ae 169 cfd project
TRANSCRIPT
AE 169
Professor Dr. Papadopoulos
Robin Dhillon
Duong Tang
1. NACA 0012 Airfoil
2. Analysis of De Laval Nozzle
● Using CFD to simulate the flow around a NACA 0012 airfoil
at Re=1,000,000
● Compare lift and drag coefficients from ESI/ACE+ with
published data
● Use CFD to simulate the flow around de laval nozzle
The NACA 0012 airfoil is a symmetrical airfoil that produces no
lift at zero angle of attack.
Specifications and parameters:
● Thickness: 12.0%
● Camber: 0.0%
● Trailing edge angle: 58.6o
● Leading edge radius: 1.7%
● Zero-lift angle: 0.0o
● Max CL: ~1.35
● Max CL angle:15.0o
● Max L/D:36.958
● Max L/D angle: 7.5o
● Max L/D CL:0.842
Grid independent study:
● Grid points: 100 for airfoil, 150 for nozzle
● Due to time constraints, 300 grid points was not used
Flow conditions to achieve Re=1,000,000:
● 𝑉 = 100𝑚/𝑠
● 𝐶 = 1𝑚
● 𝜌=1.164𝑘𝑔/𝑚3
● 𝜇 = 1.164 ∗ 10−4
● 𝑃 = 100,000𝑃𝑎
Simulation grid
● Divided into 4 sections
● Vertical divider connects
at trailing edge
Simulation geometry
Simulation geometry at an angle of attack (12AoA)
ACE simulation
NACA 0012:
•Lift and drag curve of airfoil
•Flow geometry
Velocity contours at 0 AoA
Pressure contours at 0 AoA
Pressure contours at 1 AoA
Pressure contours at 2 AoA
Pressure contours at 3 AoA
Pressure contours at 4 AoA
Pressure contours at 5 AoA
Pressure contours at 6 AoA
Pressure contours at 7 AoA
Pressure contours at 8 AoA
Pressure contours at 9 AoA
Pressure contours at 10 AoA
Pressure contours at 11 AoA
Pressure contours at 12 AoA
Pressure contours at 13 AoA
Pressure contours at 14 AoA
Pressure contours at 15 AoA
• Convergent-divergent Nozzle
• Nozzle was developed by Swedish
* inventor Gustaf De Laval in 1888
• This principle was first used in a rocket
* engine by Robert Goddard
http://www.academia.edu/7907376/cfd_analysis_of_rocket_nozzle
Parameter Dimension
Total Nozzle Length (mm) 484
Inlet Diameter(mm) 166.6
Throat Diameter(mm) 34.5
Outlet Diameter(mm) 183.0
Chamber Length(mm) 99.93
Convergent Angle (deg) 32
Divergent Angle(deg) 11.31
Static Inlet Pressure(N/m^2) 10000000
Static Outlet Pressure(N/m^2) 101325
Static Inlet Temperature (K) 3300
Grid independent study:
● 150 grid points were used (previously 100, but 150
gave more accurate results)
Simulation grid
● divided into different sections
● easier to achieve orthogonality
● Lift coefficient was more accurate than drag coefficient
● More grid points would have led to more accurate results
● Errors due to differences in Reynolds number and numbers of
iterations
● Adding Boundary Layer improves drag simulation accuracy