S4062-095-87 (s4062-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: S4062-095-87 (s4062-il) Reynolds number: 500,000 Max Cl/Cd: 128.49 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4062-il-500000.txt Download as CSV file: xf-s4062-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S4062-095-87
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3110 0.10813 0.10588 -0.0414 1.0000 0.0172
-10.000 -0.3118 0.10442 0.10221 -0.0440 1.0000 0.0177
-9.750 -0.3081 0.10065 0.09848 -0.0465 0.9938 0.0178
-9.500 -0.2941 0.09559 0.09342 -0.0521 0.9865 0.0179
-9.250 -0.2851 0.08995 0.08779 -0.0564 0.9803 0.0183
-9.000 -0.2670 0.08675 0.08457 -0.0597 0.9747 0.0187
-8.750 -0.2477 0.08361 0.08141 -0.0634 0.9680 0.0195
-8.500 -0.2313 0.07960 0.07737 -0.0683 0.9591 0.0202
-8.250 -0.2221 0.07579 0.07354 -0.0719 0.9464 0.0212
-8.000 -0.2204 0.07228 0.06999 -0.0739 0.9326 0.0219
-7.750 -0.2288 0.06764 0.06534 -0.0772 0.9165 0.0233
-7.500 -0.2294 0.06348 0.06116 -0.0808 0.9052 0.0234
-7.250 -0.2264 0.05712 0.05474 -0.0877 0.8955 0.0235
-7.000 -0.2371 0.04567 0.04306 -0.0967 0.8860 0.0241
-6.750 -0.2230 0.04409 0.04147 -0.0973 0.8797 0.0247
-6.500 -0.2077 0.04174 0.03900 -0.0985 0.8743 0.0254
-6.250 -0.1920 0.03794 0.03502 -0.1006 0.8688 0.0263
-6.000 -0.1853 0.02371 0.01923 -0.1037 0.8617 0.0181
-5.750 -0.1659 0.01931 0.01442 -0.1037 0.8577 0.0163
-5.500 -0.1415 0.01632 0.01087 -0.1034 0.8531 0.0152
-5.250 -0.1154 0.01479 0.00907 -0.1031 0.8485 0.0151
-5.000 -0.0890 0.01375 0.00785 -0.1028 0.8446 0.0154
-4.750 -0.0622 0.01295 0.00691 -0.1026 0.8408 0.0161
-4.500 -0.0349 0.01226 0.00613 -0.1025 0.8362 0.0169
-4.250 -0.0075 0.01174 0.00550 -0.1023 0.8319 0.0178
-4.000 0.0192 0.01094 0.00461 -0.1021 0.8283 0.0195
-3.750 0.0471 0.01063 0.00427 -0.1021 0.8240 0.0226
-3.500 0.0749 0.01011 0.00371 -0.1021 0.8195 0.0280
-3.250 0.1026 0.00956 0.00322 -0.1020 0.8156 0.0543
-3.000 0.1304 0.00930 0.00302 -0.1020 0.8119 0.0824
-2.750 0.1584 0.00907 0.00289 -0.1021 0.8072 0.1096
-2.500 0.1863 0.00886 0.00275 -0.1022 0.8029 0.1421
-2.250 0.2142 0.00866 0.00263 -0.1022 0.7993 0.1799
-2.000 0.2422 0.00848 0.00255 -0.1023 0.7949 0.2187
-1.750 0.2702 0.00828 0.00246 -0.1024 0.7902 0.2651
-1.500 0.2980 0.00807 0.00238 -0.1025 0.7863 0.3199
-1.250 0.3257 0.00786 0.00234 -0.1025 0.7823 0.3870
-1.000 0.3533 0.00761 0.00233 -0.1026 0.7773 0.4667
-0.750 0.3803 0.00733 0.00231 -0.1025 0.7728 0.5669
-0.500 0.4062 0.00701 0.00232 -0.1020 0.7688 0.6862
-0.250 0.4280 0.00660 0.00238 -0.1004 0.7634 0.8338
0.000 0.4660 0.00631 0.00225 -0.1020 0.7584 1.0000
0.250 0.4938 0.00635 0.00220 -0.1019 0.7526 1.0000
0.500 0.5215 0.00636 0.00216 -0.1018 0.7453 1.0000
0.750 0.5492 0.00640 0.00211 -0.1017 0.7388 1.0000
1.000 0.5769 0.00642 0.00209 -0.1016 0.7311 1.0000
1.250 0.6048 0.00647 0.00207 -0.1015 0.7250 1.0000
1.500 0.6326 0.00651 0.00210 -0.1015 0.7177 1.0000
1.750 0.6604 0.00657 0.00209 -0.1014 0.7114 1.0000
2.000 0.6881 0.00661 0.00213 -0.1013 0.7036 1.0000
2.250 0.7158 0.00668 0.00215 -0.1012 0.6968 1.0000
2.500 0.7435 0.00673 0.00221 -0.1012 0.6884 1.0000
2.750 0.7710 0.00680 0.00224 -0.1011 0.6806 1.0000
3.000 0.7985 0.00686 0.00230 -0.1010 0.6712 1.0000
3.250 0.8259 0.00694 0.00238 -0.1009 0.6617 1.0000
