Supersonic Flow Over Naca4412_finalevaluation
-
Upload
haardikgarg -
Category
Documents
-
view
224 -
download
5
description
Transcript of Supersonic Flow Over Naca4412_finalevaluation
Indian Institute of TechnologyHyderabad
SUPERSONIC FLOW OVER NACA4412
Sunil kumar Reddy(ME12B1003) Haardik Garg(ME12B1018)
INTRODUCTION
An airfoil is the shape of a wing, blade(of a propeller, rotor or turbine) or sail.
An airfoil-shaped body moved through a fluid produces an aerodynamic force.
The component of this force perpendicular to the direction of motion is called lift.
The component parallel to the direction of motion is called drag.
GeometryThe NACA airfoils are airfoil shapes for aircraft wings developed by
the National Advisory Committee for Aeronautics(NACA).
The shape of the NACA airfoils is described using a series of digits following the word "NACA".
The parameters in the numerical code can be entered into equations to precisely generate the cross-section of the airfoil and calculate its properties.
Blue-chord, green- camber mean line
NACA 4412:chamber is 0.04 or 4% of chord(first digit).maximum chamber is at 0.4 or 40% of chord(second digit).Thickness is 0.12 or 12% of the chord(last two digits).
NACA 4 digit airfoil calculation:
The NACA airfoil section is created from a camber line and a thickness distribution plotted perpendicular to the camber lineThe equations are:
P-maximum chamber positionThe thickness distribution is given by the equation:
The position of the upper and lower surface can then be calculated perpendicular to the camber line.
This is the shape of NACA 4412 obtained from points generated through the equations
Analytical Equations[Linearized Supersonic Flow on Airfoil Lift & Drag]
Geometry
Mesh
Nodes-11772 Elements-11522
Analysis for different Mach numbersInputs Analysis is done for different Mach numbers Angle of attack – 60
At sea level Ambient pressure at outlet Second order upwind scheme is used
Static Pressure for mach-0.8
Static Pressure for mach-1
Static Pressure for mach-1.2
Static Pressure for mach-2
Mach number Minimum static pressure(gauge pressure)(pa)
0.8 -5.56e4
1 -8.67e4
1.2 -1.25e5
2 -3.47e5
Velocity for mach-0.8
Velocity for mach-1
Velocity for mach-1.2
Velocity for mach-2
Mach number Maximum velocity magnitude(m/s)0.8 4.09e2
1 5.11e2
1.2 6.13e2
2 1.02e3
Analysis at different altitudesInputs Analysis is done at different altitudes Angle of attack – 60
Mach number - 2 Second order upwind scheme is used
Static Pressure at sea level
Static Pressure at 4000m high
Static Pressure at 6000m high
Static Pressure at 8000m high
Static Pressure at 10000m high
Altitude(m) Minimum static pressure(gauge pressure)(pa)
0 -3.47e5
4000 -2.06e5
6000 -1.6e5
8000 -1.24e5
10000 -9.45e4
velocity at sea level
velocity at 4000m high
velocity at 6000m high
velocity at 8000m high
velocity at 10000m high
Altitude(m) Maximum velocity magnitude(m/s)0 1.02e3
4000 9.55e2
6000 9.31e2
8000 9.06e2
10000 8.81e2
Analysis for different angle of attackInputs Analysis is done for different angle of attack At sea level Mach number - 2 Ambient pressure at outlet Second order upwind scheme is used
Static Pressure at 20 angle of attack
Static Pressure at 40 angle of attack
Static Pressure at 60 angle of attack
Static Pressure at 100 angle of attack
Angle of attack(degree) Minimum static pressure(gauge pressure)(pa)
2 -2.64e5
6 -3.47e5
10 -4.78e5
20 -9.32e5
velocity at 20 angle of attack
velocity at 60 angle of attack
velocity at 100 angle of attack
velocity at 200 angle of attack
Angle of attack(degree) Maximum velocity magnitude(m/s)2 9.58e2
6 1.02e3
10 1.09e3
20 1.26e3
Lift Coefficient & Drag Coefficient
Lift coefficient vs angle of attack Drag coefficient vs angle of attack
Analysis for different Mach numbers with viscous effectsInputs Analysis is done for different Mach numbers Angle of attack – 60
At sea level Ambient pressure at outlet Second order upwind scheme is used K-Ԑ model is used
Static Pressure for mach-0.8
Static Pressure for mach-1
Static Pressure for mach-1.2
Static Pressure for mach-2
Mach number Minimum static pressure(gauge pressure)(pa) with viscous effects
Minimum static pressure(gauge pressure)(pa) without viscous effects
0.8 -5.01e4 -5.56e41 -7.86e4 -8.67e41.2 -1.14e5 -1.25e52 -3.19e5 -3.47e5
Velocity for mach-0.8
Velocity for mach-1
Velocity for mach-1.2
Velocity for mach-2
Mach number Maximum velocity magnitude(m/s)With viscous effects
Maximum velocity magnitude(m/s)Without viscous effects
0.8 3.81e2 4.09e2
1 4.77e2 5.11e2
1.2 5.73e2 6.13e2
2 9.58e2 1.02e3
References https://en.wikipedia.org/wiki/Airfoil http://airfoiltools.com/airfoil/details?airfoil=naca4412-il http://www.edforall.net/index.php/engineering-a-technology/aeronautical-engineeri
ng/100-aerodynamics/1951-implications-of-linearized-supersonic-flow-on-airfoil-lift-and-drag