S4310 (s4310-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4310 (s4310-il) Reynolds number: 100,000 Max Cl/Cd: 56.31 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4310-il-100000.txt Download as CSV file: xf-s4310-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2522 0.10407 0.10003 -0.0390 1.0000 0.0858
-9.000 -0.2748 0.10421 0.10029 -0.0363 1.0000 0.0859
-8.750 -0.2963 0.10416 0.10036 -0.0337 1.0000 0.0860
-8.500 -0.2678 0.09815 0.09434 -0.0286 1.0000 0.0889
-8.250 -0.2941 0.09640 0.09212 -0.0378 1.0000 0.0891
-8.000 -0.3037 0.09527 0.09108 -0.0343 1.0000 0.0905
-7.750 -0.3225 0.09487 0.09080 -0.0302 1.0000 0.0916
-7.500 -0.3434 0.09457 0.09061 -0.0262 1.0000 0.0923
-7.250 -0.3647 0.09418 0.09032 -0.0226 1.0000 0.0933
-7.000 -0.3774 0.09292 0.08914 -0.0217 0.9981 0.0946
-6.750 -0.3619 0.08608 0.08221 -0.0476 0.9824 0.1005
-6.500 -0.3398 0.08260 0.07881 -0.0398 0.9801 0.1035
-6.250 -0.3150 0.07841 0.07457 -0.0459 0.9725 0.1107
-6.000 -0.2974 0.07279 0.06887 -0.0563 0.9621 0.1168
-5.750 -0.2672 0.06909 0.06513 -0.0598 0.9572 0.1247
-5.500 -0.2511 0.06463 0.06058 -0.0654 0.9468 0.1325
-5.250 -0.2268 0.06050 0.05628 -0.0717 0.9388 0.1458
-5.000 -0.2024 0.05727 0.05297 -0.0743 0.9315 0.1611
-4.750 -0.1777 0.05425 0.04989 -0.0764 0.9248 0.1770
-4.500 -0.1528 0.05122 0.04678 -0.0786 0.9172 0.1930
-4.250 -0.1209 0.04821 0.04364 -0.0818 0.9117 0.2136
-4.000 -0.0725 0.03368 0.02629 -0.0891 0.9034 0.0724
-3.750 -0.0316 0.03023 0.02261 -0.0924 0.9000 0.0759
-3.500 -0.0084 0.02866 0.02067 -0.0915 0.8912 0.0766
-3.250 0.0319 0.02674 0.01836 -0.0932 0.8867 0.0785
-3.000 0.0611 0.02585 0.01720 -0.0931 0.8794 0.0843
-2.750 0.0946 0.02448 0.01576 -0.0938 0.8733 0.0900
-2.500 0.1361 0.02334 0.01452 -0.0955 0.8697 0.1004
-2.250 0.1538 0.02282 0.01412 -0.0938 0.8595 0.1159
-2.000 0.1886 0.02108 0.01302 -0.0945 0.8554 0.2133
-1.750 0.2015 0.01991 0.01315 -0.0922 0.8457 0.5054
-1.500 0.2825 0.01841 0.01261 -0.0994 0.8446 1.0000
-1.250 0.3114 0.01848 0.01237 -0.0994 0.8380 1.0000
-1.000 0.3325 0.01872 0.01238 -0.0982 0.8287 1.0000
-0.750 0.3556 0.01896 0.01241 -0.0973 0.8203 1.0000
-0.500 0.3834 0.01903 0.01227 -0.0970 0.8131 1.0000
-0.250 0.4045 0.01935 0.01243 -0.0958 0.8039 1.0000
0.000 0.4348 0.01931 0.01223 -0.0957 0.7976 1.0000
0.250 0.4551 0.01968 0.01247 -0.0944 0.7876 1.0000
0.500 0.4868 0.01955 0.01219 -0.0944 0.7820 1.0000
0.750 0.5069 0.01994 0.01250 -0.0931 0.7715 1.0000
1.000 0.5396 0.01972 0.01214 -0.0930 0.7664 1.0000
1.250 0.5598 0.02012 0.01247 -0.0918 0.7554 1.0000
1.500 0.5848 0.02026 0.01254 -0.0910 0.7467 1.0000
1.750 0.6136 0.02017 0.01237 -0.0905 0.7392 1.0000
2.000 0.6364 0.02045 0.01260 -0.0895 0.7290 1.0000
2.250 0.6682 0.02016 0.01221 -0.0892 0.7229 1.0000
2.500 0.6903 0.02046 0.01251 -0.0881 0.7117 1.0000
2.750 0.7161 0.02053 0.01254 -0.0874 0.7025 1.0000
3.000 0.7456 0.02035 0.01230 -0.0868 0.6945 1.0000
