S3014-095-85 (s3014-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S3014-095-85 (s3014-il) Reynolds number: 100,000 Max Cl/Cd: 51.89 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3014-il-100000.txt Download as CSV file: xf-s3014-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S3014-095-85
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3443 0.11135 0.10680 -0.0159 1.0000 0.0935
-10.000 -0.3554 0.10867 0.10417 -0.0193 1.0000 0.0963
-9.750 -0.3729 0.10624 0.10184 -0.0237 1.0000 0.0971
-9.500 -0.3432 0.09997 0.09552 -0.0204 1.0000 0.1003
-9.250 -0.3346 0.09642 0.09198 -0.0205 1.0000 0.1041
-9.000 -0.3371 0.09292 0.08852 -0.0224 1.0000 0.1085
-8.750 -0.3603 0.09010 0.08581 -0.0278 1.0000 0.1108
-8.500 -0.3455 0.08481 0.08053 -0.0265 1.0000 0.1133
-8.250 -0.3315 0.08130 0.07703 -0.0254 1.0000 0.1175
-8.000 -0.3393 0.07786 0.07366 -0.0278 1.0000 0.1231
-7.750 -0.4147 0.08363 0.07919 -0.0263 1.0000 0.1166
-7.500 -0.4178 0.08068 0.07632 -0.0278 1.0000 0.1209
-7.250 -0.4559 0.07745 0.07304 -0.0405 1.0000 0.1253
-7.000 -0.4288 0.07328 0.06906 -0.0335 1.0000 0.1284
-6.750 -0.4262 0.07101 0.06685 -0.0316 1.0000 0.1341
-6.500 -0.4665 0.06931 0.06492 -0.0359 1.0000 0.1397
-6.250 -0.4510 0.06567 0.06154 -0.0304 1.0000 0.1425
-6.000 -0.4511 0.06387 0.05978 -0.0275 1.0000 0.1487
-5.750 -0.4597 0.06086 0.05668 -0.0275 1.0000 0.1565
-5.500 -0.4630 0.05860 0.05426 -0.0276 1.0000 0.1691
-5.250 -0.4551 0.05620 0.05201 -0.0240 1.0000 0.1732
-5.000 -0.4519 0.05347 0.04916 -0.0236 1.0000 0.1855
-4.750 -0.4456 0.05101 0.04660 -0.0230 1.0000 0.1990
-4.500 -0.4107 0.03525 0.02887 -0.0287 1.0000 0.0795
-4.250 -0.3900 0.03133 0.02401 -0.0271 1.0000 0.0689
-4.000 -0.3704 0.02872 0.02109 -0.0261 1.0000 0.0670
-3.750 -0.3490 0.02663 0.01860 -0.0251 1.0000 0.0658
-3.500 -0.3086 0.02473 0.01620 -0.0273 0.9946 0.0671
-3.250 -0.2688 0.02360 0.01462 -0.0293 0.9882 0.0701
-3.000 -0.2280 0.02174 0.01275 -0.0318 0.9832 0.0731
-2.750 -0.1921 0.02074 0.01175 -0.0334 0.9758 0.0785
-2.500 -0.1509 0.01979 0.01082 -0.0359 0.9698 0.0912
-2.250 -0.1194 0.01842 0.00995 -0.0368 0.9616 0.1611
-2.000 -0.0873 0.01642 0.00991 -0.0380 0.9560 0.5736
-1.750 0.0093 0.01557 0.00981 -0.0495 0.9581 1.0000
-1.500 0.0480 0.01577 0.00970 -0.0520 0.9482 1.0000
-1.250 0.0942 0.01596 0.00960 -0.0559 0.9402 1.0000
-1.000 0.1377 0.01611 0.00953 -0.0592 0.9311 1.0000
-0.750 0.1773 0.01626 0.00951 -0.0617 0.9211 1.0000
-0.500 0.2322 0.01625 0.00932 -0.0669 0.9148 1.0000
-0.250 0.2653 0.01635 0.00931 -0.0679 0.9030 1.0000
0.000 0.2988 0.01643 0.00929 -0.0688 0.8914 1.0000
0.250 0.3328 0.01646 0.00923 -0.0696 0.8801 1.0000
0.500 0.3673 0.01641 0.00910 -0.0703 0.8693 1.0000
0.750 0.3980 0.01634 0.00897 -0.0700 0.8578 1.0000
1.000 0.4226 0.01636 0.00894 -0.0688 0.8444 1.0000
1.250 0.4466 0.01636 0.00889 -0.0673 0.8309 1.0000
1.500 0.4702 0.01634 0.00883 -0.0658 0.8174 1.0000
