Blunted cone–flare in hypersonic flow

Savino, Raffaele; Paterna, D.

doi:10.1016/j.compfluid.2004.05.012

Cited by 22 publications

(16 citation statements)

References 9 publications

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“…In order to assess the accuracy and reliability of the selected solver, the hypersonic flow field around a blunted cone-flare was simulated and the results were compared with the available experimental results for the same problem (R Savino. et al [1]). Figure 1 shows the axi-symmetric blunted cone-flare with the boundary conditions and inlet conditions that was set up in fluent.…”

Section: Solver Validationmentioning

confidence: 93%

Numerical study of heat flux developed on an aero-spike structure in hypersonic flow

Soori¹

2015

2015 IEEE Aerospace Conference

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Several past studies have analyzed the topic of blunt body aerodynamics, and have gone in depth, detailing the reduction in drag caused by the effect of aero-spike structures that are attached to blunt shaped bodies in hypersonic flow, like re-entry capsules and missiles. The results have showed the formation of a bow shock in front of the spike, which creates a re-circulation region in front of the main body thus protecting it from the oncoming flow. Even though this leads to a reduction in drag on the main body, the heat flux generated on the surface of the aero-spike is immense. This study has been carried out to understand the flow properties over the aero spike in detail and to arrive at the best possible configuration that could be put to practical use for missiles and re-entry vehicles and manages to keep the heat flux on both the body as well as the aero-spike to a minimum. Initial studies were carried out on a blunted cone-flare in hypersonic flow at Mach No = 6 (Temperature = 234 K; Pressure = 1064 Pa; Altitude = 100km) to clearly grasp the flow physics at high Mach numbers and also to validate the Computational Fluid Dynamics (CFD) solver used. The results obtained were encouraging, with good agreement with the available experimental data. A test model based on Apollo re-entry capsule was designed, with a cylindrical aero-spike attached to its front. Computational analysis was done for this configuration, with the commercially available Fluent CFD software. The initial results found good similarity with the past studies, showing a drag reduction of more than 60% when the aero-spike is attached to the capsule. The dimensions of the aero-spike cylinder were varied uniformly as a function of the radius of the capsule. This showed some interesting results, with the drag decreasing gradually up to a minimum value as the spike radius is increased, and then increasing as the radius is increased further. This radius was kept constant and the length of the spike was varied next, which yielded similar uniform results for drag reduction. It was clear that the variation in the dimensions of the aero-spike was modifying the area of the flow re-circulation region in front of the capsule which in turn leads to a variation in drag. The flow separation point on the aero-spike was plotted as a function of the spike radius, and this showed a linear variation. When the aero spike is attached, the heat flux generated on the capsule decreases by about 25% of the initial value. The heat flux generated on the entire aero-spike structure is obtained. As expected, the maximum heat flux is developed at the front blunt body of the spike and then varies along the surface of the spike. The boundary layer thickness along the length of the spike is calculated using the available CFD tools. It is evident that for different aero-spike dimensions, the boundary layer thickness values at the various locations differ significantly for 978-1-4799-5380-6/151$31.00 ©2015 IEEE the same flow properties. By adjusting the spike geometry, it is po...

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Section: Solver Validationmentioning

confidence: 93%

Numerical study of heat flux developed on an aero-spike structure in hypersonic flow

Soori¹

2015

2015 IEEE Aerospace Conference

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“…A spherical blunt-cone/flare delft aerospace recovery test (DART) configuration is numerically analyzed by Otten [48] solving a laminar Navier-Stokes equations. Numerical analysis over blunted cone flare has been carried out at Mach 6 by Savino et al [49]. Barnhardt [50] has carried out numerical simulation of flowfield in the wake region of a reentry vehicle at high speeds.…”

Section: Review Of the Base Pressure Datamentioning

confidence: 99%

Numerical Simulation of Base Pressure and Drag of Space Reentry Capsules at High Speed

Mehta¹

2019

Hypersonic Vehicles - Past, Present and Future Developments

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The numerical simulations over several reentry vehicles are carried out by solving time-dependent compressible laminar axisymmetric Navier-Stokes equations for Mach 1.2-6.0. The fluid dynamics equations are discretized in spatial coordinates using integral formulation in conjunction with a finite volume method which reduce to semi-discretized ordinary differential equations. A local time-step is used to achieve steady-state solution. The numerical computation is carried out on a single-block structured computational grid. The flowfield features over the reentry vehicle such as formation of a bow shock wave ahead of the fore-body, expansion fan on the shoulder, and recirculation zone in the base region are well captured in the numerical simulations. Lower pressure acting on the base of the reentry capsule acts as base drag. The base drag coefficient based on maximum cross-section of the reentry capsule must satisfy inequality. The base drag coefficient is a function of several geometrical parameters of the fore-body and back-shell of reentry capsule, boundary layer, formation of free-shear layer in the wake region and freestream Mach number. The purpose of this chapter is to numerically evaluate and tabulate the base pressure and the base drag coefficients of various reentry space capsules at zero angle of incidence.Keywords: aerodynamic, base drag, CFD, high speed flow, viscous flow, reentry vehicle, shock wave Present and Future Developments Numerical Simulation of Base Pressure and Drag of Space Reentry Capsules at High Speed DOI: http://dx.doi.org/10.5772/intechopen.83651 the axisymmetric laminar compressible Navier-Stokes equations on a single-block structured grid, i.e., the number of grid points in the radial direction in each zone of the computational region is same. Surface pressure variations over the vehicles are computed which reveal a systematic understanding of the flow features over the capsule at high speeds. It also reveals the effect of geometrical parameters on aerodynamic base drag coefficient. The unsteady flow characteristics of the OREX and the Beagle-2 are analyzed in Ref. [28].

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“…A Newton-Raphson iterative algorithm has been developed to implement this boundary condition in the code, assuming a constant value of 0.8 for emissivity. Details on implementation of the radiative equilibrium boundary condition can be found in [17]. Fig.…”

Section: Boundary Layer Thermal Protection Of the Vehicle Structurementioning

confidence: 99%

A low risk reentry: looking backward to step forward

Monti

Paterna

2006

Aerospace Science and Technology

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Blunted cone–flare in hypersonic flow

Cited by 22 publications

References 9 publications

Numerical study of heat flux developed on an aero-spike structure in hypersonic flow

Numerical study of heat flux developed on an aero-spike structure in hypersonic flow

Numerical Simulation of Base Pressure and Drag of Space Reentry Capsules at High Speed

A low risk reentry: looking backward to step forward

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