S4310 (s4310-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4310 (s4310-il) Reynolds number: 500,000 Max Cl/Cd: 112.93 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4310-il-500000.txt Download as CSV file: xf-s4310-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S4310
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3079 0.11101 0.10876 -0.0364 1.0000 0.0160
-10.250 -0.3033 0.10748 0.10525 -0.0378 1.0000 0.0160
-10.000 -0.3036 0.10275 0.10055 -0.0387 1.0000 0.0163
-9.750 -0.2987 0.09967 0.09750 -0.0395 1.0000 0.0165
-9.500 -0.2915 0.09731 0.09516 -0.0394 1.0000 0.0168
-9.250 -0.2869 0.09448 0.09236 -0.0401 1.0000 0.0170
-9.000 -0.2837 0.09178 0.08970 -0.0407 1.0000 0.0173
-8.750 -0.2720 0.08809 0.08604 -0.0441 0.9875 0.0176
-8.500 -0.2526 0.08353 0.08146 -0.0502 0.9745 0.0181
-8.250 -0.2320 0.07853 0.07643 -0.0574 0.9608 0.0188
-8.000 -0.2152 0.07362 0.07149 -0.0640 0.9423 0.0193
-7.750 -0.2155 0.06923 0.06703 -0.0674 0.9162 0.0204
-7.500 -0.2224 0.06571 0.06345 -0.0691 0.8954 0.0206
-7.250 -0.2223 0.05918 0.05684 -0.0767 0.8776 0.0213
-7.000 -0.2173 0.05379 0.05131 -0.0807 0.8655 0.0213
-6.750 -0.2141 0.04717 0.04440 -0.0842 0.8546 0.0214
-6.500 -0.2205 0.03867 0.03555 -0.0868 0.8438 0.0220
-6.250 -0.2047 0.03665 0.03347 -0.0870 0.8356 0.0226
-6.000 -0.1872 0.03455 0.03121 -0.0872 0.8276 0.0233
-5.750 -0.1684 0.03213 0.02860 -0.0874 0.8197 0.0244
-5.500 -0.1568 0.02301 0.01848 -0.0867 0.8126 0.0191
-5.250 -0.1346 0.02005 0.01505 -0.0861 0.8055 0.0191
-5.000 -0.1101 0.01813 0.01274 -0.0855 0.7985 0.0198
-4.750 -0.0847 0.01627 0.01052 -0.0850 0.7919 0.0201
-4.500 -0.0581 0.01515 0.00915 -0.0845 0.7849 0.0208
-4.250 -0.0311 0.01437 0.00813 -0.0841 0.7786 0.0216
-4.000 -0.0058 0.01272 0.00637 -0.0837 0.7717 0.0232
-3.750 0.0213 0.01236 0.00594 -0.0836 0.7655 0.0255
-3.500 0.0487 0.01186 0.00538 -0.0833 0.7584 0.0272
-3.250 0.0761 0.01149 0.00488 -0.0830 0.7523 0.0283
-3.000 0.1024 0.01065 0.00400 -0.0828 0.7454 0.0309
-2.750 0.1298 0.01035 0.00365 -0.0826 0.7390 0.0336
-2.500 0.1575 0.01007 0.00331 -0.0825 0.7324 0.0357
-2.250 0.1852 0.00976 0.00293 -0.0823 0.7257 0.0390
-2.000 0.2130 0.00954 0.00268 -0.0822 0.7194 0.0455
-1.750 0.2404 0.00907 0.00241 -0.0821 0.7125 0.0997
-1.500 0.2672 0.00867 0.00229 -0.0820 0.7065 0.1984
-1.250 0.2944 0.00831 0.00222 -0.0821 0.6993 0.2927
-1.000 0.3209 0.00795 0.00217 -0.0820 0.6931 0.4136
-0.750 0.3467 0.00747 0.00217 -0.0817 0.6859 0.5652
-0.500 0.3699 0.00699 0.00218 -0.0807 0.6794 0.7333
-0.250 0.3886 0.00662 0.00227 -0.0779 0.6723 0.9023
0.000 0.4351 0.00656 0.00217 -0.0814 0.6649 0.9844
0.250 0.4778 0.00656 0.00209 -0.0846 0.6568 1.0000
0.500 0.5032 0.00664 0.00206 -0.0840 0.6497 1.0000
0.750 0.5291 0.00669 0.00206 -0.0836 0.6417 1.0000
1.250 0.5816 0.00683 0.00207 -0.0829 0.6263 1.0000
1.500 0.6080 0.00693 0.00209 -0.0825 0.6189 1.0000
1.750 0.6348 0.00699 0.00212 -0.0823 0.6103 1.0000
2.000 0.6615 0.00709 0.00215 -0.0820 0.6023 1.0000
2.250 0.6883 0.00718 0.00219 -0.0818 0.5933 1.0000
2.500 0.7153 0.00726 0.00225 -0.0816 0.5840 1.0000
2.750 0.7420 0.00738 0.00230 -0.0814 0.5748 1.0000
