Add to ORKGThe Direct Simulation Monte Carlo method is used to study the hypersonic, rarified flow interference effects on a flat plate caused by nearby surfaces. Calculations focus on shock-boundary-layer and shock-lip interactions in hypersonic inlets. Results are presented for geometries consisting of a flat plate with different leading-edge shapes over a flat lower wall and a blunt-edge flat plate over a 5-degree wedge. The problems simulated correspond to a typical entry flight condition of 7.5 km/s at altitudes of 75 to 90 km. The results show increases in predicted local heating rates for shock-boundary-layer and shock-lip interactions that are quantitatively similar to those observed experimentally at much higher densities
The problem considered was that of the behaviour of a non - equilibrium flow behind a shock wave su...
The results of an experimental study of off-center-line shock-interference heating on basic shapes a...
Hypersonic transitional flow has been studied using the Direct Simulation Monte Carlo method. The cy...
For hypersonic flow with a shock wave, there is a similar solution consistent throughout the viscous...
Results of a numerical study using the direct simulation Monte Carlo (DSMC) method are presented for...
In studying transition behavior a shock tube and tunnel were used to produce high temperatures, and ...
Cold wall and multibody collision effects on reflection of imploding shock waves using Monte Carlo...
Effect of simulated ablation gas injection on shock layer of blunt bodies at Mach 3 and
Pressure distributions, aerodynamic coefficients, and shock shapes were measured on blunt bodies of ...
Three-dimensional hypersonic rarefied flow about the Aeroassist Flight Experiment (AFE) vehicle was ...
Spatial distribution of radiant heat in reentry vehicle hypersonic shock layers at angle of attac
One dimensional analysis of hypervelocity impact of pellet onto thin bumper using finite difference ...
An analytical and experimental study is presented of the aerodynamic heating resulting from six type...
A brief survey is given on the study of transonic shock/boundary layer effects in flight. Then the p...
Peer Reviewedhttp://deepblue.lib.umich.edu/bitstream/2027.42/77152/1/AIAA-2009-1315-750.pd
The problem considered was that of the behaviour of a non - equilibrium flow behind a shock wave su...
The results of an experimental study of off-center-line shock-interference heating on basic shapes a...
Hypersonic transitional flow has been studied using the Direct Simulation Monte Carlo method. The cy...
For hypersonic flow with a shock wave, there is a similar solution consistent throughout the viscous...
Results of a numerical study using the direct simulation Monte Carlo (DSMC) method are presented for...
In studying transition behavior a shock tube and tunnel were used to produce high temperatures, and ...
Cold wall and multibody collision effects on reflection of imploding shock waves using Monte Carlo...
Effect of simulated ablation gas injection on shock layer of blunt bodies at Mach 3 and
Pressure distributions, aerodynamic coefficients, and shock shapes were measured on blunt bodies of ...
Three-dimensional hypersonic rarefied flow about the Aeroassist Flight Experiment (AFE) vehicle was ...
Spatial distribution of radiant heat in reentry vehicle hypersonic shock layers at angle of attac
One dimensional analysis of hypervelocity impact of pellet onto thin bumper using finite difference ...
An analytical and experimental study is presented of the aerodynamic heating resulting from six type...
A brief survey is given on the study of transonic shock/boundary layer effects in flight. Then the p...
Peer Reviewedhttp://deepblue.lib.umich.edu/bitstream/2027.42/77152/1/AIAA-2009-1315-750.pd
The problem considered was that of the behaviour of a non - equilibrium flow behind a shock wave su...
The results of an experimental study of off-center-line shock-interference heating on basic shapes a...
Hypersonic transitional flow has been studied using the Direct Simulation Monte Carlo method. The cy...