S4320 (s4320-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4320 (s4320-il) Reynolds number: 100,000 Max Cl/Cd: 61.67 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4320-il-100000-n5.txt Download as CSV file: xf-s4320-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4320
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2091 0.09347 0.08919 -0.0357 1.0000 0.0505
-8.500 -0.2172 0.09142 0.08724 -0.0371 1.0000 0.0518
-8.250 -0.2260 0.08950 0.08543 -0.0381 0.9970 0.0523
-8.000 -0.2184 0.08517 0.08112 -0.0444 0.9834 0.0526
-7.750 -0.1989 0.07914 0.07510 -0.0436 0.9771 0.0546
-7.500 -0.1791 0.07506 0.07100 -0.0451 0.9687 0.0579
-7.250 -0.1664 0.07070 0.06665 -0.0490 0.9574 0.0599
-7.000 -0.1560 0.06635 0.06230 -0.0529 0.9445 0.0611
-6.750 -0.1477 0.06214 0.05807 -0.0565 0.9308 0.0613
-6.500 -0.1406 0.05779 0.05371 -0.0600 0.9174 0.0601
-6.250 -0.1843 0.06307 0.05867 -0.0749 0.9326 0.0422
-6.000 -0.1597 0.05517 0.05055 -0.0825 0.9204 0.0319
-5.750 -0.1382 0.05113 0.04640 -0.0860 0.9099 0.0312
-5.500 -0.1149 0.04616 0.04121 -0.0905 0.8990 0.0305
-5.250 -0.0918 0.04115 0.03587 -0.0943 0.8875 0.0299
-5.000 -0.0662 0.03608 0.03026 -0.0977 0.8773 0.0307
-4.750 -0.0380 0.03189 0.02531 -0.0999 0.8690 0.0319
-4.500 -0.0120 0.02888 0.02175 -0.1007 0.8591 0.0320
-4.250 0.0156 0.02642 0.01875 -0.1011 0.8511 0.0322
-4.000 0.0422 0.02425 0.01622 -0.1013 0.8425 0.0328
-3.750 0.0690 0.02282 0.01456 -0.1013 0.8342 0.0343
-3.500 0.0964 0.02183 0.01334 -0.1012 0.8263 0.0371
-3.250 0.1237 0.02067 0.01190 -0.1009 0.8179 0.0388
-3.000 0.1514 0.01961 0.01060 -0.1004 0.8107 0.0400
-2.750 0.1782 0.01880 0.00962 -0.1000 0.8022 0.0414
-2.500 0.2051 0.01794 0.00872 -0.0996 0.7954 0.0439
-2.250 0.2317 0.01747 0.00818 -0.0993 0.7866 0.0493
-2.000 0.2591 0.01691 0.00750 -0.0989 0.7800 0.0553
-1.750 0.2861 0.01647 0.00698 -0.0986 0.7712 0.0657
-1.500 0.3134 0.01582 0.00651 -0.0983 0.7645 0.1112
-1.250 0.3394 0.01519 0.00637 -0.0983 0.7559 0.2465
-1.000 0.3639 0.01428 0.00637 -0.0977 0.7491 0.5044
-0.750 0.3801 0.01343 0.00638 -0.0943 0.7410 0.7919
-0.500 0.4163 0.01317 0.00603 -0.0952 0.7338 1.0000
-0.250 0.4438 0.01329 0.00592 -0.0950 0.7253 1.0000
0.000 0.4713 0.01340 0.00582 -0.0948 0.7174 1.0000
0.250 0.4988 0.01352 0.00574 -0.0945 0.7094 1.0000
0.500 0.5260 0.01365 0.00572 -0.0943 0.7008 1.0000
0.750 0.5535 0.01376 0.00565 -0.0940 0.6931 1.0000
1.000 0.5804 0.01391 0.00569 -0.0938 0.6836 1.0000
1.250 0.6077 0.01403 0.00567 -0.0934 0.6755 1.0000
1.500 0.6346 0.01417 0.00572 -0.0931 0.6659 1.0000
1.750 0.6615 0.01432 0.00579 -0.0928 0.6564 1.0000
2.000 0.6887 0.01443 0.00578 -0.0925 0.6479 1.0000
2.250 0.7152 0.01459 0.00590 -0.0922 0.6373 1.0000
2.500 0.7419 0.01475 0.00601 -0.0918 0.6272 1.0000
