S4061-096-84 (s4061-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4061-096-84 (s4061-il) Reynolds number: 1,000,000 Max Cl/Cd: 139.27 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4061-il-1000000.txt Download as CSV file: xf-s4061-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3110 0.07990 0.07831 -0.0479 0.9558 0.0122
-8.500 -0.2613 0.06689 0.06511 -0.0419 0.8704 0.0130
-6.500 -0.3085 0.01771 0.01334 -0.0842 0.8242 0.0093
-6.250 -0.2821 0.01677 0.01223 -0.0842 0.8178 0.0092
-6.000 -0.2574 0.01482 0.00999 -0.0841 0.8119 0.0091
-5.750 -0.2308 0.01370 0.00866 -0.0840 0.8059 0.0092
-5.500 -0.2057 0.01182 0.00655 -0.0838 0.7997 0.0096
-5.250 -0.1787 0.01111 0.00574 -0.0837 0.7939 0.0101
-5.000 -0.1510 0.01061 0.00518 -0.0837 0.7877 0.0105
-4.750 -0.1234 0.01018 0.00465 -0.0837 0.7817 0.0110
-4.500 -0.0954 0.00975 0.00416 -0.0837 0.7756 0.0113
-4.250 -0.0674 0.00939 0.00372 -0.0836 0.7693 0.0117
-4.000 -0.0393 0.00908 0.00332 -0.0836 0.7634 0.0121
-3.750 -0.0111 0.00863 0.00281 -0.0836 0.7570 0.0130
-3.500 0.0170 0.00837 0.00248 -0.0836 0.7509 0.0143
-3.250 0.0455 0.00814 0.00220 -0.0836 0.7446 0.0157
-3.000 0.0739 0.00787 0.00189 -0.0836 0.7382 0.0201
-2.750 0.1020 0.00749 0.00165 -0.0836 0.7321 0.0533
-2.500 0.1304 0.00730 0.00152 -0.0837 0.7254 0.0766
-2.250 0.1586 0.00715 0.00142 -0.0838 0.7192 0.1010
-2.000 0.1870 0.00698 0.00133 -0.0839 0.7125 0.1297
-1.750 0.2152 0.00685 0.00126 -0.0839 0.7060 0.1608
-1.500 0.2437 0.00669 0.00120 -0.0840 0.6994 0.1968
-1.250 0.2719 0.00655 0.00115 -0.0841 0.6925 0.2408
-1.000 0.3004 0.00642 0.00111 -0.0842 0.6858 0.2799
-0.750 0.3286 0.00629 0.00108 -0.0843 0.6787 0.3297
-0.500 0.3568 0.00613 0.00107 -0.0844 0.6718 0.3906
-0.250 0.3848 0.00595 0.00107 -0.0845 0.6642 0.4641
0.000 0.4127 0.00577 0.00107 -0.0845 0.6567 0.5435
0.250 0.4400 0.00554 0.00110 -0.0845 0.6483 0.6475
0.500 0.4661 0.00526 0.00114 -0.0840 0.6394 0.7693
0.750 0.4876 0.00488 0.00118 -0.0822 0.6306 0.9460
1.000 0.5246 0.00489 0.00115 -0.0841 0.6209 1.0000
1.250 0.5528 0.00496 0.00117 -0.0841 0.6120 1.0000
1.750 0.6091 0.00512 0.00122 -0.0842 0.5925 1.0000
2.000 0.6372 0.00521 0.00126 -0.0842 0.5825 1.0000
2.250 0.6652 0.00532 0.00131 -0.0841 0.5721 1.0000
2.500 0.6933 0.00540 0.00137 -0.0842 0.5612 1.0000
2.750 0.7212 0.00551 0.00143 -0.0842 0.5501 1.0000
3.000 0.7491 0.00562 0.00149 -0.0842 0.5383 1.0000
3.250 0.7768 0.00575 0.00158 -0.0841 0.5256 1.0000
3.500 0.8044 0.00589 0.00167 -0.0841 0.5119 1.0000
3.750 0.8319 0.00604 0.00176 -0.0841 0.4975 1.0000
4.000 0.8593 0.00620 0.00187 -0.0840 0.4820 1.0000
4.250 0.8865 0.00637 0.00200 -0.0840 0.4652 1.0000
