S4061-096-84 (s4061-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4061-096-84 (s4061-il) Reynolds number: 200,000 Max Cl/Cd: 81.21 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4061-il-200000-n5.txt Download as CSV file: xf-s4061-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4061-096-84
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3427 0.09016 0.08673 -0.0368 1.0000 0.0150
-8.750 -0.3365 0.08774 0.08434 -0.0376 1.0000 0.0147
-8.500 -0.3355 0.08419 0.08086 -0.0391 1.0000 0.0146
-8.250 -0.3317 0.08065 0.07737 -0.0414 0.9916 0.0143
-8.000 -0.3184 0.07534 0.07206 -0.0480 0.9683 0.0141
-7.750 -0.3083 0.06942 0.06614 -0.0553 0.9489 0.0140
-7.500 -0.3000 0.06374 0.06043 -0.0625 0.9315 0.0136
-7.250 -0.2951 0.05639 0.05302 -0.0712 0.9150 0.0133
-7.000 -0.3051 0.03819 0.03427 -0.0859 0.8971 0.0124
-6.750 -0.2976 0.03018 0.02538 -0.0893 0.8868 0.0124
-6.500 -0.2777 0.02757 0.02236 -0.0899 0.8782 0.0130
-6.250 -0.2568 0.02498 0.01926 -0.0900 0.8714 0.0138
-6.000 -0.2338 0.02262 0.01638 -0.0900 0.8637 0.0143
-5.750 -0.2099 0.02073 0.01405 -0.0896 0.8573 0.0146
-5.500 -0.1847 0.01926 0.01225 -0.0893 0.8504 0.0148
-5.250 -0.1592 0.01809 0.01080 -0.0888 0.8438 0.0151
-5.000 -0.1340 0.01696 0.00955 -0.0885 0.8377 0.0157
-4.750 -0.1080 0.01615 0.00864 -0.0883 0.8307 0.0164
-4.250 -0.0549 0.01485 0.00706 -0.0877 0.8180 0.0188
-4.000 -0.0283 0.01431 0.00644 -0.0875 0.8120 0.0213
-3.750 -0.0010 0.01384 0.00586 -0.0873 0.8055 0.0244
-3.500 0.0262 0.01330 0.00526 -0.0871 0.7989 0.0302
-3.250 0.0533 0.01279 0.00476 -0.0869 0.7931 0.0477
-3.000 0.0806 0.01243 0.00447 -0.0868 0.7860 0.0748
-2.750 0.1076 0.01210 0.00425 -0.0867 0.7803 0.1117
-2.500 0.1351 0.01185 0.00406 -0.0866 0.7730 0.1444
-2.250 0.1624 0.01162 0.00385 -0.0865 0.7668 0.1724
-2.000 0.1899 0.01142 0.00369 -0.0864 0.7599 0.2043
-1.750 0.2173 0.01121 0.00354 -0.0863 0.7532 0.2427
-1.500 0.2446 0.01100 0.00343 -0.0862 0.7467 0.2890
-1.250 0.2719 0.01078 0.00334 -0.0861 0.7395 0.3439
-1.000 0.2988 0.01056 0.00325 -0.0859 0.7332 0.4079
-0.750 0.3254 0.01030 0.00323 -0.0856 0.7257 0.4855
-0.500 0.3510 0.01001 0.00318 -0.0850 0.7195 0.5826
-0.250 0.3745 0.00964 0.00321 -0.0838 0.7117 0.7069
0.250 0.4383 0.00915 0.00304 -0.0844 0.6973 1.0000
0.500 0.4658 0.00922 0.00299 -0.0842 0.6904 1.0000
0.750 0.4934 0.00930 0.00300 -0.0841 0.6820 1.0000
1.250 0.5485 0.00948 0.00301 -0.0838 0.6660 1.0000
1.500 0.5759 0.00957 0.00302 -0.0837 0.6580 1.0000
1.750 0.6033 0.00967 0.00306 -0.0835 0.6486 1.0000
2.000 0.6306 0.00977 0.00311 -0.0833 0.6388 1.0000
2.250 0.6577 0.00988 0.00315 -0.0831 0.6286 1.0000
2.500 0.6848 0.00999 0.00321 -0.0829 0.6174 1.0000
2.750 0.7119 0.01011 0.00330 -0.0827 0.6061 1.0000
3.000 0.7389 0.01024 0.00339 -0.0825 0.5949 1.0000
3.250 0.7658 0.01038 0.00350 -0.0822 0.5833 1.0000
3.750 0.8191 0.01069 0.00375 -0.0817 0.5577 1.0000
4.000 0.8456 0.01086 0.00391 -0.0815 0.5441 1.0000
4.250 0.8720 0.01105 0.00408 -0.0812 0.5297 1.0000
4.500 0.8980 0.01125 0.00426 -0.0808 0.5144 1.0000
4.750 0.9238 0.01148 0.00447 -0.0805 0.4979 1.0000