1.750 0.4936 0.01630 0.00876 -0.0642 0.8037 1.0000
2.000 0.5170 0.01624 0.00868 -0.0625 0.7899 1.0000
2.250 0.5405 0.01616 0.00858 -0.0608 0.7759 1.0000
2.500 0.5642 0.01606 0.00846 -0.0592 0.7615 1.0000
2.750 0.5880 0.01594 0.00834 -0.0575 0.7467 1.0000
3.000 0.6121 0.01580 0.00818 -0.0559 0.7313 1.0000
3.250 0.6365 0.01565 0.00800 -0.0543 0.7153 1.0000
3.500 0.6606 0.01554 0.00787 -0.0527 0.6976 1.0000
3.750 0.6842 0.01548 0.00784 -0.0512 0.6773 1.0000
4.000 0.7090 0.01536 0.00766 -0.0497 0.6576 1.0000
4.250 0.7325 0.01539 0.00767 -0.0483 0.6337 1.0000
4.500 0.7565 0.01542 0.00765 -0.0469 0.6091 1.0000
4.750 0.7802 0.01552 0.00770 -0.0455 0.5823 1.0000
5.000 0.8033 0.01572 0.00782 -0.0441 0.5534 1.0000
5.250 0.8260 0.01599 0.00802 -0.0428 0.5225 1.0000
5.500 0.8484 0.01635 0.00828 -0.0415 0.4910 1.0000
5.750 0.8704 0.01679 0.00859 -0.0402 0.4598 1.0000
6.000 0.8922 0.01732 0.00902 -0.0390 0.4297 1.0000
6.250 0.9137 0.01790 0.00950 -0.0378 0.4008 1.0000
6.500 0.9350 0.01855 0.01006 -0.0367 0.3733 1.0000
6.750 0.9561 0.01924 0.01068 -0.0356 0.3474 1.0000
7.000 0.9772 0.01999 0.01138 -0.0345 0.3237 1.0000
7.250 0.9980 0.02077 0.01209 -0.0334 0.3011 1.0000
7.500 1.0185 0.02161 0.01293 -0.0323 0.2795 1.0000
7.750 1.0389 0.02247 0.01375 -0.0312 0.2593 1.0000
8.000 1.0591 0.02341 0.01467 -0.0302 0.2404 1.0000
8.250 1.0782 0.02433 0.01569 -0.0290 0.2216 1.0000
8.500 1.0975 0.02532 0.01669 -0.0278 0.2045 1.0000
8.750 1.1164 0.02634 0.01769 -0.0266 0.1883 1.0000
9.000 1.1352 0.02748 0.01882 -0.0255 0.1731 1.0000
9.250 1.1520 0.02861 0.02002 -0.0241 0.1581 1.0000
9.500 1.1650 0.02955 0.02112 -0.0223 0.1425 1.0000
9.750 1.1724 0.03015 0.02189 -0.0200 0.1256 1.0000
10.000 1.1772 0.03083 0.02261 -0.0176 0.1092 1.0000
10.250 1.1809 0.03203 0.02382 -0.0151 0.0939 1.0000
10.500 1.1788 0.03372 0.02556 -0.0118 0.0775 1.0000
10.750 1.1765 0.03598 0.02786 -0.0087 0.0633 1.0000
11.000 1.1771 0.03854 0.03038 -0.0063 0.0540 1.0000
11.250 1.1808 0.04065 0.03261 -0.0044 0.0481 1.0000
11.500 1.1860 0.04340 0.03540 -0.0028 0.0438 1.0000
11.750 1.1902 0.04590 0.03819 -0.0012 0.0409 1.0000
12.000 1.1941 0.04857 0.04105 0.0001 0.0388 1.0000
12.250 1.1975 0.05146 0.04408 0.0013 0.0372 1.0000
12.500 1.2007 0.05486 0.04761 0.0022 0.0361 1.0000
12.750 1.1982 0.05934 0.05236 0.0030 0.0354 1.0000
13.000 1.1889 0.06369 0.05699 0.0035 0.0352 1.0000
13.250 1.1747 0.06804 0.06159 0.0035 0.0351 1.0000
13.500 1.1589 0.07279 0.06659 0.0028 0.0351 1.0000
13.750 1.1416 0.07809 0.07213 0.0013 0.0351 1.0000
14.000 1.1230 0.08373 0.07803 -0.0009 0.0352 1.0000
14.250 1.1022 0.08994 0.08447 -0.0042 0.0354 1.0000
14.500 1.0785 0.09707 0.09181 -0.0090 0.0359 1.0000
14.750 0.9821 0.12295 0.11821 -0.0288 0.0409 1.0000
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Polar data table (+)
Polar graphs
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