Add to ORKGThe hypersonic flow fields around a $120Z^o$ apex angle blunt cone fitted with spikes have been visualized using electric discharge technique at Mach 5.75 in a hypersonic shock tunnel. The blunt cone has been fitted with a flat tipped spike and a flat aerodisc tipped spike assembly. The length of the aerodisc tipped spike assembly has been kept equal to the model base diameter (L/D=1) and the length of the flat tipped spike has been kept at 12mm. The flow field pictures reveal all the salient features of the flow fields around the spiked bodies. Numerical simulations carried out to complement the experiments agree well with the experimental pictures
A novel technique for visualizing the gas temperature layer around bodies flying at hypersonic speed...
We describe here an experimental study on the effect of energy deposition in the flow field of a $12...
The visualization of the wake structure behind hypersonic vehicle was carried out using a new method...
The hypersonic flow fields around a $120Z^o$ apex angle blunt cone fitted with spikes have been visu...
The flowfield around large angle blunt cones flying at hypersonic Mach numbers is complex with a str...
The flow fields around a large apex angle. spiked blunt cone have been analyzed at a hypersonic Mach...
Visualization of the detached shock wave that forms ahead of a blunt body flying at hypersonic Mach ...
Effectiveness of aerospikes/aerodisk assemblies as retractable drag-reduction devices for large-angl...
Based on the principle of dependence of the intensity and the spectrum of the spontaneous light emit...
Investigations on the spatial flowfield of hypersonic shock-wave/boundary-layer interaction have bee...
A three-component accelerometer balance system is used to study the drag reduction effect of an aero...
The experimental investigation on a 600 apex-angle is carried out to study feasibility of simultaneo...
The flow field around a Sharp cone model configuration has been investigated by means of Schlieren ...
This paper described a new visualizing method of streamlines around a body in hypersonic flows. The ...
This paper describes a method for visualizing three-dimensional shock shapes around hypersonic vehic...
A novel technique for visualizing the gas temperature layer around bodies flying at hypersonic speed...
We describe here an experimental study on the effect of energy deposition in the flow field of a $12...
The visualization of the wake structure behind hypersonic vehicle was carried out using a new method...
The hypersonic flow fields around a $120Z^o$ apex angle blunt cone fitted with spikes have been visu...
The flowfield around large angle blunt cones flying at hypersonic Mach numbers is complex with a str...
The flow fields around a large apex angle. spiked blunt cone have been analyzed at a hypersonic Mach...
Visualization of the detached shock wave that forms ahead of a blunt body flying at hypersonic Mach ...
Effectiveness of aerospikes/aerodisk assemblies as retractable drag-reduction devices for large-angl...
Based on the principle of dependence of the intensity and the spectrum of the spontaneous light emit...
Investigations on the spatial flowfield of hypersonic shock-wave/boundary-layer interaction have bee...
A three-component accelerometer balance system is used to study the drag reduction effect of an aero...
The experimental investigation on a 600 apex-angle is carried out to study feasibility of simultaneo...
The flow field around a Sharp cone model configuration has been investigated by means of Schlieren ...
This paper described a new visualizing method of streamlines around a body in hypersonic flows. The ...
This paper describes a method for visualizing three-dimensional shock shapes around hypersonic vehic...
A novel technique for visualizing the gas temperature layer around bodies flying at hypersonic speed...
We describe here an experimental study on the effect of energy deposition in the flow field of a $12...
The visualization of the wake structure behind hypersonic vehicle was carried out using a new method...