4.500 0.9136 0.00656 0.00213 -0.0839 0.4468 1.0000
4.750 0.9402 0.00680 0.00228 -0.0837 0.4269 1.0000
5.000 0.9668 0.00703 0.00246 -0.0836 0.4059 1.0000
5.250 0.9928 0.00733 0.00265 -0.0834 0.3811 1.0000
5.500 1.0182 0.00770 0.00288 -0.0831 0.3495 1.0000
5.750 1.0431 0.00811 0.00315 -0.0828 0.3153 1.0000
6.000 1.0679 0.00852 0.00343 -0.0825 0.2851 1.0000
6.250 1.0919 0.00901 0.00375 -0.0820 0.2523 1.0000
6.500 1.1159 0.00947 0.00408 -0.0816 0.2236 1.0000
6.750 1.1401 0.00990 0.00441 -0.0812 0.1993 1.0000
7.000 1.1638 0.01037 0.00475 -0.0807 0.1759 1.0000
7.250 1.1875 0.01082 0.00511 -0.0803 0.1549 1.0000
7.500 1.2106 0.01130 0.00550 -0.0797 0.1343 1.0000
7.750 1.2328 0.01187 0.00593 -0.0790 0.1119 1.0000
8.000 1.2553 0.01236 0.00634 -0.0784 0.0952 1.0000
8.250 1.2772 0.01290 0.00680 -0.0777 0.0789 1.0000
8.500 1.2981 0.01349 0.00730 -0.0768 0.0638 1.0000
8.750 1.3188 0.01408 0.00783 -0.0759 0.0506 1.0000
9.000 1.3385 0.01472 0.00840 -0.0749 0.0384 1.0000
9.250 1.3554 0.01555 0.00913 -0.0735 0.0236 1.0000
9.500 1.3712 0.01642 0.00993 -0.0719 0.0149 1.0000
9.750 1.3892 0.01705 0.01059 -0.0706 0.0129 1.0000
10.000 1.4048 0.01782 0.01139 -0.0689 0.0114 1.0000
10.250 1.4211 0.01840 0.01204 -0.0674 0.0109 1.0000
10.500 1.4338 0.01905 0.01274 -0.0652 0.0104 1.0000
10.750 1.4450 0.01977 0.01352 -0.0629 0.0101 1.0000
11.000 1.4552 0.02060 0.01441 -0.0607 0.0096 1.0000
11.250 1.4642 0.02156 0.01543 -0.0585 0.0093 1.0000
11.500 1.4701 0.02279 0.01676 -0.0561 0.0089 1.0000
11.750 1.4730 0.02430 0.01838 -0.0536 0.0086 1.0000
12.000 1.4780 0.02576 0.01993 -0.0516 0.0084 1.0000
12.250 1.4882 0.02687 0.02111 -0.0503 0.0083 1.0000
12.500 1.4958 0.02824 0.02257 -0.0488 0.0081 1.0000
12.750 1.5030 0.02971 0.02411 -0.0475 0.0078 1.0000
13.000 1.5076 0.03146 0.02595 -0.0461 0.0077 1.0000
13.250 1.5113 0.03336 0.02795 -0.0449 0.0076 1.0000
13.500 1.5158 0.03527 0.02995 -0.0439 0.0073 1.0000
13.750 1.5183 0.03744 0.03222 -0.0430 0.0072 1.0000
14.000 1.5188 0.03991 0.03478 -0.0422 0.0071 1.0000
14.250 1.5197 0.04242 0.03738 -0.0417 0.0069 1.0000
14.500 1.5177 0.04535 0.04040 -0.0413 0.0068 1.0000
14.750 1.5160 0.04839 0.04355 -0.0411 0.0068 1.0000
15.000 1.5112 0.05191 0.04718 -0.0412 0.0066 1.0000
15.250 1.5053 0.05577 0.05114 -0.0415 0.0065 1.0000
15.500 1.4976 0.06003 0.05551 -0.0422 0.0064 1.0000
15.750 1.4859 0.06503 0.06064 -0.0432 0.0063 1.0000
16.000 1.4743 0.07025 0.06599 -0.0445 0.0062 1.0000
16.250 1.4625 0.07563 0.07152 -0.0460 0.0062 1.0000
16.500 1.4544 0.08072 0.07673 -0.0477 0.0061 1.0000
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Polar data table (+)
Polar graphs
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