Aerospike for Drag Reduction in Hypersonic Flow

Kalimuthu, R.; Rathakrishnan, E.

doi:10.2514/6.2008-4707

Cited by 16 publications

(6 citation statements)

References 6 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Mach 6.0 experiments with variations in geometrical parameters of spike and di erent shapes were tested by Kalimuthu et al [5], who reported that the aerodisc con guration performed better than aerospikes. However, in the same line, Kalimuthu and Rathakrishnan [6] reported that with a hemispherical aerospike at L=D = 2:0, there was a drag reduction of about 78%. The mechanism of drag reduction with spikes of di erent diameters and lengths at M = 6:0 using extensive computations was reported by Ahmed and Qin [7][8][9].…”

Section: Introductionmentioning

confidence: 93%

Hypersonic Flow over Hemispherical Blunt Body with Spikes

2018

View full text Add to dashboard Cite

Abstract. Use of spike on a hemispherical body changes the ow eld and hence, the aerodynamic drag. Computational studies have been carried out to obtain the ow eld around a hemispherical body with spikes at a hypersonic Mach number of 6. The e ect of shape of spike tip and length has been studied. Laminar computations have been made adopting structured grid using commercial software FLUENT. It is observed that use of a sharp spike itself reduces the drag signi cantly. However, the use of a hemispherical head spike further reduces the drag. Contribution of di erent components towards drag indicates that the increase in length of a spike does not change the spike contribution. However, the ow eld on main body is altered, which leads to reduction in drag with change in length. The estimated maximum drag is found to be highest among all reported drag values with any spike shape and length in the literature.

show abstract

Section: Introductionmentioning

confidence: 93%

Hypersonic Flow over Hemispherical Blunt Body with Spikes

2018

View full text Add to dashboard Cite

show abstract

“…Spikes with different lengths and aerodisk designs were examined and drag and aeroheating to the forebody at different incidence angles were measured. Mehta and his co-researchers conducted a number of experimental and numerical studies [26,39,48,[79][80][81][82][83][84][85][86]. They examined drag and aeroheating to a hemispherical forebody model equipped with various spike and aerodisk designs at Mach 6 and different incidence angles.…”

Section: Survey On Key Studies On Mechanical Spikesmentioning

confidence: 99%

Forebody shock control devices for drag and aero-heating reduction: A comprehensive survey with a practical perspective

Ahmed

Qin

2020

Progress in Aerospace Sciences

View full text Add to dashboard Cite

One key feature that distinguishes the flowfield around vehicles flying in supersonic and hypersonic regimes is the bow shock wave ahead of forebody. The severe drag and aeroheating impacting these vehicles can be significantly reduced if the bow shock wave ahead of the vehicles forebodies is controlled to yield weaker system of oblique shocks. Benefits of forebody shock control include increasing flight ranges, economizing fuel consumption, reducing dead weights, and thermally protecting forebody structure and onboard equipment. Forebody shock control that has been widely studied since the early 1900s is achievable in numerous techniques that vary according to the mechanism of control. While some of these techniques have already been implemented in real systems, other techniques involve serious complications and tough trade-offs. The present paper is intended to serve as the first comprehensive survey on the field of forebody shock control devices. The objectives of the present paper are multifold. The paper categorizes the various forebody shock control devices in a physics-based manner, explains the underlying physics for each device, and surveys the key studies and state-of-the-art knowledge. The paper also addresses the existing gaps in knowledge, highlights the existing systems implementing these devices, and discusses the associated practical implementation issues and design-tradeoffs. 2. Structural devices, the mechanical spikes: 2.1. Principle of operation of mechanical spikes Drag and Aeroheating Reduction Devices Fluidic Devices Opposing jets Structural Devices Mechanical spikes Energetic Devices Energy deposition Basic devices Structural-Fluidic Devices Structural-Energetic Devices Hybrid devices

show abstract

“…The diameter of the cylindrical forebody, D, is 40 mm and the length of the forebody is taken as 1.25D. L/D ratio is taken as 1.5 and 2 depending on the case selection [13]. Aerospike tip is taken as hemispherical with diameter 0.1D as shown in the Fig.…”

Section: Geometry and Computational Domainmentioning

confidence: 99%

Study of Hypersonic Flow Past Spiked Blunt Body Using Direct Simulation Monte Carlo Method

Jiss¹,

Sandeep²,

Reji³

et al. 2016

Topical Problems of Fluid Mechanics 2016

View full text Add to dashboard Cite

High speed flow past a blunt body generates a detached bow shock which leads to a high surface pressure and as a result the development of a high aerodynamic drag. One of the ways to reduce drag and heat flux is the employment of an aerospike. Flow under consideration occurs at rarefied conditions. In the present study, the flow around a blunted body fitted with an aerospike is analyzed using an open source Direct Simulation Monte Carlo (DSMC) code, called as dsmcFoam in OpenFOAM, at a high Mach number (M=6) at different length to diameter ratios (L/D = 1.5, 2) at an angle of attack 0 o. The aerospike replaces the strong detached shock wave ahead of the body with a system of weaker oblique shock waves. A recirculating flow zone is developed between the shock and the blunt body, which acts like a streamlined profile, thus reducing the drag and wall heat flux. Reducing the aerodynamic drag ensures reaching the desired range or altitude, reduces the fuel usage, simplify the propulsion system requirements and maximize the ratio of payload to take off gross weight.

show abstract

Aerospike for Drag Reduction in Hypersonic Flow

Cited by 16 publications

References 6 publications

Hypersonic Flow over Hemispherical Blunt Body with Spikes

Hypersonic Flow over Hemispherical Blunt Body with Spikes

Forebody shock control devices for drag and aero-heating reduction: A comprehensive survey with a practical perspective

Study of Hypersonic Flow Past Spiked Blunt Body Using Direct Simulation Monte Carlo Method

Contact Info

Product

Resources

About