DU86-084/18 8.44% (du8608418-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: DU86-084/18 8.44% (du8608418-il) Reynolds number: 100,000 Max Cl/Cd: 46.95 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-du8608418-il-100000.txt Download as CSV file: xf-du8608418-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: DU86-084/18 8.44%
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 -0.4387 0.09374 0.08951 -0.0161 1.0000 0.1085
-9.000 -0.4557 0.08962 0.08547 -0.0208 1.0000 0.1123
-8.750 -0.4835 0.08505 0.08098 -0.0278 1.0000 0.1131
-8.500 -0.4441 0.08069 0.07658 -0.0209 1.0000 0.1198
-8.250 -0.4569 0.07630 0.07225 -0.0245 1.0000 0.1248
-8.000 -0.4902 0.07175 0.06777 -0.0308 1.0000 0.1262
-7.750 -0.4695 0.06712 0.06318 -0.0279 1.0000 0.1314
-7.500 -0.4791 0.06348 0.05957 -0.0285 1.0000 0.1355
-7.250 -0.5129 0.06033 0.05638 -0.0296 1.0000 0.1395
-6.500 -0.5763 0.06134 0.05700 -0.0233 1.0000 0.1478
-5.750 -0.5545 0.04170 0.03743 -0.0163 1.0000 0.1832
-5.500 -0.5686 0.04049 0.03399 -0.0165 1.0000 0.0715
-5.250 -0.5535 0.03559 0.02847 -0.0139 1.0000 0.0578
-5.000 -0.5374 0.03196 0.02445 -0.0121 1.0000 0.0540
-4.750 -0.5177 0.02870 0.02047 -0.0099 1.0000 0.0502
-4.500 -0.4956 0.02630 0.01757 -0.0082 1.0000 0.0493
-4.250 -0.4745 0.02470 0.01583 -0.0071 1.0000 0.0536
-4.000 -0.4512 0.02320 0.01402 -0.0058 1.0000 0.0577
-3.750 -0.4267 0.02157 0.01215 -0.0044 1.0000 0.0603
-3.500 -0.4043 0.01982 0.01050 -0.0032 1.0000 0.0686
-3.250 -0.3828 0.01869 0.00932 -0.0019 1.0000 0.0858
-3.000 -0.3629 0.01700 0.00804 -0.0005 1.0000 0.1371
-2.750 -0.3546 0.01370 0.00746 0.0032 1.0000 0.6006
-2.500 -0.1479 0.01510 0.00871 -0.0239 1.0000 1.0000
-2.250 -0.1403 0.01504 0.00847 -0.0211 1.0000 1.0000
-2.000 -0.1316 0.01501 0.00827 -0.0183 1.0000 1.0000
-1.750 -0.1221 0.01499 0.00811 -0.0156 1.0000 1.0000
-1.500 -0.1121 0.01499 0.00797 -0.0130 1.0000 1.0000
-1.250 -0.1016 0.01500 0.00784 -0.0105 1.0000 1.0000
-1.000 -0.0909 0.01503 0.00776 -0.0080 1.0000 1.0000
-0.750 -0.0799 0.01508 0.00770 -0.0055 1.0000 1.0000
-0.500 -0.0687 0.01513 0.00767 -0.0031 1.0000 1.0000
-0.250 -0.0574 0.01520 0.00767 -0.0008 1.0000 1.0000
0.000 -0.0458 0.01529 0.00769 0.0015 1.0000 1.0000
0.250 -0.0338 0.01540 0.00772 0.0037 1.0000 1.0000
0.500 -0.0216 0.01554 0.00781 0.0057 1.0000 1.0000
0.750 0.0194 0.01603 0.00825 0.0022 0.9937 1.0000
1.000 0.0676 0.01655 0.00875 -0.0027 0.9846 1.0000
1.250 0.1146 0.01702 0.00922 -0.0073 0.9743 1.0000
1.500 0.1649 0.01749 0.00972 -0.0123 0.9630 1.0000
1.750 0.2195 0.01790 0.01019 -0.0179 0.9506 1.0000
2.000 0.2793 0.01818 0.01059 -0.0242 0.9367 1.0000
2.250 0.3462 0.01828 0.01083 -0.0315 0.9220 1.0000
2.500 0.4236 0.01808 0.01088 -0.0404 0.9078 1.0000
2.750 0.4869 0.01769 0.01072 -0.0461 0.8914 1.0000
3.000 0.5358 0.01725 0.01047 -0.0483 0.8735 1.0000
3.250 0.5584 0.01710 0.01050 -0.0457 0.8510 1.0000
3.500 0.5800 0.01683 0.01036 -0.0426 0.8288 1.0000
3.750 0.5960 0.01650 0.01017 -0.0385 0.8033 1.0000
4.000 0.6087 0.01599 0.00982 -0.0342 0.7706 1.0000
4.250 0.6222 0.01523 0.00925 -0.0301 0.7259 1.0000
4.500 0.6413 0.01410 0.00809 -0.0256 0.6570 1.0000
4.750 0.6563 0.01398 0.00729 -0.0206 0.5250 1.0000
5.000 0.6658 0.01508 0.00762 -0.0168 0.3964 1.0000
5.250 0.6763 0.01635 0.00826 -0.0139 0.3014 1.0000
5.500 0.6885 0.01762 0.00909 -0.0113 0.2348 1.0000
5.750 0.7019 0.01885 0.00999 -0.0090 0.1876 1.0000
6.000 0.7176 0.02011 0.01108 -0.0069 0.1550 1.0000
6.250 0.7351 0.02144 0.01229 -0.0051 0.1319 1.0000
6.500 0.7536 0.02268 0.01353 -0.0035 0.1123 1.0000
6.750 0.7742 0.02436 0.01513 -0.0022 0.0968 1.0000
7.000 0.7940 0.02608 0.01693 -0.0009 0.0813 1.0000
7.250 0.8132 0.02784 0.01885 0.0005 0.0673 1.0000
7.500 0.8342 0.03018 0.02129 0.0017 0.0583 1.0000
7.750 0.8521 0.03247 0.02407 0.0034 0.0508 1.0000
8.000 0.8703 0.03523 0.02708 0.0047 0.0472 1.0000
8.250 0.8846 0.03954 0.03172 0.0061 0.0455 1.0000
8.500 0.8937 0.04424 0.03692 0.0079 0.0452 1.0000
8.750 0.8979 0.04831 0.04150 0.0100 0.0447 1.0000
9.000 0.8983 0.05170 0.04544 0.0123 0.0439 1.0000
9.250 0.8958 0.05585 0.04998 0.0141 0.0439 1.0000
9.500 0.8876 0.05993 0.05442 0.0159 0.0436 1.0000
9.750 0.8770 0.06434 0.05907 0.0172 0.0439 1.0000
10.000 0.8644 0.06863 0.06349 0.0184 0.0444 1.0000
10.250 0.8097 0.07676 0.07209 0.0168 0.0541 1.0000
10.500 0.7966 0.08214 0.07751 0.0149 0.0554 1.0000
10.750 0.7883 0.08782 0.08320 0.0128 0.0563 1.0000
|
Polar data table (+)
Polar graphs
<< Back to DU86-084/18 8.44% (du8608418-il)