Steady-state and dynamic flow characteristics associated with two sets of vortex generators having different mixing criteria were determined. The inlet performance with and without these vortex generators is presented. The vortex generators were successful in eliminating separation, increasing area-weighted total pressure recovery, and decreasing distortion. Transmission times obtained from cross-correlations of the wall static pressures and the diffuser exit total pressure showed no effect of the upstream flow characteristics on the diffuser exit pressures when generators were used. Without generators, separation occurred and the upstream pressure characteristics had immediate effects on the diffuser exit pressure characteristics
Wind tunnel tests to determine Mach 2.5 performance of bicone inlet with internal focused compressio...
Results of experimental tests conducted on a supersonic, mixed-compression, axisymmetric inlet are p...
Performance tests of wind tunnel model inlet for bleed system back pressure and porous area effect o...
Vortex generators were investigated as a means of controlling the throat boundary layer in a Mach 2....
Performance of vortex generators installed aft of inlet throat on centerbody evaluated at Mach numbe...
Vortex generators within a two-dimensional, external-compression supersonic inlet for Mach 1.6 were ...
The distortion characteristics were investigated at the subsonic diffuser exit of a full-scale, Mach...
Vortex generators within a streamline-traced, external-compression supersonic inlet for Mach 1.66 we...
An experimental study was conducted to determine the performance of a two-dimensional, mixed-compres...
The inlet was designed to have the minimum internal contraction consistent with high total-pressure ...
Computational simulations of the flow within a streamline-traced, external-compression supersonic in...
Reduce the total pressure distortion at the engine-fan face due to low-momentum flow caused by the i...
Results of experimental tests conducted on a supersonic, mixed compression, axisymmetric inlet are p...
The theoretical and experimental work carried out under the NASA/MOD Joint Aeronautical Program has ...
Effects of boundary layer bleed rate and location on performance of axisymmetric inlet designed for ...
Wind tunnel tests to determine Mach 2.5 performance of bicone inlet with internal focused compressio...
Results of experimental tests conducted on a supersonic, mixed-compression, axisymmetric inlet are p...
Performance tests of wind tunnel model inlet for bleed system back pressure and porous area effect o...
Vortex generators were investigated as a means of controlling the throat boundary layer in a Mach 2....
Performance of vortex generators installed aft of inlet throat on centerbody evaluated at Mach numbe...
Vortex generators within a two-dimensional, external-compression supersonic inlet for Mach 1.6 were ...
The distortion characteristics were investigated at the subsonic diffuser exit of a full-scale, Mach...
Vortex generators within a streamline-traced, external-compression supersonic inlet for Mach 1.66 we...
An experimental study was conducted to determine the performance of a two-dimensional, mixed-compres...
The inlet was designed to have the minimum internal contraction consistent with high total-pressure ...
Computational simulations of the flow within a streamline-traced, external-compression supersonic in...
Reduce the total pressure distortion at the engine-fan face due to low-momentum flow caused by the i...
Results of experimental tests conducted on a supersonic, mixed compression, axisymmetric inlet are p...
The theoretical and experimental work carried out under the NASA/MOD Joint Aeronautical Program has ...
Effects of boundary layer bleed rate and location on performance of axisymmetric inlet designed for ...
Wind tunnel tests to determine Mach 2.5 performance of bicone inlet with internal focused compressio...
Results of experimental tests conducted on a supersonic, mixed-compression, axisymmetric inlet are p...
Performance tests of wind tunnel model inlet for bleed system back pressure and porous area effect o...