Experimental investigation on drag and heat flux reduction in supersonic/hypersonic flows: A survey
Z Wang, X Sun, W Huang, S Li, L Yan - Acta Astronautica, 2016 - Elsevier
The drag and heat reduction problem of hypersonic vehicles has always attracted the
attention worldwide, and the experimental test approach is the basis of theoretical analysis …
attention worldwide, and the experimental test approach is the basis of theoretical analysis …
Grooved cavity as a passive controller behind backward facing step
A semicircular grooved cavity is designed for controlling the base pressure and hence the
base drag in case of a backward facing step. This paper presents the effect of the continuous …
base drag in case of a backward facing step. This paper presents the effect of the continuous …
Study of direct gas injection into stagnation zone of blunt nose at hypersonic flow
P Harmon, A Vashishtha, D Callaghan… - AIAA Propulsion and …, 2021 - arc.aiaa.org
View Video Presentation: https://doi. org/10.2514/6.2021-3529. vid Direct gas injection in the
shocked or compressed region has importance in many applications from drag control to …
shocked or compressed region has importance in many applications from drag control to …
Conceptual design of deployment structure of morphing nose cone
For a reusable space vehicle or a missile, the shape of the nose cone has a significant effect
on the drag of the vehicle. In this paper, the concept of morphing nose cone is proposed to …
on the drag of the vehicle. In this paper, the concept of morphing nose cone is proposed to …
Flow field around a blunt-nosed body with spike
S Khurana, K Suzuki, E Rathakrishnan - Int. J. Turbo Jet-Engines, 2012 - degruyter.com
The zone of influence and the positive pressure field over the nose, for a blunt-nosed body,
with and without spike, were measured by direct means. Flow past the body, with and …
with and without spike, were measured by direct means. Flow past the body, with and …
Aerodynamic characteristics of breathing blunt nose configuration at hypersonic speeds
Y Watanabe, K Suzuki… - Proceedings of the …, 2017 - journals.sagepub.com
Breathing blunt nose technique is one of the promising methods for reducing the drag of
blunt-nosed body at hypersonic speeds. The air, traversed by the bow shock positioned …
blunt-nosed body at hypersonic speeds. The air, traversed by the bow shock positioned …
Bow-shock instability and its control in front of hemispherical concave shell at hypersonic Mach number 7
A Vashishtha, Y Watanabe, K Suzuki - TRANSACTIONS OF THE …, 2016 - jstage.jst.go.jp
The blunt nose shapes have great influence on drag of moving object in hypersonic flow-
field because of detached bow-shock formation in front of the body. For the same reference …
field because of detached bow-shock formation in front of the body. For the same reference …
Experimental analysis on drag coefficient reduction techniques
Drag reduction geometries is one of the burning issues in the present aerodynamics on
which vast range of work is going on. Generally drag is the force exerted by the medium on …
which vast range of work is going on. Generally drag is the force exerted by the medium on …
[PDF][PDF] Effect of vortex-size around spike root and body base on possible hypersonic drag reduction
S Khurana, K Suzuki, E Rathakrishnan - The Seventh International …, 2012 - iawe.org
Large drag encountered by a blunt-nosed body, flying at a hypersonic speed, is primarily
due to the high-pressure zone caused by the detached shock at the nose of the body. Spike …
due to the high-pressure zone caused by the detached shock at the nose of the body. Spike …
Design and analysis of breathing blunt nose (BBN) with flat-faced aero-disk for drag reduction in supersonic flows
P Sagar, SG Rakesh - AIP Conference Proceedings, 2022 - pubs.aip.org
The design of a vehicle flying at supersonic and hypersonic velocities plays a crucial role in
the performance and efficiency of the vehicle, because at these velocities there will be shock …
the performance and efficiency of the vehicle, because at these velocities there will be shock …