Comparison of Symmetric and KFm3 Airfoil

46 Pages·2012·1.13 MB·English

by  D Abhinav

CFD Analysis of KF Airfoil
D Abhinav
Ashfaq Ali Y
©2011 D Abhinav, Ashfaq Ali Y
Comparison of Symmetric and KFm3 Airfoil
α Cl Cd Cm 0.25 Cl/Cd
[°] [-] [-] [-] [-]
-18 -0.44 -0.89142 0.37374 0.24115 0.023 -0.04677 -1.17729 -3.69654
-15 -0.487 -0.81412 0.30681 0.1928 0.014 -0.0538 -1.5873 -4.22261
-12 -0.5 -0.70899 0.22341 0.14493 0.006 -0.05687 -2.23804 -4.89195
-9 -0.4 -0.57421 0.13885 0.10076 0.003 -0.05489 -2.88081 -5.69879
-6 -0.562 -0.4001 0.04647 0.06216 0.003 -0.04471 -12.0938 -6.43662
-3 -0.366 -0.22527 0.01418 0.03815 0.003 -0.03425 -25.811 -5.90485
0 0 0.052102 0.01175 0.1159 0 0.00661 0 0.449543
3 0.366 0.12185 0.01418 0.033154 -0.003 -0.01796 25.811 3.675273
6 0.562 0.27602 0.04647 0.048905 -0.003 -0.0148 12.09382 5.644004
9 0.4 0.44342 0.13885 0.080482 -0.003 -0.00562 2.880807 5.509555
12 0.5 0.56405 0.22341 0.11492 -0.006 -0.00746 2.238038 4.908197
15 0.487 0.51259 0.30681 0.10515 -0.014 -0.04963 1.587302 4.874845
18 0.44 0.60385 0.37374 0.14109 -0.023 -0.05313 1.177289 4.279892
NACA 0009
KFm3
Lift Coefficient vs Angle of Attack
Cl vs α
0.8
0.6
0.4
0.2
0
α-2 0 -15 -10 -5 0 5 10 15 20 NACA 0009
-0.2 KFm3
-0.4
-0.6
-0.8
-1
Cl
Drag Coefficient vs Angle of Attack
Cd vs α
0.4
0.35
0.3
0.25
0.2
NACA 0009
KFm3
0.15
0.1
α
0.05
0
-20 -15 -10 -5 0 5 10 15 20
Cd
Lift/Drag vs Angle of Attack
L/D vs α
30
20
10
α 0 NACA 0009
-20 -15 -10 -5 0 5 10 15 20
KFm3
-10
-20
-30
L/D
Moment Coefficient vs Angle of Attack
Cm vs α
0.03
0.02
0.01
0
-20 -15 -10 -5 0 5 10 15 20
-0.01
α -0.02 NACA 0009
KFm3
-0.03
-0.04
-0.05
-0.06
-0.07
Cm
NACA 0009
AOA 0⁰

KFm3
AOA 0⁰