High-Pressure Shock Tunnel Experiments and CFD Calculations on Spike-Tipped Blunt Bodies

Srulijes, J.; Gnemmi, Patrick; Runne, K.; Seiler, F.

doi:10.2514/6.2002-2918

Cited by 17 publications

(9 citation statements)

References 7 publications

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“…All the proposed techniques focus only on reducing the shock strength in front of the nose. Spikes ahead of the blunt-nose with different spike-tip shapes are employed to weaken the shock strength (bow and oblique shocks) to reduce the pressure drag on the aft body [3]. However, the use of spike adds an extra weight to the flying body and during maneuver (like pitch and yaw), there is an additional side-force, due to the spike, acting on the body.…”

Section: Introductionmentioning

confidence: 99%

Breathing blunt-nose concept for drag reduction in supersonic flow

Vashishtha

Rathakrishnan

2008

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper presents the results and the physics behind the process which results in the reduction of pressure drag of blunt-nosed body by passive control in form of breathing nose at a supersonic Mach number. The drag of a blunt-nosed body with and without breathing nose at Mach 1.96 is compared. The breathing nose is found to reduce the drag on the body by manipulating the high pressure at the nose and the low pressure at the base simultaneously. The shock at the nose of the body becomes weaker when the hole at the nose is open. Direct measurement of drag and the pressure at the nose and at the surface downstream of the nose has been carried out. Flow field around the body with and without breathing nose has been visualized with shadowgraph. A maximum drag reduction of 21 per cent was obtained at NPR 2. This is because of the combined effect of the decrease of high pressure at the nose and increase of low pressure at the base, due to the breathing through the nose hole.

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Section: Introductionmentioning

confidence: 99%

Breathing blunt-nose concept for drag reduction in supersonic flow

Vashishtha

Rathakrishnan

2008

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Many researchers carried out parametric studies to interpret the length and shape of the spike, aerodisk geometry, spike diameter, forebody geometry, and free stream conditions. [43][44][45] Factors affecting mechanical spike. The spike effectiveness can be enhanced by increasing spike length.…”

Section: Mechanical Spikementioning

confidence: 99%

Review of wave drag reduction techniques: Advances in active, passive, and hybrid flow control

Rashid

Nawaz

Maqsood

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Typical challenges of supersonic flight include wave drag, acoustic signature, and aerodynamic heating due to the formation of shock waves ahead of the vehicle. Efforts in the form of sleek aerodynamic designs, better propulsion systems, and the implementation of passive and active techniques are generally adopted to achieve a weaker shock wave system. Shock reduction can improve flight range, reduce fuel consumption, and provide thermal protection of the forebody region. This paper briefly reviews shock reduction techniques, including passive, active, and hybrid flow control. Airfoil shape optimization, mechanical spike, and forebody cavities are studied as passive flow control approaches. For active flow control, developments in the area of opposing jets and energy deposition are explored. The combination of active and passive flow control and the hybrid flow techniques are discussed in the end. The discussions include the principle of operation, physics of fluid behavior, and overall contribution to flight stability characteristics. The implications in the usage of these technologies, along with potential gaps, are also identified. This comprehensive review can serve as the basis for contemporary solutions to realize sustainable supersonic travel for the aviation industry.

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“…To control and reduce the aerodynamic heating and drag force imposed on the body by the strong shock, several methods were proposed, such as attachment of aero spike at the blunt-nose in one such technique. 1 A spike attached at the blunt-nose and projecting ahead of the body changes the bow shock to oblique shock, thereby causing significant reduction of drag and aerodynamic heating. Counter-jet flow method 2 is another method.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic characteristics of breathing blunt nose configuration at hypersonic speeds

Watanabe

Suzuki

Rathakrishnan

2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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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 ahead of the nose, at the stagnation region is allowed to enter through a hole at the blunt-nose and ejected at the rear part (base region) of the body. This manipulation reduces the positive pressure over the stagnation regions of the nose and increases the pressure at the base, resulting in reduced suction at the base. The simultaneous manifestation of reducing the compression at the nose and suction at the base regions results in reduction of the total drag. The drag reduction caused by the breathing blunt nose technique has been measured in a Mach 7 tunnel. Also, the drag and flow field around the blunt-nosed body, with and without breathing hole, has been computed. The aerodynamic characteristics of the breathing blunt nose model obtained experimentally are compared with the CFD results. It is found that the breathing results in 5% reduction in drag. The lift coefficient also comes down for the model with breathing nose. But the lift-to-drag ratio is found to be the same for both the cases; the blunt-nosed body with and without nose-hole.

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High-Pressure Shock Tunnel Experiments and CFD Calculations on Spike-Tipped Blunt Bodies

Cited by 17 publications

References 7 publications

Breathing blunt-nose concept for drag reduction in supersonic flow

Breathing blunt-nose concept for drag reduction in supersonic flow

Review of wave drag reduction techniques: Advances in active, passive, and hybrid flow control

Aerodynamic characteristics of breathing blunt nose configuration at hypersonic speeds

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