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Relevant bibliographies by topics / Spiked body

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Journal articles

Academic literature on the topic 'Spiked body'

Author: Grafiati

Published: 6 September 2023

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Journal articles on the topic "Spiked body"

1

Kalimuthu, R., R. C. Mehta, and E. Rathakrishnan. "Investigation of aerodynamic coefficients at Mach 6 over conical, hemispherical and flat-face spiked body." Aeronautical Journal 121, no. 1245 (2017): 1711–32. http://dx.doi.org/10.1017/aer.2017.100.

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ABSTRACTA forward spike attached to a blunt body significantly alters its flow field characteristics and influences aerodynamic characteristics at hypersonic flow due to formation of separated flow and re-circulation region around the spiked body. An experimental investigation was performed to measure aerodynamic forces for spikes blunt bodies with a conical, hemispherical and flat-face spike at Mach 6 and at an angle-of-attack range from 0° to 8° and length-to-diameterL/Dratio of spike varies from 0.5 to 2.0, whereLis the length of the spike andDis diameter of blunt body. The shape of the lea

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2

Khurana, Shashank, Kojiro Suzuki, and Ethirajan Rathakrishnan. "Flow field behavior with Reynolds number variance around a spiked body." Modern Physics Letters B 30, no. 30 (2016): 1650362. http://dx.doi.org/10.1142/s0217984916503620.

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An experimental visualization study was performed to investigate the dependence of the pressure hill height and the influence zone expanse, for flow past a spiked body with different nose configurations, over a Reynolds number range from 2278 to 4405 to establish the vortex shedding process, and applicability in low speed flow regime for effective pressure reduction. It is found that the spike reduces the radius of curvature of the approaching streamline, leading to the deflection of the streamlines towards the shoulder of the basic body, resulting in a narrow zone of the positive pressure hil

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3

d’Humières, G., and J. L. Stollery. "Drag reduction on a spiked body at hypersonic speed." Aeronautical Journal 114, no. 1152 (2010): 113–19. http://dx.doi.org/10.1017/s0001924000003584.

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AbstractFitting a spike on a blunt body provides a drag reduction at supersonic and hypersonic speeds. In this study, the laminar flow over a spiked, conical body terminated by a spherical cap, inspired by the Apollo re-entry capsule design, was investigated using a hypersonic wind tunnel. Schlieren pictures revealed the absence of flow unsteadiness for the range of spike lengths tested, and force measurements showed a maximum reduction of 77% of the unspiked body drag.A simple theoretical model based on the pressure drag generated by a solid cone showed good agreement with the experimental da

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4

Han, Guilai, and Zonglin Jiang. "Hypersonic Flow Field Reconfiguration and Drag Reduction of Blunt Body with Spikes and Sideward Jets." International Journal of Aerospace Engineering 2018 (2018): 1–16. http://dx.doi.org/10.1155/2018/7432961.

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Flow field reconfiguration and drag reduction have been investigated by numerically solving Navier-Stokes equations, with the 2nd order dispersion controlled dissipative scheme adopted for the convective term discretion and the 2nd order central difference scheme for viscous term. Spikes and sideward jets nearby the spike noses were set up in the front of the blunt body to reconfigure the flow field and reduce drag during hypersonic flight. The spikes and the sideward jets led to the formation of the conical shock, the reattached shock, and the circumfluence, instead of a bow shock. According

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5

Feszty, D., K. J. Badcock, and B. E. Richards. "Utilising CFD in the investigation of high-speed unsteady spiked body flows." Aeronautical Journal 106, no. 1058 (2002): 161–74. http://dx.doi.org/10.1017/s0001924000012963.

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AbstractUnsteady spiked body flows were simulated by a second order time-accurate CFD method. Laminar, axisymmetric flow was considered at Mach 2.21 and Mach 6 freestreams and Reynolds’ numbers based on the blunt body diameter of 0.12 million and 0.13 million, respectively. A spiked forward facing cylinder with spike lengths between LID = 1.00 and LID = 2.40 was used as the model geometry. Following the numerical method’s verification, the individual flow modes of oscillation and pulsation were examined. The frequency of the events was found in good agreement with the experiment, while the pre

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6

Fan, Bing, and Jie Huang. "Coupled Fluid-Thermal Investigation on Drag and Heat Reduction of a Hypersonic Spiked Blunt Body with an Aerodisk." Aerospace 9, no. 1 (2021): 19. http://dx.doi.org/10.3390/aerospace9010019.

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In the traditional investigations on the drag and heat reduction of hypersonic spiked models, only the aerodynamic calculation is performed, and the structural temperature cannot be obtained. This paper adopted the loosely coupled method to study its efficiency of drag and heat reduction, in which the feedback effect of wall temperature rise on aeroheating is considered. The aeroheating and structural temperature were obtained by the CFD and ABAQUS software respectively. The coupling analysis of the hypersonic circular tube was carried out to verify the accuracy of the fluid field, the structu

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7

Wüstenberg, Daniel G., Milena Boytcheva, Bernd Grünewald, John H. Byrne, Randolf Menzel, and Douglas A. Baxter. "Current- and Voltage-Clamp Recordings and Computer Simulations of Kenyon Cells in the Honeybee." Journal of Neurophysiology 92, no. 4 (2004): 2589–603. http://dx.doi.org/10.1152/jn.01259.2003.

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The mushroom body of the insect brain is an important locus for olfactory information processing and associative learning. The present study investigated the biophysical properties of Kenyon cells, which form the mushroom body. Current- and voltage-clamp analyses were performed on cultured Kenyon cells from honeybees. Current-clamp analyses indicated that Kenyon cells did not spike spontaneously in vitro. However, spikes could be elicited by current injection in approximately 85% of the cells. Of the cells that produced spikes during a 1-s depolarizing current pulse, approximately 60% exhibite

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8

Kalimuthu, R., R. C. Mehta, and E. Rathakrishnan. "Experimental investigation on spiked body in hypersonic flow." Aeronautical Journal 112, no. 1136 (2008): 593–98. http://dx.doi.org/10.1017/s0001924000002554.

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Abstract A spike attached to a hemispherical body drastically changes its flowfield and influences aerodynamic drag in a hypersonic flow. It is, therefore, a potential candidate for drag reduction of a future high-speed vehicle. The effect of the spike length, shape, spike nose configuration and angle-of-attack on the reduction of the drag is experimentally studied with use of hypersonic wind-tunnel at Mach 6. The effects of geometrical parameters of the spike and angle-of-attack on the aerodynamic coefficient are analysed using schlieren picture and measuring aerodynamic forces. These experim

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9

Mansour, Kamyar, and Mahdi Khorsandi. "The drag reduction in spherical spiked blunt body." Acta Astronautica 99 (June 2014): 92–98. http://dx.doi.org/10.1016/j.actaastro.2014.02.009.

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10

Ahmed, M. Y. M., and N. Qin. "Numerical investigation of aeroheating characteristics of spiked blunt bodies at Mach six flight conditions." Aeronautical Journal 115, no. 1168 (2011): 377–86. http://dx.doi.org/10.1017/s0001924000005893.

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AbstractAdding a small aerodisk at the tip of the spike was proved to improve the spike’s performance in reducing the drag. If designed properly, the aerodisk spike can offer better performance in drag reduction in comparison with the pointed sharp-nosed spike. However, the impact of the aerodisk on the aeroheating reduction capabilities of the spike was not investigated in detail before. In the present work, a numerical investigation of the aerothermodynamic characteristics of spiked blunt bodies at Mach 6 flight conditions is conducted. It was found that, adding an aerodisk degrades the perf

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