3.250 0.7690 0.02056 0.01251 -0.0859 0.6834 1.0000
3.500 0.7963 0.02052 0.01246 -0.0852 0.6742 1.0000
3.750 0.8252 0.02035 0.01225 -0.0847 0.6651 1.0000
4.000 0.8492 0.02050 0.01241 -0.0837 0.6533 1.0000
4.250 0.8750 0.02053 0.01243 -0.0829 0.6422 1.0000
4.500 0.9040 0.02033 0.01222 -0.0824 0.6322 1.0000
4.750 0.9315 0.02022 0.01209 -0.0817 0.6208 1.0000
5.000 0.9562 0.02027 0.01216 -0.0808 0.6076 1.0000
5.250 0.9815 0.02030 0.01223 -0.0799 0.5943 1.0000
5.500 1.0070 0.02030 0.01224 -0.0791 0.5806 1.0000
5.750 1.0326 0.02031 0.01225 -0.0783 0.5663 1.0000
6.000 1.0580 0.02032 0.01227 -0.0774 0.5514 1.0000
6.250 1.0832 0.02035 0.01231 -0.0765 0.5359 1.0000
6.500 1.1084 0.02040 0.01234 -0.0757 0.5198 1.0000
6.750 1.1331 0.02050 0.01242 -0.0748 0.5029 1.0000
7.000 1.1542 0.02079 0.01276 -0.0735 0.4837 1.0000
7.250 1.1767 0.02104 0.01302 -0.0724 0.4647 1.0000
7.500 1.1999 0.02131 0.01322 -0.0714 0.4461 1.0000
7.750 1.2194 0.02177 0.01371 -0.0700 0.4258 1.0000
8.000 1.2396 0.02223 0.01414 -0.0687 0.4057 1.0000
8.250 1.2600 0.02276 0.01461 -0.0675 0.3865 1.0000
8.500 1.2771 0.02342 0.01532 -0.0659 0.3662 1.0000
8.750 1.2953 0.02411 0.01596 -0.0645 0.3472 1.0000
9.000 1.3135 0.02487 0.01663 -0.0632 0.3290 1.0000
9.250 1.3285 0.02573 0.01754 -0.0614 0.3108 1.0000
9.500 1.3436 0.02663 0.01847 -0.0598 0.2935 1.0000
9.750 1.3586 0.02758 0.01941 -0.0581 0.2771 1.0000
10.000 1.3730 0.02858 0.02041 -0.0565 0.2617 1.0000
10.250 1.3863 0.02963 0.02147 -0.0547 0.2470 1.0000
10.500 1.3985 0.03074 0.02261 -0.0529 0.2331 1.0000
10.750 1.4098 0.03192 0.02383 -0.0509 0.2201 1.0000
11.000 1.4193 0.03312 0.02512 -0.0488 0.2080 1.0000
11.250 1.4286 0.03437 0.02638 -0.0467 0.1968 1.0000
11.500 1.4405 0.03567 0.02764 -0.0450 0.1858 1.0000
11.750 1.4449 0.03699 0.02909 -0.0426 0.1760 1.0000
12.000 1.4492 0.03855 0.03080 -0.0403 0.1668 1.0000
12.250 1.4599 0.04007 0.03230 -0.0388 0.1576 1.0000
12.500 1.4620 0.04167 0.03404 -0.0367 0.1495 1.0000
12.750 1.4654 0.04355 0.03605 -0.0348 0.1417 1.0000
13.000 1.4754 0.04504 0.03743 -0.0337 0.1326 1.0000
13.250 1.4640 0.04736 0.04014 -0.0312 0.1271 1.0000
13.500 1.4650 0.04904 0.04170 -0.0299 0.1189 1.0000
13.750 1.4514 0.05176 0.04476 -0.0283 0.1133 1.0000
14.000 1.4472 0.05390 0.04679 -0.0274 0.1059 1.0000
14.250 1.4324 0.05722 0.05043 -0.0268 0.1005 1.0000
14.500 1.4261 0.05987 0.05298 -0.0265 0.0937 1.0000
14.750 1.4125 0.06386 0.05732 -0.0266 0.0887 1.0000
15.000 1.4086 0.06683 0.06015 -0.0267 0.0820 1.0000
15.250 1.3919 0.07176 0.06547 -0.0277 0.0773 1.0000
15.500 1.3827 0.07576 0.06944 -0.0286 0.0714 1.0000
15.750 1.3662 0.08138 0.07532 -0.0303 0.0661 1.0000
16.000 1.3544 0.08628 0.08022 -0.0320 0.0605 1.0000
16.250 1.3379 0.09254 0.08669 -0.0342 0.0556 1.0000
16.500 1.3263 0.09808 0.09230 -0.0364 0.0511 1.0000
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Polar data table (+)
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