0000
12.250 1.3261 0.02451 0.01926 -0.0039 0.0040 1.0000
12.500 1.3347 0.02553 0.02037 -0.0021 0.0038 1.0000
12.750 1.3366 0.02710 0.02205 0.0000 0.0038 1.0000
13.000 1.3423 0.02848 0.02353 0.0015 0.0037 1.0000
13.250 1.3435 0.03034 0.02549 0.0030 0.0036 1.0000
13.500 1.3418 0.03256 0.02785 0.0043 0.0036 1.0000
13.750 1.3458 0.03442 0.02980 0.0050 0.0035 1.0000
14.000 1.3429 0.03707 0.03258 0.0056 0.0034 1.0000
14.250 1.3423 0.03967 0.03528 0.0058 0.0033 1.0000
14.500 1.3351 0.04320 0.03895 0.0055 0.0034 1.0000
14.750 1.3303 0.04669 0.04256 0.0048 0.0032 1.0000
15.000 1.3212 0.05097 0.04697 0.0036 0.0033 1.0000
15.250 1.3124 0.05548 0.05161 0.0020 0.0032 1.0000
15.500 1.2997 0.06080 0.05708 -0.0002 0.0033 1.0000
15.750 1.2880 0.06634 0.06274 -0.0027 0.0032 1.0000
16.000 1.2728 0.07266 0.06920 -0.0058 0.0032 1.0000
16.250 1.2571 0.07932 0.07599 -0.0091 0.0032 1.0000
16.500 1.2415 0.08624 0.08303 -0.0127 0.0032 1.0000
16.750 1.2244 0.09354 0.09046 -0.0164 0.0032 1.0000
17.000 1.2057 0.10136 0.09841 -0.0205 0.0033 1.0000
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Polar data table (+)
Polar graphs
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