S3016-095-87 (s3016-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S3016-095-87 (s3016-il) Reynolds number: 200,000 Max Cl/Cd: 65.7 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3016-il-200000.txt Download as CSV file: xf-s3016-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3869 0.08490 0.08181 -0.0196 1.0000 0.0561
-8.750 -0.4033 0.07928 0.07625 -0.0257 1.0000 0.0579
-8.500 -0.4187 0.07338 0.07039 -0.0318 1.0000 0.0582
-8.250 -0.4705 0.08047 0.07727 -0.0247 1.0000 0.0557
-8.000 -0.4823 0.07506 0.07194 -0.0313 1.0000 0.0568
-7.750 -0.5021 0.06793 0.06455 -0.0419 1.0000 0.0582
-7.250 -0.4966 0.05798 0.05465 -0.0429 1.0000 0.0606
-7.000 -0.4880 0.05567 0.05237 -0.0418 1.0000 0.0622
-6.750 -0.4882 0.05327 0.04994 -0.0400 1.0000 0.0641
-6.500 -0.4956 0.05097 0.04756 -0.0372 1.0000 0.0663
-5.750 -0.4803 0.03064 0.02493 -0.0338 0.9932 0.0356
-5.250 -0.4136 0.02446 0.01782 -0.0370 0.9840 0.0355
-5.000 -0.3813 0.02178 0.01474 -0.0380 0.9790 0.0356
-4.750 -0.3472 0.01915 0.01185 -0.0392 0.9747 0.0368
-4.500 -0.3085 0.01777 0.01041 -0.0415 0.9713 0.0399
-4.250 -0.2741 0.01684 0.00938 -0.0427 0.9658 0.0438
-4.000 -0.2372 0.01567 0.00811 -0.0443 0.9611 0.0470
-3.750 -0.1978 0.01466 0.00714 -0.0468 0.9576 0.0555
-3.500 -0.1672 0.01384 0.00632 -0.0473 0.9504 0.0667
-3.250 -0.1357 0.01236 0.00555 -0.0484 0.9447 0.2023
-3.000 -0.1078 0.01176 0.00534 -0.0487 0.9370 0.3115
-2.750 -0.0782 0.01124 0.00518 -0.0491 0.9303 0.4148
-2.500 -0.0560 0.01074 0.00514 -0.0478 0.9214 0.5325
-2.250 -0.0322 0.01023 0.00511 -0.0463 0.9147 0.6610
-2.000 -0.0119 0.00990 0.00513 -0.0438 0.9051 0.7682
-1.750 0.0217 0.00967 0.00509 -0.0436 0.8998 0.8631
-1.500 0.0704 0.00963 0.00502 -0.0469 0.8929 0.9261
-1.250 0.1227 0.00959 0.00485 -0.0511 0.8875 0.9594
-1.000 0.1730 0.00957 0.00469 -0.0553 0.8798 0.9836
-0.750 0.2250 0.00939 0.00438 -0.0600 0.8723 1.0000
-0.500 0.2431 0.00935 0.00423 -0.0579 0.8592 1.0000
-0.250 0.2622 0.00931 0.00409 -0.0560 0.8463 1.0000
0.000 0.2825 0.00929 0.00397 -0.0543 0.8336 1.0000
0.250 0.3037 0.00927 0.00387 -0.0527 0.8213 1.0000
0.500 0.3256 0.00926 0.00377 -0.0512 0.8093 1.0000
0.750 0.3481 0.00924 0.00367 -0.0498 0.7972 1.0000
1.000 0.3710 0.00923 0.00358 -0.0485 0.7848 1.0000
1.250 0.3944 0.00923 0.00351 -0.0473 0.7709 1.0000
1.500 0.4182 0.00924 0.00346 -0.0462 0.7567 1.0000
1.750 0.4421 0.00925 0.00340 -0.0452 0.7420 1.0000
2.000 0.4664 0.00928 0.00339 -0.0442 0.7260 1.0000
2.250 0.4907 0.00931 0.00338 -0.0432 0.7084 1.0000
2.500 0.5151 0.00936 0.00337 -0.0422 0.6900 1.0000
2.750 0.5395 0.00943 0.00335 -0.0413 0.6711 1.0000
3.000 0.5639 0.00952 0.00341 -0.0404 0.6494 1.0000
3.250 0.5883 0.00965 0.00344 -0.0394 0.6274 1.0000
3.500 0.6126 0.00980 0.00352 -0.0385 0.6021 1.0000