2.750 0.7688 0.01488 0.00608 -0.0915 0.6177 1.0000
3.000 0.7952 0.01505 0.00621 -0.0911 0.6068 1.0000
3.250 0.8215 0.01522 0.00637 -0.0907 0.5955 1.0000
3.500 0.8478 0.01539 0.00651 -0.0903 0.5842 1.0000
3.750 0.8740 0.01556 0.00666 -0.0899 0.5727 1.0000
4.000 0.9001 0.01573 0.00680 -0.0895 0.5606 1.0000
4.250 0.9259 0.01593 0.00699 -0.0890 0.5473 1.0000
4.500 0.9514 0.01613 0.00720 -0.0885 0.5334 1.0000
4.750 0.9767 0.01635 0.00744 -0.0880 0.5190 1.0000
5.000 1.0019 0.01659 0.00768 -0.0875 0.5040 1.0000
5.250 1.0267 0.01685 0.00793 -0.0869 0.4883 1.0000
5.500 1.0511 0.01714 0.00823 -0.0863 0.4715 1.0000
5.750 1.0753 0.01746 0.00859 -0.0857 0.4542 1.0000
6.000 1.0990 0.01782 0.00894 -0.0850 0.4363 1.0000
6.250 1.1222 0.01821 0.00931 -0.0843 0.4182 1.0000
6.500 1.1450 0.01864 0.00973 -0.0835 0.3995 1.0000
6.750 1.1672 0.01912 0.01024 -0.0827 0.3804 1.0000
7.000 1.1888 0.01965 0.01075 -0.0818 0.3614 1.0000
7.250 1.2099 0.02022 0.01130 -0.0809 0.3432 1.0000
7.500 1.2305 0.02082 0.01192 -0.0799 0.3244 1.0000
7.750 1.2503 0.02148 0.01261 -0.0789 0.3068 1.0000
8.000 1.2693 0.02218 0.01331 -0.0778 0.2896 1.0000
8.250 1.2877 0.02292 0.01406 -0.0767 0.2736 1.0000
8.500 1.3052 0.02371 0.01486 -0.0754 0.2581 1.0000
8.750 1.3222 0.02452 0.01572 -0.0742 0.2431 1.0000
9.000 1.3381 0.02538 0.01665 -0.0728 0.2292 1.0000
9.500 1.3669 0.02723 0.01861 -0.0697 0.2033 1.0000
9.750 1.3796 0.02821 0.01968 -0.0681 0.1913 1.0000
10.000 1.3898 0.02924 0.02079 -0.0661 0.1805 1.0000
10.500 1.4054 0.03164 0.02333 -0.0620 0.1616 1.0000
10.750 1.4136 0.03292 0.02475 -0.0602 0.1522 1.0000
11.000 1.4194 0.03441 0.02630 -0.0584 0.1441 1.0000
11.250 1.4251 0.03598 0.02798 -0.0568 0.1361 1.0000
11.500 1.4307 0.03765 0.02977 -0.0554 0.1285 1.0000
11.750 1.4335 0.03956 0.03175 -0.0541 0.1216 1.0000
12.000 1.4382 0.04147 0.03383 -0.0530 0.1141 1.0000
12.250 1.4378 0.04381 0.03619 -0.0520 0.1076 1.0000
12.500 1.4396 0.04612 0.03873 -0.0513 0.0987 1.0000
12.750 1.4382 0.04882 0.04153 -0.0509 0.0902 1.0000
13.000 1.4335 0.05199 0.04472 -0.0508 0.0824 1.0000
13.250 1.4305 0.05520 0.04806 -0.0509 0.0729 1.0000
13.500 1.4268 0.05863 0.05161 -0.0512 0.0646 1.0000
13.750 1.4194 0.06266 0.05570 -0.0518 0.0592 1.0000
14.000 1.4149 0.06648 0.05972 -0.0524 0.0534 1.0000
14.250 1.4044 0.07131 0.06464 -0.0536 0.0494 1.0000
14.500 1.3969 0.07595 0.06948 -0.0548 0.0441 1.0000
14.750 1.3842 0.08162 0.07525 -0.0568 0.0405 1.0000
15.000 1.3721 0.08747 0.08126 -0.0589 0.0367 1.0000
15.250 1.3583 0.09384 0.08777 -0.0615 0.0337 1.0000
15.500 1.3424 0.10086 0.09490 -0.0647 0.0319 1.0000
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Polar data table (+)
Polar graphs
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