Numerical Investigation of a Spiked Blunt Nose Cone at Hypersonic Speeds

Gauer, Markus; Paull, A.

doi:10.2514/1.30590

Cited by 80 publications

(39 citation statements)

References 9 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…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]. Numerical studies made by Gauer and Paull [10] at Mach numbers from 5.0 to 10.0 with various L=D's of spikes (1.0 to 4.0) indicated maximum drag reduction of 30% with sharp spike, 50% with blunt spike, and 62% with aerodome spike. Computation at M = 6:0 with conical, hemispherical, and a at faced aerodisk spikes achieved a maximum drag reduction of 60% in the reports by Tahani et al [11].…”

Section: Introductionmentioning

confidence: 65%

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: 65%

Hypersonic Flow over Hemispherical Blunt Body with Spikes

2018

View full text Add to dashboard Cite

show abstract

“…However, the effect of drag and heat transfer reduction depend on the flow conditions, blunt body shape, and spike geometry. In addition, the drag of the hypersonic body with aerospike can be reduced from 20 to 60 percent [3]. There are many studies as to the investigation of the reduction of drag and heat transfer in the blunt bodies, Crawford [4] measured the drag and heat transfer amounts of hypersonic hemisphere cylindrical bodies coupled with pointed spikes in laminar and turbulent flows at Mach number equals 6.8.…”

Section: Introductionmentioning

confidence: 99%

Drag Reduction Optimization for Hypersonic Blunt Body with Aerospikes

Wan¹,

Cm²

2017

J Aeronaut Aerospace Eng

View full text Add to dashboard Cite

Pressure drag and aeroheating stirred by the shock wave is the main challenge of hypersonic flight, and blunt body is always the principle configuration at hypersonic flow regime for heat distribution, but it would induce substantial drag. Therefore, both aerospikes and aerodisks can be efficiently utilized as a mean for drag reduction. In this work, we investigate the effect of different geometric shapes of aerospikes with various disk gap widths on drag reduction. Accordingly, a series of numerical simulation work was implemented to find the behaviour as to hypersonic flow over aerospiked blunt bodies. Moreover, the drag reduction efficiency of spiked blunt bodies would be optimized via the Kriging method. For the models we studied, we found that the drag on the spiked blunt bodies is much lower than the spike off one. The drag reduction efficiency especially would be predominated by the scale of recirculation zone, which increases as both the spike length and the gap size of aerodisk increase. Hence, the performance of drag diminution will depend on the design parameters such as main body configurations, aerospike length, and tip geometric shapes.

show abstract

“…Of these techniques, using spikes is the simplest and the most reliable technique. Gauer and Paull [10] numerically investigated the drag and the heat-transfer reduction of a forward-facing spike with varying length and shape in comparison to the unspiked nose cone. Ahmed and Qin [11] compared the spike and aerodisk with the unspiked nose cone and researched a mechanism to explain the drag reduction and the cause of flow instability based on the shape of an effective body.…”

Section: Introductionmentioning

confidence: 99%

Conceptual Design of Deployment Structure of Morphing Nose Cone

Yan

2013

Advances in Mechanical Engineering

View full text Add to dashboard Cite

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 reduce the drag when the reentry vehicle flies back into the atmosphere. The conceptual design of the structure of morphing nose cone is conducted. Mechanical design and optimization approach are developed by employing genetic algorithm to find the optimal geometric parameters of the morphing structure. An example is analyzed by using the proposed method. The results show that optimal solution supplies the minimum position error. The concept of morphing nose cone will provide a novel way for the drag reduction of reentry vehicle. The proposed method could be practically used for the design and optimization of the deployable structure of morphing nose cone.

show abstract

Numerical Investigation of a Spiked Blunt Nose Cone at Hypersonic Speeds

Cited by 80 publications

References 9 publications

Hypersonic Flow over Hemispherical Blunt Body with Spikes

Hypersonic Flow over Hemispherical Blunt Body with Spikes

Drag Reduction Optimization for Hypersonic Blunt Body with Aerospikes

Conceptual Design of Deployment Structure of Morphing Nose Cone

Contact Info

Product

Resources

About