Aerodynamic analysis of Commercial Experiment Transporter re-entry capsule

Wood, William A.; Gnoffo, Peter A.; Rault, D. F.

doi:10.2514/3.26814

Cited by 17 publications

(7 citation statements)

References 8 publications

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“…19 The upwind-biasedinviscid ux is constructedusing Roe's ux-difference-splitting 20 and Harten's entropy x 21 with second-ordercorrectionsbased on Yee's symmetric totalvariation-diminishingscheme. 22 LAURA is the same computational tool that has been used to describe the aerothermodynamics of blunt body shapes such as Mars Path nder, 23;24 Mars Microprobe, 25 Stardust, 26 and COMET, 27 and other vehiclessuch as X-33 (Ref. 28), HL-20 (Ref.…”

Section: Methodsmentioning

confidence: 99%

Computational Aeroheating Predictions for X-34

Kleb

Wood

Gnoffo

et al. 1999

Journal of Spacecraft and Rockets

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Section: Methodsmentioning

confidence: 99%

Computational Aeroheating Predictions for X-34

Kleb

Wood

Gnoffo

et al. 1999

Journal of Spacecraft and Rockets

Self Cite

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“…The flow is assumed to be laminar, which is consistent with the numerical simulation of [8,10,11,18]. The coefficient of molecular viscosity is computed according to Sutherland's law as…”

Section: ∂T ∂Rmentioning

confidence: 99%

“…A summary of developments relating to the base pressure prediction is reported in the review paper of Lamb and Oberkamf [9]. An aerodynamic analysis of the Commercial Experiment Transport (COMET) reentry capsule has been carried by Wood et al [10] solving the laminar thin layer Navier-Stokes equations flow solver LAURA. The flow field past blunt and short reentry capsule has been analyzed in order to understand the mechanism of the instability at supersonic speeds, which occurs due to decay of base pressure [11].…”

Section: Introductionmentioning

confidence: 99%

Numerical Computation of Heat Transfer on Reentry Capsules at Mach 5

Mehta

2023

joast

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The heat transfer over various reentry axisymmetric configurations is studied numerically by solving time-dependent compressible laminar Navier-Stokes equations. The governing fluid flow equations are disrectized in spatial coordinates employing a finite volume approach, which reduces the equations to semi-discretized ordinary differential equations. Temporal integration is performed using multi-stage Runge-Kutta time stepping scheme. A local time step is used to achieve steady state solution. The numerical simulation is carried out on a mono-block structured grid. The numerical computation is carried out for freestream Mach number of 5.0. The numerical scheme captures well all the essential flow field features such as bow shock wave, sonic line, expansion fan on the corner, recompression shock wave and recirculating flow in the base region. Comparisons of the flow field, surface pressure, skin friction coefficient and wall heat flux results are made between different configurations of the reentry capsules such as ARD (ESA’ s Atmospheric Reentry Demonstrator), CARINA, Apollo, Muses-C (Mu Science Engineering Satellite), OREX (Orbital Reentry Experiments) and Beagle-2. The effects of geometrical parameters of the different reentry capsules on surface pressure, skin friction coefficients and heat flux and forebody aerodynamic drag are analyzed. Base pressure is independent of the forebody shape of the reentry capsules. The effects of module geometry on the flow field are numerically analyzed which may be useful for optimization of the reentry capsule.

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“…A COMET blunt body capsule is an axisymmetric design with a spherical heat shield of 1.22 m radius. The frontal diameter and area are 1.32 m and 1.37 m 2 , respectively have been analysed using thin layer Navier-Stokes solver LAURA [7]. The geometrical detail of MUSES-C blunt body capsule is having nose radius of 50 mm, semi apex angle 45 deg, maximum diameter 100 mm, body length 50 mm and base configuration with 45 deg truncated cone [8].…”

Section: Introductionmentioning

confidence: 99%

Comparative Studies of Aerodynamic Drag Using Inviscid Flow Computation and Newtonian Method at High Speed

R. C. Mehta,

S.B. Tiwari

2023

joast

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The flow field analysis over various reentry configurations is studied numerically by solving time-dependent compressible Euler equations. The governing fluid flow equations are discretized in spatial coordinates employing a finite volume approach, which reduces the equations to semi-discretized ordinary differential equations. Temporal integration is performed using multi-stage Runge-Kutta time stepping scheme. A local time step is used to achieve steady state solution. The numerical computation is carried out for freestream Mach number of 10.0 and angle of attack of 10.0 degree. The flow features around the blunt body are characterized by a bow shock wave, expansion wave and base flow region. The numerical scheme captures all the flow field features well. Comparisons of the flow field and surface pressure distribution results are made between different configurations of the blunt body capsules such as ARD (ESA’ s Atmospheric Reentry Demonstrator), Apollo II, MUSES-C, OREX (Orbital Reentry Experiments) with and without shoulder curvature and spherically blunted cone with flare angle of 30 and 35 degree. The inviscid analysis takes into consideration centrifugal force and expansion fan at the shoulder of the reentry capsules. The effects of the capsule geometry on the flow field may be useful for optimization of the reentry capsule. The Newtonian flow assumptions are used to calculate forebody aerodynamic drag for various blunt- bodies in conjunction with the NISA software. A comparison between CFD and the Newtonian flow assumptions for various reentry modules are made, and comparison shows an agreement between them.

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Aerodynamic analysis of Commercial Experiment Transporter re-entry capsule

Cited by 17 publications

References 8 publications

Computational Aeroheating Predictions for X-34

Computational Aeroheating Predictions for X-34

Numerical Computation of Heat Transfer on Reentry Capsules at Mach 5

Comparative Studies of Aerodynamic Drag Using Inviscid Flow Computation and Newtonian Method at High Speed

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