S3016-095-87 (s3016-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S3016-095-87 (s3016-il) Reynolds number: 500,000 Max Cl/Cd: 78.77 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3016-il-500000-n5.txt Download as CSV file: xf-s3016-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5181 0.09612 0.09389 -0.0110 1.0000 0.0054
-10.000 -0.5245 0.09015 0.08796 -0.0140 1.0000 0.0055
-9.500 -0.7376 0.03509 0.03220 -0.0448 1.0000 0.0048
-9.250 -0.7295 0.03213 0.02897 -0.0445 1.0000 0.0050
-9.000 -0.7185 0.02944 0.02600 -0.0440 1.0000 0.0051
-8.750 -0.6978 0.02685 0.02308 -0.0449 0.9819 0.0053
-8.500 -0.6757 0.02391 0.01972 -0.0458 0.9657 0.0055
-8.250 -0.6534 0.02199 0.01748 -0.0459 0.9525 0.0058
-8.000 -0.6328 0.02044 0.01563 -0.0451 0.9402 0.0061
-7.750 -0.6126 0.01905 0.01396 -0.0440 0.9293 0.0064
-7.500 -0.5910 0.01798 0.01267 -0.0431 0.9197 0.0068
-7.250 -0.5675 0.01737 0.01187 -0.0423 0.9115 0.0072
-7.000 -0.5459 0.01627 0.01061 -0.0414 0.9030 0.0078
-6.750 -0.5217 0.01571 0.00996 -0.0408 0.8956 0.0082
-6.500 -0.4974 0.01515 0.00929 -0.0402 0.8882 0.0087
-6.250 -0.4726 0.01454 0.00856 -0.0396 0.8812 0.0094
-6.000 -0.4480 0.01392 0.00781 -0.0390 0.8742 0.0102
-5.750 -0.4225 0.01342 0.00719 -0.0385 0.8677 0.0109
-5.500 -0.3975 0.01283 0.00648 -0.0379 0.8610 0.0116
-5.250 -0.3721 0.01234 0.00595 -0.0375 0.8547 0.0129
-5.000 -0.3459 0.01201 0.00556 -0.0372 0.8480 0.0143
-4.750 -0.3198 0.01165 0.00511 -0.0368 0.8419 0.0156
-4.500 -0.2931 0.01133 0.00472 -0.0365 0.8350 0.0164
-4.250 -0.2673 0.01087 0.00415 -0.0360 0.8287 0.0179
-4.000 -0.2407 0.01050 0.00374 -0.0357 0.8216 0.0197
-3.500 -0.1868 0.00999 0.00309 -0.0351 0.8079 0.0225
-3.250 -0.1598 0.00978 0.00279 -0.0348 0.8012 0.0244
-3.000 -0.1325 0.00953 0.00253 -0.0346 0.7936 0.0291
-2.750 -0.1059 0.00924 0.00229 -0.0343 0.7864 0.0491
-2.500 -0.0791 0.00892 0.00210 -0.0341 0.7781 0.0864
-2.250 -0.0524 0.00865 0.00193 -0.0339 0.7700 0.1252
-2.000 -0.0257 0.00838 0.00178 -0.0337 0.7608 0.1714
-1.750 0.0010 0.00809 0.00167 -0.0335 0.7514 0.2272
-1.500 0.0274 0.00782 0.00156 -0.0333 0.7415 0.2888
-1.250 0.0539 0.00759 0.00146 -0.0330 0.7297 0.3467
-1.000 0.0793 0.00724 0.00139 -0.0326 0.7155 0.4417
-0.750 0.1045 0.00693 0.00134 -0.0321 0.7005 0.5323
-0.500 0.1306 0.00677 0.00129 -0.0316 0.6858 0.5889
-0.250 0.1562 0.00660 0.00126 -0.0311 0.6708 0.6499
0.000 0.1812 0.00643 0.00125 -0.0304 0.6549 0.7144
0.250 0.2059 0.00629 0.00125 -0.0295 0.6386 0.7775
0.500 0.2307 0.00617 0.00126 -0.0285 0.6211 0.8393
0.750 0.2599 0.00613 0.00130 -0.0285 0.6026 0.9018
1.000 0.3044 0.00621 0.00134 -0.0319 0.5807 0.9464
1.250 0.3447 0.00635 0.00137 -0.0345 0.5585 0.9703
1.500 0.3811 0.00649 0.00140 -0.0364 0.5354 0.9844
2.000 0.4526 0.00682 0.00150 -0.0400 0.4851 1.0000
2.250 0.4775 0.00700 0.00156 -0.0394 0.4606 1.0000
2.500 0.5024 0.00720 0.00165 -0.0389 0.4353 1.0000