5.000 0.9493 0.01173 0.00469 -0.0801 0.4798 1.0000
5.250 0.9745 0.01200 0.00494 -0.0796 0.4599 1.0000
5.500 0.9990 0.01232 0.00520 -0.0791 0.4387 1.0000
5.750 1.0233 0.01266 0.00552 -0.0786 0.4154 1.0000
6.000 1.0468 0.01306 0.00585 -0.0780 0.3907 1.0000
6.250 1.0696 0.01352 0.00623 -0.0773 0.3636 1.0000
6.500 1.0916 0.01404 0.00667 -0.0765 0.3348 1.0000
6.750 1.1129 0.01461 0.00715 -0.0757 0.3051 1.0000
7.000 1.1332 0.01526 0.00768 -0.0747 0.2747 1.0000
7.250 1.1530 0.01594 0.00826 -0.0737 0.2470 1.0000
7.500 1.1729 0.01661 0.00888 -0.0728 0.2228 1.0000
7.750 1.1924 0.01728 0.00950 -0.0718 0.2021 1.0000
8.000 1.2112 0.01799 0.01016 -0.0707 0.1809 1.0000
8.250 1.2289 0.01876 0.01087 -0.0695 0.1602 1.0000
8.500 1.2452 0.01960 0.01162 -0.0682 0.1374 1.0000
8.750 1.2603 0.02050 0.01244 -0.0667 0.1145 1.0000
9.000 1.2739 0.02147 0.01331 -0.0651 0.0949 1.0000
9.250 1.2868 0.02239 0.01418 -0.0633 0.0788 1.0000
9.500 1.2979 0.02331 0.01510 -0.0613 0.0674 1.0000
9.750 1.3081 0.02432 0.01611 -0.0592 0.0574 1.0000
10.000 1.3175 0.02543 0.01724 -0.0573 0.0483 1.0000
10.250 1.3257 0.02667 0.01849 -0.0553 0.0405 1.0000
10.500 1.3329 0.02804 0.01988 -0.0535 0.0330 1.0000
10.750 1.3401 0.02948 0.02138 -0.0517 0.0275 1.0000
11.000 1.3457 0.03110 0.02306 -0.0500 0.0238 1.0000
11.250 1.3515 0.03275 0.02479 -0.0485 0.0210 1.0000
11.500 1.3551 0.03466 0.02677 -0.0471 0.0195 1.0000
11.750 1.3600 0.03652 0.02877 -0.0458 0.0183 1.0000
12.000 1.3637 0.03856 0.03097 -0.0447 0.0174 1.0000
12.250 1.3662 0.04078 0.03331 -0.0437 0.0166 1.0000
12.500 1.3679 0.04318 0.03582 -0.0429 0.0160 1.0000
12.750 1.3668 0.04595 0.03870 -0.0423 0.0155 1.0000
13.000 1.3641 0.04899 0.04186 -0.0418 0.0152 1.0000
13.250 1.3637 0.05190 0.04492 -0.0415 0.0148 1.0000
13.500 1.3628 0.05497 0.04815 -0.0414 0.0145 1.0000
13.750 1.3612 0.05819 0.05152 -0.0415 0.0141 1.0000
14.000 1.3595 0.06156 0.05504 -0.0418 0.0137 1.0000
14.250 1.3573 0.06513 0.05875 -0.0422 0.0134 1.0000
14.500 1.3546 0.06890 0.06268 -0.0430 0.0130 1.0000
14.750 1.3514 0.07285 0.06675 -0.0439 0.0126 1.0000
15.000 1.3472 0.07706 0.07110 -0.0450 0.0125 1.0000
15.250 1.3425 0.08152 0.07568 -0.0464 0.0122 1.0000
15.500 1.3375 0.08609 0.08039 -0.0479 0.0120 1.0000
15.750 1.3322 0.09082 0.08524 -0.0495 0.0119 1.0000
16.000 1.3263 0.09571 0.09025 -0.0512 0.0117 1.0000
16.250 1.3205 0.10070 0.09536 -0.0531 0.0116 1.0000
16.500 1.3150 0.10584 0.10066 -0.0552 0.0115 1.0000
16.750 1.3088 0.11125 0.10624 -0.0576 0.0114 1.0000
17.000 1.3022 0.11688 0.11205 -0.0603 0.0113 1.0000
17.250 1.2947 0.12282 0.11817 -0.0634 0.0112 1.0000
17.500 1.2866 0.12899 0.12452 -0.0666 0.0112 1.0000
17.750 1.2776 0.13560 0.13130 -0.0704 0.0111 1.0000
18.000 1.2679 0.14252 0.13840 -0.0745 0.0111 1.0000
18.250 1.2572 0.14993 0.14599 -0.0790 0.0110 1.0000
18.500 1.2457 0.15779 0.15401 -0.0840 0.0110 1.0000
18.750 1.2327 0.16632 0.16272 -0.0895 0.0110 1.0000
19.000 1.2182 0.17569 0.17224 -0.0957 0.0111 1.0000
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Polar data table (+)
Polar graphs
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