3.750 0.6368 0.00999 0.00364 -0.0377 0.5757 1.0000
4.000 0.6608 0.01021 0.00376 -0.0368 0.5474 1.0000
4.250 0.6845 0.01047 0.00392 -0.0359 0.5175 1.0000
4.500 0.7080 0.01078 0.00411 -0.0350 0.4858 1.0000
4.750 0.7312 0.01113 0.00435 -0.0341 0.4531 1.0000
5.000 0.7542 0.01152 0.00462 -0.0332 0.4196 1.0000
5.250 0.7770 0.01195 0.00492 -0.0324 0.3877 1.0000
5.500 0.7996 0.01241 0.00526 -0.0315 0.3576 1.0000
5.750 0.8222 0.01288 0.00566 -0.0307 0.3301 1.0000
6.000 0.8447 0.01337 0.00606 -0.0299 0.3053 1.0000
6.250 0.8669 0.01391 0.00650 -0.0291 0.2833 1.0000
6.500 0.8896 0.01440 0.00696 -0.0283 0.2617 1.0000
6.750 0.9116 0.01495 0.00745 -0.0275 0.2426 1.0000
7.000 0.9336 0.01550 0.00799 -0.0267 0.2242 1.0000
7.250 0.9557 0.01603 0.00853 -0.0259 0.2063 1.0000
7.500 0.9773 0.01661 0.00910 -0.0250 0.1897 1.0000
7.750 0.9983 0.01722 0.00970 -0.0241 0.1737 1.0000
8.000 1.0187 0.01789 0.01036 -0.0231 0.1585 1.0000
8.250 1.0386 0.01859 0.01105 -0.0221 0.1440 1.0000
8.500 1.0579 0.01933 0.01179 -0.0210 0.1299 1.0000
8.750 1.0769 0.02008 0.01255 -0.0199 0.1167 1.0000
9.000 1.0954 0.02081 0.01332 -0.0188 0.1040 1.0000
9.250 1.1131 0.02155 0.01409 -0.0176 0.0911 1.0000
9.500 1.1301 0.02230 0.01490 -0.0164 0.0784 1.0000
9.750 1.1456 0.02319 0.01582 -0.0150 0.0661 1.0000
10.000 1.1577 0.02435 0.01700 -0.0132 0.0542 1.0000
10.250 1.1660 0.02578 0.01845 -0.0110 0.0424 1.0000
10.500 1.1706 0.02721 0.01992 -0.0082 0.0338 1.0000
10.750 1.1751 0.02874 0.02158 -0.0056 0.0290 1.0000
11.000 1.1765 0.03050 0.02339 -0.0031 0.0260 1.0000
11.250 1.1742 0.03298 0.02593 -0.0005 0.0243 1.0000
11.500 1.1793 0.03486 0.02801 0.0013 0.0227 1.0000
11.750 1.1835 0.03692 0.03022 0.0029 0.0216 1.0000
12.000 1.1863 0.03910 0.03253 0.0042 0.0204 1.0000
12.250 1.1885 0.04138 0.03494 0.0053 0.0196 1.0000
12.500 1.1874 0.04412 0.03775 0.0062 0.0185 1.0000
12.750 1.1840 0.04798 0.04180 0.0073 0.0179 1.0000
13.000 1.1810 0.05089 0.04492 0.0076 0.0175 1.0000
13.250 1.1762 0.05411 0.04838 0.0075 0.0170 1.0000
13.500 1.1695 0.05793 0.05243 0.0070 0.0168 1.0000
13.750 1.1604 0.06230 0.05703 0.0061 0.0167 1.0000
14.000 1.1489 0.06716 0.06211 0.0045 0.0166 1.0000
14.250 1.1355 0.07256 0.06773 0.0023 0.0165 1.0000
14.500 1.1205 0.07852 0.07390 -0.0005 0.0166 1.0000
14.750 1.1037 0.08518 0.08076 -0.0042 0.0166 1.0000
15.000 1.0859 0.09251 0.08828 -0.0084 0.0168 1.0000
15.250 1.0662 0.10069 0.09665 -0.0135 0.0168 1.0000
15.500 1.0462 0.10943 0.10555 -0.0189 0.0171 1.0000
15.750 1.0240 0.11927 0.11554 -0.0252 0.0173 1.0000
16.000 1.0003 0.12991 0.12630 -0.0317 0.0176 1.0000
16.250 0.9772 0.14104 0.13754 -0.0384 0.0179 1.0000
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Polar data table (+)
Polar graphs
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