S3016-095-87 (s3016-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S3016-095-87 (s3016-il) Reynolds number: 500,000 Max Cl/Cd: 85.52 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3016-il-500000.txt Download as CSV file: xf-s3016-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4229 0.08008 0.07811 -0.0191 1.0000 0.0191
-9.250 -0.4242 0.07583 0.07387 -0.0203 1.0000 0.0196
-9.000 -0.4281 0.07060 0.06867 -0.0226 1.0000 0.0197
-8.750 -0.4293 0.06645 0.06454 -0.0243 1.0000 0.0201
-8.500 -0.4345 0.06145 0.05956 -0.0268 1.0000 0.0204
-8.250 -0.4951 0.04360 0.04156 -0.0431 1.0000 0.0192
-8.000 -0.5081 0.03793 0.03574 -0.0452 1.0000 0.0194
-7.750 -0.5091 0.03377 0.03149 -0.0459 1.0000 0.0197
-7.500 -0.4938 0.03042 0.02804 -0.0479 0.9906 0.0203
-7.250 -0.4747 0.02635 0.02379 -0.0508 0.9805 0.0211
-7.000 -0.4581 0.02204 0.01919 -0.0525 0.9696 0.0222
-6.750 -0.4458 0.01869 0.01552 -0.0518 0.9569 0.0236
-6.500 -0.4565 0.02348 0.01903 -0.0511 0.9640 0.0169
-6.250 -0.4371 0.01956 0.01453 -0.0497 0.9540 0.0157
-6.000 -0.4159 0.01780 0.01247 -0.0483 0.9445 0.0160
-5.750 -0.3937 0.01648 0.01094 -0.0470 0.9357 0.0166
-5.500 -0.3713 0.01549 0.00977 -0.0457 0.9281 0.0174
-5.250 -0.3474 0.01469 0.00882 -0.0447 0.9198 0.0182
-5.000 -0.3251 0.01354 0.00750 -0.0434 0.9128 0.0194
-4.750 -0.3021 0.01261 0.00654 -0.0425 0.9049 0.0215
-4.500 -0.2781 0.01203 0.00588 -0.0415 0.8983 0.0230
-4.250 -0.2532 0.01150 0.00527 -0.0408 0.8908 0.0246
-4.000 -0.2282 0.01110 0.00477 -0.0400 0.8844 0.0262
-3.750 -0.2036 0.01041 0.00402 -0.0392 0.8768 0.0297
-3.500 -0.1779 0.01009 0.00361 -0.0386 0.8706 0.0327
-3.250 -0.1515 0.00974 0.00322 -0.0381 0.8630 0.0382
-3.000 -0.1267 0.00918 0.00282 -0.0374 0.8567 0.0836
-2.750 -0.1017 0.00859 0.00259 -0.0370 0.8488 0.1730
-2.500 -0.0763 0.00824 0.00242 -0.0365 0.8422 0.2385
-2.250 -0.0506 0.00785 0.00229 -0.0361 0.8340 0.3150
-2.000 -0.0253 0.00750 0.00216 -0.0356 0.8269 0.3934
-1.750 0.0004 0.00718 0.00206 -0.0352 0.8183 0.4653
-1.500 0.0251 0.00684 0.00199 -0.0344 0.8104 0.5559
-1.250 0.0481 0.00641 0.00194 -0.0333 0.8014 0.6689
-1.000 0.0708 0.00606 0.00190 -0.0318 0.7913 0.7682
-0.750 0.0945 0.00580 0.00187 -0.0304 0.7816 0.8520
-0.500 0.1275 0.00569 0.00185 -0.0309 0.7717 0.9172
-0.250 0.1742 0.00570 0.00183 -0.0346 0.7609 0.9565
0.000 0.2176 0.00574 0.00179 -0.0377 0.7497 0.9759
0.250 0.2591 0.00578 0.00174 -0.0404 0.7376 0.9887
0.500 0.3022 0.00580 0.00167 -0.0437 0.7240 0.9976
0.750 0.3338 0.00582 0.00161 -0.0445 0.7096 1.0000
1.000 0.3587 0.00585 0.00158 -0.0438 0.6946 1.0000
1.250 0.3837 0.00591 0.00155 -0.0432 0.6784 1.0000
1.500 0.4087 0.00598 0.00154 -0.0425 0.6607 1.0000
1.750 0.4338 0.00607 0.00154 -0.0419 0.6425 1.0000
2.000 0.4590 0.00618 0.00157 -0.0413 0.6228 1.0000
2.250 0.4842 0.00630 0.00161 -0.0407 0.6019 1.0000
2.500 0.5094 0.00644 0.00166 -0.0401 0.5795 1.0000
3.000 0.5595 0.00678 0.00181 -0.0389 0.5311 1.0000
3.250 0.5845 0.00698 0.00191 -0.0384 0.5052 1.0000
3.500 0.6093 0.00720 0.00202 -0.0378 0.4781 1.0000
3.750 0.6340 0.00744 0.00216 -0.0372 0.4495 1.0000