3.500 0.8530 0.00703 0.00244 -0.1007 0.6514 1.0000
3.750 0.8800 0.00713 0.00251 -0.1005 0.6395 1.0000
4.000 0.9069 0.00723 0.00261 -0.1003 0.6261 1.0000
4.250 0.9335 0.00735 0.00272 -0.1001 0.6112 1.0000
4.500 0.9597 0.00750 0.00284 -0.0997 0.5939 1.0000
4.750 0.9855 0.00767 0.00298 -0.0994 0.5723 1.0000
5.000 1.0104 0.00791 0.00315 -0.0989 0.5464 1.0000
5.250 1.0339 0.00825 0.00336 -0.0981 0.5104 1.0000
5.500 1.0553 0.00875 0.00365 -0.0971 0.4617 1.0000
5.750 1.0746 0.00944 0.00405 -0.0958 0.4048 1.0000
6.000 1.0945 0.01009 0.00448 -0.0947 0.3580 1.0000
6.250 1.1152 0.01067 0.00490 -0.0937 0.3219 1.0000
6.500 1.1359 0.01123 0.00532 -0.0927 0.2906 1.0000
6.750 1.1562 0.01181 0.00576 -0.0916 0.2588 1.0000
7.000 1.1761 0.01240 0.00622 -0.0905 0.2300 1.0000
7.250 1.1957 0.01299 0.00668 -0.0894 0.2034 1.0000
7.500 1.2154 0.01354 0.00714 -0.0883 0.1798 1.0000
7.750 1.2342 0.01414 0.00763 -0.0870 0.1560 1.0000
8.250 1.2702 0.01536 0.00870 -0.0843 0.1170 1.0000
8.500 1.2869 0.01601 0.00927 -0.0828 0.0997 1.0000
8.750 1.3010 0.01670 0.00988 -0.0808 0.0841 1.0000
9.000 1.3137 0.01741 0.01054 -0.0786 0.0703 1.0000
9.250 1.3262 0.01816 0.01125 -0.0764 0.0574 1.0000
9.500 1.3378 0.01900 0.01205 -0.0742 0.0455 1.0000
9.750 1.3472 0.02004 0.01303 -0.0719 0.0335 1.0000
10.000 1.3561 0.02116 0.01414 -0.0695 0.0258 1.0000
10.250 1.3638 0.02241 0.01541 -0.0671 0.0220 1.0000
10.500 1.3756 0.02338 0.01646 -0.0653 0.0201 1.0000
10.750 1.3856 0.02451 0.01763 -0.0634 0.0185 1.0000
11.000 1.3893 0.02616 0.01936 -0.0609 0.0171 1.0000
11.250 1.3980 0.02745 0.02076 -0.0592 0.0164 1.0000
11.500 1.4068 0.02877 0.02219 -0.0575 0.0157 1.0000
11.750 1.4139 0.03027 0.02379 -0.0558 0.0151 1.0000
12.000 1.4206 0.03184 0.02544 -0.0542 0.0144 1.0000
12.250 1.4259 0.03358 0.02728 -0.0526 0.0140 1.0000
12.500 1.4296 0.03552 0.02929 -0.0511 0.0134 1.0000
12.750 1.4286 0.03799 0.03185 -0.0495 0.0129 1.0000
13.000 1.4217 0.04120 0.03521 -0.0477 0.0125 1.0000
13.250 1.4285 0.04305 0.03718 -0.0468 0.0122 1.0000
13.500 1.4330 0.04519 0.03944 -0.0459 0.0119 1.0000
13.750 1.4358 0.04759 0.04198 -0.0451 0.0115 1.0000
14.000 1.4368 0.05028 0.04479 -0.0444 0.0113 1.0000
14.250 1.4377 0.05306 0.04771 -0.0439 0.0110 1.0000
14.500 1.4376 0.05606 0.05083 -0.0436 0.0107 1.0000
14.750 1.4377 0.05912 0.05402 -0.0435 0.0104 1.0000
15.000 1.4361 0.06251 0.05752 -0.0436 0.0102 1.0000
15.250 1.4343 0.06600 0.06110 -0.0439 0.0099 1.0000
15.500 1.4305 0.06992 0.06514 -0.0445 0.0097 1.0000
15.750 1.4236 0.07442 0.06976 -0.0452 0.0094 1.0000
16.000 1.4113 0.07994 0.07546 -0.0461 0.0092 1.0000
16.250 1.3997 0.08560 0.08133 -0.0477 0.0090 1.0000
16.500 1.3925 0.09079 0.08669 -0.0496 0.0089 1.0000
16.750 1.3845 0.09630 0.09237 -0.0520 0.0088 1.0000
17.000 1.3760 0.10209 0.09833 -0.0548 0.0087 1.0000
17.250 1.3647 0.10858 0.10501 -0.0579 0.0086 1.0000
17.500 1.3532 0.11538 0.11197 -0.0615 0.0086 1.0000
17.750 1.3404 0.12263 0.11940 -0.0655 0.0085 1.0000
18.000 1.3274 0.13015 0.12709 -0.0699 0.0085 1.0000
18.250 1.3132 0.13817 0.13528 -0.0748 0.0085 1.0000
18.500 1.2983 0.14668 0.14395 -0.0802 0.0084 1.0000
18.750 1.2827 0.15558 0.15301 -0.0859 0.0085 1.0000
19.000 1.2662 0.16510 0.16269 -0.0922 0.0085 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S4062-095-87 (s4062-il)