Add to ORKGEffects of boundary layer bleed rate and location on performance of axisymmetric inlet designed for Mach 2.
The supersonic diffuser of a Mach 2.68 bifurcated, rectangular, mixed-compression inlet was analyzed...
An analytical bleed system design procedure is applied to a Mach 3.5, axisymmetric, translating cent...
Wind tunnel study of boundary-layer-control throat bleed slot variations on internal performance of ...
Performance tests of wind tunnel model inlet for bleed system back pressure and porous area effect o...
An experimental investigation has been made of the boundary layer flow in a supersonic axisymmetric ...
The results of an experimental bleed development study for a full-scale, Mach 2.5, axisymmetric, mix...
An experimental investigation of a full scale mixed compression inlet sized for the TF30-P-3 turbofa...
The results of an experimental investigation to increase the stable airflow range of a super sonic m...
An investigation of the tolerances of two Mach 2.50 axisymmetric mixed-compression inlets to upstrea...
Vortex generators were investigated as a means of controlling the throat boundary layer in a Mach 2....
The results of an experimental bleed development study for a full-scale, Mach 2.5, axisymmetric, mix...
The results of an experimental investigation to increase the stable airflow operating range of a sup...
An experimental study was conducted to determine the performance of a two-dimensional, mixed-compres...
The distortion characteristics were investigated at the subsonic diffuser exit of a full-scale, Mach...
The effect of an external boundary layer on the performance of an axisymmetric external-internal-com...
The supersonic diffuser of a Mach 2.68 bifurcated, rectangular, mixed-compression inlet was analyzed...
An analytical bleed system design procedure is applied to a Mach 3.5, axisymmetric, translating cent...
Wind tunnel study of boundary-layer-control throat bleed slot variations on internal performance of ...
Performance tests of wind tunnel model inlet for bleed system back pressure and porous area effect o...
An experimental investigation has been made of the boundary layer flow in a supersonic axisymmetric ...
The results of an experimental bleed development study for a full-scale, Mach 2.5, axisymmetric, mix...
An experimental investigation of a full scale mixed compression inlet sized for the TF30-P-3 turbofa...
The results of an experimental investigation to increase the stable airflow range of a super sonic m...
An investigation of the tolerances of two Mach 2.50 axisymmetric mixed-compression inlets to upstrea...
Vortex generators were investigated as a means of controlling the throat boundary layer in a Mach 2....
The results of an experimental bleed development study for a full-scale, Mach 2.5, axisymmetric, mix...
The results of an experimental investigation to increase the stable airflow operating range of a sup...
An experimental study was conducted to determine the performance of a two-dimensional, mixed-compres...
The distortion characteristics were investigated at the subsonic diffuser exit of a full-scale, Mach...
The effect of an external boundary layer on the performance of an axisymmetric external-internal-com...
The supersonic diffuser of a Mach 2.68 bifurcated, rectangular, mixed-compression inlet was analyzed...
An analytical bleed system design procedure is applied to a Mach 3.5, axisymmetric, translating cent...
Wind tunnel study of boundary-layer-control throat bleed slot variations on internal performance of ...