Search
CSV
RISEffects of Boundary-Layer Bleed Parameters on Supersonic Intake Performance
Mach numbers of 1.8, 2.0, and 2.2 and at a zero degree angle of attack are studied. The intake performance is assessed using the total pressure recovery, mass flow ratio, flow distortion, and bleed mass flow ratio. The results show that applying...
Comparison between Scalar, CUSP and AUSM family Schemes in Low and High Mach numbers
In this research two flux vector splitting applied in the solution of Euler Equations namely AUSM+up and AUSM+ schemes are analyzed. The functionality of each scheme, in first and second order accuracy, and the effect of ...
Investigation of Corner Rounding Effects on the Performance of a Supersonic Air Intake
In this research, flow is simulated numerically through and around a mixed-compression intake to investigate effects of corner rounding on intake performance at free stream Mach numbers of 1.8, 2 and 2.2 and at zero degrees angle of attack...
A single-magnetic cell-to-cell battery equalization converter
Compressibility effects on the flow past a rotating cylinder
Abstract
In this paper, the flow past a rotating circular cylinder placed in a compressible uniform stream is investigated via numerical two-dimensional computations. Then, the effect of the free stream Mach number and the non...
STALL SIMULATION OF FLOW AROUND AN AIRFOIL USING LES MODEL AND COMPARISON OF RANS MODELS AT LOW ANGLES OF ATTACK
In this paper, the influence of turbulence modeling, Reynolds number and stall condition
on the fluid numerical solution over NACA0012 airfoil is studied by using the OpenFOAM
package. Large-eddy simulation ...
STALL SIMULATION OF FLOW AROUND AN AIRFOIL USING LES MODEL AND COMPARISON OF RANS MODELS AT LOW ANGLES OF ATTACK
In this paper, the influence of turbulence modeling, Reynolds number and stall condition
on the fluid numerical solution over NACA0012 airfoil is studied by using the OpenFOAM
package. Large-eddy simulation ...
Axisymmetric stagnation flow and heat transfer of a compressible fluid impinging on a cylinder moving axially
. The general self-similar solution is obtained when the wall temperature of the cylinder or its wall heat flux is constant. All the solutions above are presented for Reynolds numbers, , ranging from 0.1 to 1000, low Mach number, selected values...