A three-dimensional implicit Full Navier-Stokes (FNS) analysis and a 3D Reduced Navier-Stokes (RNS) initial value space marching solution technique has been applied to a class of separate flow problems within a diffusing S-duct configuration characterized as vortex-liftoff. Both Full Navier-Stokes and Reduced Navier-Stokes solution techniques were able to capture the overall flow physics of vortex lift-off, however more consideration must be given to the development of turbulence models for the prediction of the locations of separation and reattachment. This accounts for some of the discrepancies in the prediction of the relevant inlet distortion descriptors, particularly circumferential distortion. The 3D RNS solution technique adequately ...
The supersonic diffuser of a Mach 2.68 bifurcated, rectangular, mixed-compression inlet was analyzed...
The internal fluid mechanics research program in inlets, ducts, and nozzles consists of a balanced e...
Previous work at NASA LeRC has shown that flow distortions in aircraft engine inlet ducts can be sig...
A Reduced Navier-Stokes (RNS) solution technique was successfully combined with the concept of parti...
A reduced Navier Stokes (RNS) initial value space marching solution technique was applied to vortex ...
Full three-dimensional Navier-Stokes computational results are compared with new experimental measur...
Numerical investigations on a diffusing S-duct with/without vortex generators and a straight duct wi...
The purpose of the present study was to evaluate the capability of the computational fluid dynamics ...
Computational uncertainties in turbulence modeling for three dimensional inlet flow fields include f...
The present study demonstrates that the Reduced Navier-Stokes code RNS3D can be used very effectivel...
The theoretical and experimental work carried out under the NASA/MOD Joint Aeronautical Program has ...
A parabolized Navier-Stokes code was used to analyze a number of diffusers typical of a modern inlet...
The supersonic diffuser of a Mach 2.68 bifurcated, rectangular, mixed-compression inlet was analyzed...
A method for calculating the flow field in aircraft engine inlets is presented. The phenomena of inl...
A three-dimensional parabolic Navier-Stokes code, PEPSIG, was used to analyze the flow in the subson...
The supersonic diffuser of a Mach 2.68 bifurcated, rectangular, mixed-compression inlet was analyzed...
The internal fluid mechanics research program in inlets, ducts, and nozzles consists of a balanced e...
Previous work at NASA LeRC has shown that flow distortions in aircraft engine inlet ducts can be sig...
A Reduced Navier-Stokes (RNS) solution technique was successfully combined with the concept of parti...
A reduced Navier Stokes (RNS) initial value space marching solution technique was applied to vortex ...
Full three-dimensional Navier-Stokes computational results are compared with new experimental measur...
Numerical investigations on a diffusing S-duct with/without vortex generators and a straight duct wi...
The purpose of the present study was to evaluate the capability of the computational fluid dynamics ...
Computational uncertainties in turbulence modeling for three dimensional inlet flow fields include f...
The present study demonstrates that the Reduced Navier-Stokes code RNS3D can be used very effectivel...
The theoretical and experimental work carried out under the NASA/MOD Joint Aeronautical Program has ...
A parabolized Navier-Stokes code was used to analyze a number of diffusers typical of a modern inlet...
The supersonic diffuser of a Mach 2.68 bifurcated, rectangular, mixed-compression inlet was analyzed...
A method for calculating the flow field in aircraft engine inlets is presented. The phenomena of inl...
A three-dimensional parabolic Navier-Stokes code, PEPSIG, was used to analyze the flow in the subson...
The supersonic diffuser of a Mach 2.68 bifurcated, rectangular, mixed-compression inlet was analyzed...
The internal fluid mechanics research program in inlets, ducts, and nozzles consists of a balanced e...
Previous work at NASA LeRC has shown that flow distortions in aircraft engine inlet ducts can be sig...