Navier-Stokes solution for a heat shield with and without a forward facing spike

Mehta, R. C.; Jayachandran, T.

doi:10.1016/s0045-7930(97)00011-x

Cited by 16 publications

(8 citation statements)

References 6 publications

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“…They observed in the experimental studies that the reliable estimating of aerodynamic effects of the spike can be made in conjunction with flow visualisation technique. Numerical simulations (16,17) have been performed to get the comparative studies of flowfield features over a payload fairing of a typical satellite launch vehicle with and without forward facing spike for freestream Mach number range 0⋅9 ≤ M ∞ ≤ 3⋅0 and freestream Reynolds number range of 33⋅35 × 10 6 /m ≤ Re ∞ ≤ 46⋅75 × 10 6 /m. are shown in Fig.…”

Section: Modelsmentioning

confidence: 99%

Experimental investigation on spiked body in hypersonic flow

2008

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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 experiments show that the aerodisk is superior to the aerospike. The aerodisk of appropriate length, diameter and nose configuration may have the capability for the drag reduction. The inclusion of an aero disk at the leading edge of the spike has an advantage for the drag reduction mechanism if it is at an angle-of-attack, however consideration to be given for increased moment resulting from the spike is required.

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Section: Modelsmentioning

confidence: 99%

Experimental investigation on spiked body in hypersonic flow

2008

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“…The fore and afterbody diameters of the heat shield [38][39] are 43.26 Â 10 À3 and 35 Â 10 À3 m, respectively, as shown in Figure 3(a). The semi-cone angle of the heat shield is 20 .…”

Section: Heat Shield With Forward Facing Spikementioning

confidence: 99%

Heat Transfer Analysis without and with Forward Facing Spike Attached to a Blunt Body at High Speed Flow

Mehta¹

2018

Heat Transfer - Models, Methods and Applications

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The present chapter deals with heat transfer analysis around unspiked and spiked bodies at high speeds. A spike attached to a blunt-nosed body drastically alters its flowfield and influences the aerodynamic heating in a high speed flow. The effect of spike length, shape and spike-nose configuration is numerically studied at zero angle of incidence. The numerical analysis describes overall flowfield features over without and with forward facing spike attached to a blunt body at high speed flow. The shock stand-off distance, sonic line, stagnation point velocity gradient and stagnation point heat flux are analyzed and compared with different aerodisk configurations. It is found that the hemispherical aerodisk experiences high wall heat flux as compared to the flat-faced aerodisk. Numerical and experimental studies reveal that the wall heat flux levels are decreased in the presence of the spikes and aerospike as compared to without attached spiked to the blunt-nose basic configuration.

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“…An aerospike can be used to measure angle-of-attack in the flight of a space vehicle (1) , to reduce aerodynamic drag in a satellite launch vehicle (2) and to make the stand-off distance for anti-tank projectiles (3) and re-entry capsules (4) . An aerodynamist encounters a variety of aerodynamic design problems associated to flow field characteristics around a spike attached with a blunt-body.…”

Section: Introductionmentioning

confidence: 99%

Investigation of aerodynamic coefficients at Mach 6 over conical, hemispherical and flat-face spiked body

2017

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A 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 leading edge of the spiked blunt body reveals different types of flow field features in the formation of a shock wave, shear layer, flow separation, re-circulation region and re-attachment shock. They are analysed with the help of schlieren pictures. The shock distance ahead of the hemisphere and the flat-face spike is compared with the analytical solution and is showing satisfactory agreement with the schlieren pictures. The influence of geometrical parameters of the spike, the shape of the spike tip and angle-of-attack on the aerodynamic coefficients are investigated by measuring aerodynamic forces in a hypersonic wind tunnel. It is found that a maximum reduction of drag of about 77% was found for hemisphere spike ofL/D= 2.0 at zero angle-of-attack. Consideration for compensation of increased pitching moment is required to stabilise the aerodynamic forces.

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Navier-Stokes solution for a heat shield with and without a forward facing spike

Cited by 16 publications

References 6 publications

Experimental investigation on spiked body in hypersonic flow

Experimental investigation on spiked body in hypersonic flow

Heat Transfer Analysis without and with Forward Facing Spike Attached to a Blunt Body at High Speed Flow

Investigation of aerodynamic coefficients at Mach 6 over conical, hemispherical and flat-face spiked body

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