Add to ORKGCounterflow drag reduction by supersonic jet for a large angle blunt cone at hypersonic Mach number is investigated in a shock tunnel. The flowfields around the test model in the hypersonic flow with an opposing supersonic jet emanating from the stagnation point of the model are visualized by high speed schlieren technique. The aerodynamic drag force is measured using the accelerometer based force balance system. The experimental measurements show about 30%–45% reduction in drag coefficient for different jet pressures
This paper presents a summary and comparison of results of parametric numerical studies examining va...
A computational survey of the pressure drag on axisymmetric conical bodies of varying vertex angle a...
A new idea of drag reduction and thermal protection for hypersonic vehicles is proposed based on the...
Counterflow supersonic jet is used as a drag reduction device during the experiments in free piston ...
Counterflow drag reduction by supersonic jet for a 60° apex angle blunt cone flying at hypersonic Ma...
Substantial aerodynamic drag, while flying at hypersonic Machnumber, due to the presence of strong s...
A three-component accelerometer balance system is used to study the drag reduction effect of an aero...
An experimental investigation of aerodynamic drag reduction by counter now plasma jet injection from...
Reduction in aerodynamic drag for a large angle blunt cone flying at hypersonic Mach number by heat ...
Drag reduction studies are conducted using a flat disc tipped aerospike for a 120-degree apex angle ...
AbstractRecently, Nhypersonic research activities around the universe have been in major focus becau...
The time-dependent evolution of flow around a 120° blunt cone model with a base radius of 60 mm has ...
This study describes numerical computations of aerospike and counterflowing jet as the drag reductio...
Passive and active flow control methods are used to manipulate flow fields to reduce acoustic signat...
Effectiveness of aerospikes/aerodisk assemblies as retractable drag-reduction devices for large-angl...
This paper presents a summary and comparison of results of parametric numerical studies examining va...
A computational survey of the pressure drag on axisymmetric conical bodies of varying vertex angle a...
A new idea of drag reduction and thermal protection for hypersonic vehicles is proposed based on the...
Counterflow supersonic jet is used as a drag reduction device during the experiments in free piston ...
Counterflow drag reduction by supersonic jet for a 60° apex angle blunt cone flying at hypersonic Ma...
Substantial aerodynamic drag, while flying at hypersonic Machnumber, due to the presence of strong s...
A three-component accelerometer balance system is used to study the drag reduction effect of an aero...
An experimental investigation of aerodynamic drag reduction by counter now plasma jet injection from...
Reduction in aerodynamic drag for a large angle blunt cone flying at hypersonic Mach number by heat ...
Drag reduction studies are conducted using a flat disc tipped aerospike for a 120-degree apex angle ...
AbstractRecently, Nhypersonic research activities around the universe have been in major focus becau...
The time-dependent evolution of flow around a 120° blunt cone model with a base radius of 60 mm has ...
This study describes numerical computations of aerospike and counterflowing jet as the drag reductio...
Passive and active flow control methods are used to manipulate flow fields to reduce acoustic signat...
Effectiveness of aerospikes/aerodisk assemblies as retractable drag-reduction devices for large-angl...
This paper presents a summary and comparison of results of parametric numerical studies examining va...
A computational survey of the pressure drag on axisymmetric conical bodies of varying vertex angle a...
A new idea of drag reduction and thermal protection for hypersonic vehicles is proposed based on the...