4.000 0.6585 0.00770 0.00232 -0.0366 0.4201 1.0000
4.250 0.6829 0.00799 0.00248 -0.0360 0.3907 1.0000
4.500 0.7071 0.00830 0.00267 -0.0354 0.3609 1.0000
4.750 0.7313 0.00862 0.00289 -0.0348 0.3329 1.0000
5.000 0.7555 0.00894 0.00311 -0.0342 0.3073 1.0000
5.250 0.7796 0.00928 0.00335 -0.0336 0.2841 1.0000
5.500 0.8039 0.00959 0.00360 -0.0330 0.2631 1.0000
5.750 0.8282 0.00992 0.00387 -0.0325 0.2445 1.0000
6.250 0.8766 0.01058 0.00443 -0.0314 0.2103 1.0000
6.500 0.9008 0.01091 0.00473 -0.0308 0.1951 1.0000
6.750 0.9248 0.01126 0.00505 -0.0303 0.1794 1.0000
7.000 0.9487 0.01162 0.00539 -0.0297 0.1646 1.0000
7.250 0.9723 0.01200 0.00574 -0.0291 0.1501 1.0000
7.500 0.9957 0.01241 0.00611 -0.0285 0.1355 1.0000
7.750 1.0188 0.01284 0.00650 -0.0278 0.1215 1.0000
8.000 1.0413 0.01332 0.00693 -0.0272 0.1062 1.0000
8.250 1.0634 0.01382 0.00738 -0.0264 0.0918 1.0000
8.500 1.0855 0.01433 0.00784 -0.0257 0.0792 1.0000
8.750 1.1074 0.01483 0.00833 -0.0250 0.0686 1.0000
9.000 1.1290 0.01535 0.00884 -0.0242 0.0589 1.0000
9.250 1.1499 0.01592 0.00943 -0.0233 0.0498 1.0000
9.500 1.1698 0.01656 0.01006 -0.0223 0.0402 1.0000
9.750 1.1869 0.01747 0.01087 -0.0210 0.0265 1.0000
10.000 1.2008 0.01866 0.01202 -0.0192 0.0161 1.0000
10.250 1.2135 0.01988 0.01329 -0.0173 0.0123 1.0000
10.500 1.2291 0.02073 0.01423 -0.0157 0.0109 1.0000
10.750 1.2416 0.02175 0.01534 -0.0138 0.0099 1.0000
11.000 1.2447 0.02318 0.01688 -0.0107 0.0091 1.0000
11.250 1.2483 0.02441 0.01824 -0.0077 0.0087 1.0000
11.500 1.2541 0.02560 0.01955 -0.0052 0.0084 1.0000
11.750 1.2581 0.02699 0.02106 -0.0030 0.0082 1.0000
12.000 1.2616 0.02851 0.02270 -0.0010 0.0078 1.0000
12.250 1.2638 0.03024 0.02455 0.0008 0.0076 1.0000
12.500 1.2662 0.03206 0.02647 0.0022 0.0073 1.0000
12.750 1.2657 0.03425 0.02878 0.0034 0.0072 1.0000
13.000 1.2647 0.03663 0.03129 0.0043 0.0070 1.0000
13.250 1.2621 0.03933 0.03410 0.0049 0.0068 1.0000
13.500 1.2577 0.04239 0.03727 0.0051 0.0067 1.0000
13.750 1.2528 0.04571 0.04073 0.0049 0.0067 1.0000
14.000 1.2453 0.04955 0.04470 0.0043 0.0065 1.0000
14.250 1.2372 0.05366 0.04895 0.0034 0.0065 1.0000
14.500 1.2309 0.05777 0.05320 0.0021 0.0065 1.0000
14.750 1.2164 0.06316 0.05874 0.0003 0.0063 1.0000
15.000 1.2113 0.06754 0.06326 -0.0015 0.0064 1.0000
15.250 1.1975 0.07337 0.06924 -0.0040 0.0063 1.0000
15.500 1.1897 0.07857 0.07458 -0.0065 0.0064 1.0000
15.750 1.1738 0.08524 0.08140 -0.0096 0.0063 1.0000
16.000 1.1644 0.09115 0.08745 -0.0128 0.0063 1.0000
16.250 1.1517 0.09781 0.09425 -0.0163 0.0063 1.0000
16.500 1.1401 0.10450 0.10107 -0.0200 0.0063 1.0000
16.750 1.1280 0.11150 0.10821 -0.0239 0.0064 1.0000
17.000 1.1164 0.11864 0.11548 -0.0279 0.0064 1.0000
17.250 1.1015 0.12659 0.12356 -0.0325 0.0064 1.0000
17.500 1.0898 0.13417 0.13126 -0.0369 0.0064 1.0000
17.750 1.0769 0.14228 0.13951 -0.0417 0.0065 1.0000
18.000 1.0594 0.15195 0.14934 -0.0474 0.0066 1.0000
18.250 1.0248 0.16723 0.16486 -0.0563 0.0070 1.0000
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Polar data table (+)
Polar graphs
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