2.750 0.5273 0.00741 0.00174 -0.0384 0.4094 1.0000
3.000 0.5521 0.00763 0.00186 -0.0378 0.3841 1.0000
3.250 0.5769 0.00787 0.00199 -0.0373 0.3602 1.0000
3.500 0.6016 0.00812 0.00213 -0.0367 0.3352 1.0000
3.750 0.6265 0.00836 0.00229 -0.0362 0.3136 1.0000
4.250 0.6758 0.00887 0.00264 -0.0351 0.2730 1.0000
4.500 0.7005 0.00913 0.00282 -0.0346 0.2550 1.0000
4.750 0.7252 0.00939 0.00304 -0.0341 0.2384 1.0000
5.000 0.7498 0.00966 0.00325 -0.0336 0.2225 1.0000
5.500 0.7991 0.01021 0.00370 -0.0325 0.1933 1.0000
5.750 0.8237 0.01050 0.00395 -0.0320 0.1795 1.0000
6.000 0.8484 0.01077 0.00422 -0.0315 0.1677 1.0000
6.250 0.8728 0.01108 0.00449 -0.0310 0.1547 1.0000
6.500 0.8970 0.01140 0.00478 -0.0305 0.1420 1.0000
6.750 0.9214 0.01171 0.00509 -0.0300 0.1317 1.0000
7.000 0.9453 0.01207 0.00542 -0.0294 0.1199 1.0000
7.250 0.9689 0.01245 0.00579 -0.0288 0.1085 1.0000
7.500 0.9923 0.01285 0.00617 -0.0282 0.0976 1.0000
7.750 1.0152 0.01330 0.00657 -0.0276 0.0845 1.0000
8.000 1.0374 0.01380 0.00701 -0.0269 0.0698 1.0000
8.250 1.0594 0.01432 0.00748 -0.0262 0.0579 1.0000
8.500 1.0812 0.01485 0.00798 -0.0254 0.0483 1.0000
8.750 1.1025 0.01541 0.00853 -0.0246 0.0394 1.0000
9.000 1.1238 0.01595 0.00907 -0.0238 0.0323 1.0000
9.250 1.1443 0.01655 0.00967 -0.0229 0.0253 1.0000
9.500 1.1630 0.01730 0.01038 -0.0218 0.0171 1.0000
9.750 1.1806 0.01813 0.01119 -0.0205 0.0109 1.0000
10.000 1.1976 0.01898 0.01206 -0.0192 0.0071 1.0000
10.250 1.2154 0.01969 0.01285 -0.0179 0.0059 1.0000
10.500 1.2315 0.02050 0.01375 -0.0165 0.0051 1.0000
10.750 1.2460 0.02140 0.01474 -0.0149 0.0046 1.0000
11.000 1.2606 0.02220 0.01564 -0.0133 0.0043 1.0000
11.250 1.2716 0.02303 0.01657 -0.0111 0.0041 1.0000
11.500 1.2801 0.02398 0.01763 -0.0087 0.0039 1.0000
11.750 1.2880 0.02500 0.01876 -0.0065 0.0037 1.0000
12.000 1.2945 0.02619 0.02007 -0.0044 0.0036 1.0000
12.250 1.3004 0.02749 0.02147 -0.0025 0.0034 1.0000
12.500 1.3047 0.02898 0.02308 -0.0008 0.0033 1.0000
12.750 1.3087 0.03058 0.02480 0.0007 0.0032 1.0000
13.000 1.3098 0.03252 0.02686 0.0020 0.0031 1.0000
13.250 1.3063 0.03502 0.02952 0.0032 0.0030 1.0000
13.500 1.3055 0.03742 0.03205 0.0039 0.0030 1.0000
13.750 1.2975 0.04076 0.03555 0.0041 0.0029 1.0000
14.000 1.2909 0.04420 0.03914 0.0039 0.0028 1.0000
14.250 1.2744 0.04919 0.04429 0.0028 0.0027 1.0000
14.500 1.2694 0.05304 0.04828 0.0016 0.0028 1.0000
14.750 1.2591 0.05788 0.05327 -0.0003 0.0027 1.0000
15.000 1.2496 0.06285 0.05837 -0.0025 0.0027 1.0000
15.250 1.2382 0.06844 0.06411 -0.0051 0.0027 1.0000
15.500 1.2248 0.07463 0.07046 -0.0082 0.0027 1.0000
15.750 1.2106 0.08122 0.07719 -0.0115 0.0027 1.0000
16.000 1.1922 0.08879 0.08491 -0.0154 0.0027 1.0000
16.250 1.1752 0.09626 0.09250 -0.0193 0.0027 1.0000
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Polar data table (+)
Polar graphs
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