3.000 0.7688 0.00748 0.00236 -0.0812 0.5645 1.0000
3.250 0.7957 0.00758 0.00245 -0.0810 0.5542 1.0000
3.500 0.8223 0.00771 0.00253 -0.0808 0.5436 1.0000
3.750 0.8488 0.00786 0.00262 -0.0805 0.5323 1.0000
4.000 0.8754 0.00798 0.00272 -0.0803 0.5202 1.0000
4.250 0.9018 0.00813 0.00285 -0.0801 0.5075 1.0000
4.500 0.9280 0.00829 0.00298 -0.0798 0.4942 1.0000
4.750 0.9540 0.00848 0.00312 -0.0796 0.4799 1.0000
5.000 0.9797 0.00868 0.00329 -0.0792 0.4649 1.0000
5.250 1.0051 0.00890 0.00346 -0.0789 0.4490 1.0000
5.500 1.0301 0.00916 0.00366 -0.0785 0.4322 1.0000
5.750 1.0549 0.00942 0.00387 -0.0781 0.4144 1.0000
6.000 1.0794 0.00971 0.00411 -0.0776 0.3956 1.0000
6.250 1.1034 0.01003 0.00437 -0.0771 0.3764 1.0000
6.500 1.1268 0.01039 0.00465 -0.0765 0.3575 1.0000
6.750 1.1503 0.01074 0.00495 -0.0759 0.3381 1.0000
7.000 1.1731 0.01113 0.00528 -0.0753 0.3194 1.0000
7.250 1.1952 0.01156 0.00564 -0.0745 0.3011 1.0000
7.500 1.2176 0.01196 0.00600 -0.0738 0.2849 1.0000
7.750 1.2396 0.01238 0.00637 -0.0731 0.2688 1.0000
8.000 1.2609 0.01282 0.00678 -0.0722 0.2526 1.0000
8.250 1.2819 0.01327 0.00720 -0.0713 0.2380 1.0000
8.500 1.3021 0.01374 0.00763 -0.0703 0.2229 1.0000
8.750 1.3212 0.01426 0.00810 -0.0692 0.2067 1.0000
9.000 1.3396 0.01480 0.00859 -0.0679 0.1917 1.0000
9.250 1.3559 0.01542 0.00914 -0.0664 0.1750 1.0000
9.500 1.3717 0.01602 0.00969 -0.0648 0.1610 1.0000
9.750 1.3857 0.01658 0.01024 -0.0628 0.1492 1.0000
10.000 1.3987 0.01718 0.01083 -0.0608 0.1389 1.0000
10.250 1.4106 0.01785 0.01149 -0.0586 0.1295 1.0000
10.500 1.4213 0.01863 0.01224 -0.0565 0.1187 1.0000
10.750 1.4323 0.01943 0.01304 -0.0546 0.1085 1.0000
11.000 1.4436 0.02025 0.01387 -0.0528 0.0996 1.0000
11.250 1.4536 0.02119 0.01481 -0.0509 0.0918 1.0000
11.750 1.4709 0.02338 0.01697 -0.0474 0.0736 1.0000
12.000 1.4794 0.02456 0.01816 -0.0459 0.0662 1.0000
12.250 1.4856 0.02596 0.01955 -0.0442 0.0583 1.0000
12.500 1.4923 0.02739 0.02098 -0.0428 0.0508 1.0000
12.750 1.4949 0.02920 0.02277 -0.0413 0.0406 1.0000
13.000 1.4940 0.03138 0.02490 -0.0397 0.0295 1.0000
13.250 1.4876 0.03417 0.02763 -0.0381 0.0182 1.0000
13.500 1.4819 0.03706 0.03052 -0.0368 0.0119 1.0000
13.750 1.4790 0.03982 0.03334 -0.0359 0.0097 1.0000
14.000 1.4801 0.04226 0.03589 -0.0352 0.0089 1.0000
14.250 1.4785 0.04508 0.03881 -0.0348 0.0082 1.0000
14.500 1.4750 0.04825 0.04209 -0.0345 0.0076 1.0000
14.750 1.4708 0.05164 0.04561 -0.0344 0.0073 1.0000
15.000 1.4689 0.05489 0.04898 -0.0346 0.0071 1.0000
15.250 1.4653 0.05848 0.05269 -0.0350 0.0068 1.0000
15.500 1.4625 0.06209 0.05643 -0.0356 0.0066 1.0000
15.750 1.4559 0.06636 0.06083 -0.0365 0.0064 1.0000
16.000 1.4487 0.07089 0.06550 -0.0376 0.0063 1.0000
16.250 1.4416 0.07554 0.07027 -0.0390 0.0061 1.0000
16.500 1.4339 0.08042 0.07529 -0.0406 0.0059 1.0000
16.750 1.4241 0.08582 0.08082 -0.0425 0.0059 1.0000
17.000 1.4109 0.09197 0.08711 -0.0449 0.0057 1.0000
17.250 1.3996 0.09792 0.09319 -0.0473 0.0057 1.0000
17.500 1.3871 0.10427 0.09967 -0.0501 0.0056 1.0000
17.750 1.3750 0.11067 0.10620 -0.0530 0.0056 1.0000
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