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Abstract
The flowfield over a sharp-tipped double cone axisymmetric configuration is carried out by solving time dependent axisymmetric laminar compressible Navier-Stokes equations for freestream Mach number range of 2.0 - 6.0. The fluid dynamics equations are discretized in spatial coordinates using integral formulation in conjunction with finite volume method which reduces the governing equations to semi-discretized ordinary differential equations. Temporal integration is performed employing multistage Runge-Kutta time-stepping scheme. A local time step is used to achieve steady-state solution. The numerical computation is carried out on a mono-block with structured grids. The flowfield features over the sharp-tipped double cone configuration such as conical shock wave, separation region, separation and reattachment shock wave and bow shock wave in the cone region, expansion fan, and recirculation flow in the base region are well captured at Mach number 3 and 6 which are identical to the Edney VI type shock interaction. The velocity vector, Mach contours plots and variations of surface pressure coefficient along the sharp-tipped double cone configuration are analyzed at various Mach numbers. The fore-body aerodynamic drag is calculated employing computed pressure distribution. The paper presents the influence of the freestream Mach number on the flows with shock interactions over the sharp-tipped double cone geometry.
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References
- Mehta, R. C., "High Speed Field Analysis for Satellite Launch Vehicle and Reentry Capsule", Journal of Magneto-hydrodynamics, Plasma and Space Research, Vol.15, No.1, 2010, pp.53-100.
- Chanetz, B., Benay, R., Bousquet, J.-M., Bur, R., Oswald, J., Pot, T., Grasso, F and Moss, J., "Experimental and Numerical Study of the Laminar Separation in Hypersonic Flow", Aerospace Science and Technology, Vol.10, No.3, 1998, pp.205-218.
- MacLean, M., Wadhams, T., Holden, M and Candler, G., "Integration of CFD and Experiments in the Cubrc Lens Shock Tunnel Facilities to Understand the Physics of Hypersonic and Hypervelocity Flows", 4th Symposium on Integrating CFD and Experiments in Aerodynamics von Karman Institute, Rhode-Saint-Gense, Belgium, 14-16 September 2009.
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- Nagata, Y., Yamada, K and Abe, T., "Hypersonic Double-Cone Flow with Applied Magnetic Field", Journal of Spacecraft and Rockets, Vol.50, No.5, 2013, pp.981-991.
- Prabhu, R., Stewart, J and Theraja, R., "Shock Interaction Studies on a Circular Cylinder at Mach 16", AIAA Paper 90-0606, 1990.
- Gaitonde, D and Shang, J., "Accuracy of Flux Split Algorithms in High Speed Viscous Flows", AIAA Journal, Vol.31, No.7, 1993, pp.1215-1221.
- Peyret, R and Vivind, H., Computational Methods for Fluid Flow, Springer-Verlag, 1993, pp.109-111.
- Jameson, A., Schmidt, W and Turkel, E., "Numerical Solution of Euler Equations by Finite Volume Methods Using Runge-Kutta Time Stepping Schemes", AIAA Paper 81-1259, 1981.
- Mehta, R. C., "Flow Field Simulation Over Reentry Modules at High Speed", Journal of Aerospace Sciences and Technologies, Vol.62, No.1, February, 2010, pp.55-65.
- Mehta, R. C., "Numerical Simulation of the Flow Field Over Conical, Disc and Flat Spiked Body at Mach 6", The Aeronautical Journal of the Royal Aeronautical Society, Vol.114, No.1154, 2010, pp.225-236.
- Mehta, R. C., "Block Structured Finite Element Grid Generation Method", Computational Fluid Dynamics Journal, Vol.18, No.2, 2011.
- Shang, J. S., "Numerical Simulation of Wing-fuselage Aerodynamic Interaction", AIAA Journal, Vol.22, No.10, 1984, pp.1345-1353.
- Lunev, V., Real Gas Flows with High Velocities, CRC Press, USA, 2009, pp.247-249.
- Mehta, R. C., "High Speed Flow over Spiked Blunt Body and Representation of Shock Polar", Computational Fluid Dynamics Journal, Vol.18, No.3, 2009, pp.22-30.
- Mehta, R. C., "Computations of Flow Field Over Reentry Modules at High Speed", Computational Simulations and Applications, Edited by J. Zho, INTECH Open, Croatia, 2011, pp.347-372.
- Edney, B., "Anomalous Heat Transfer and Pressure Distributions on Blunt Bodies at Hypersonic Speeds in the Presence of an Impinging Shock", FFA Report 115, 1968.
- Hirschel, E. H., Basics of Aerothermodynamics, Springer (India) Private Limited, New Delhi, 2008.
References
Mehta, R. C., "High Speed Field Analysis for Satellite Launch Vehicle and Reentry Capsule", Journal of Magneto-hydrodynamics, Plasma and Space Research, Vol.15, No.1, 2010, pp.53-100.
Chanetz, B., Benay, R., Bousquet, J.-M., Bur, R., Oswald, J., Pot, T., Grasso, F and Moss, J., "Experimental and Numerical Study of the Laminar Separation in Hypersonic Flow", Aerospace Science and Technology, Vol.10, No.3, 1998, pp.205-218.
MacLean, M., Wadhams, T., Holden, M and Candler, G., "Integration of CFD and Experiments in the Cubrc Lens Shock Tunnel Facilities to Understand the Physics of Hypersonic and Hypervelocity Flows", 4th Symposium on Integrating CFD and Experiments in Aerodynamics von Karman Institute, Rhode-Saint-Gense, Belgium, 14-16 September 2009.
Wright, M. J., Sinha, K., Olejniczak, J., Candler, G. V., Magruder, T. D and Smits, A. J., "Numerical and Experimental Investigation of Double-Cone Shock Interactions", AIAA Journal, Vol.38, No.12, December, 2000, pp.2268-2276.
Nagata, Y., Yamada, K and Abe, T., "Hypersonic Double-Cone Flow with Applied Magnetic Field", Journal of Spacecraft and Rockets, Vol.50, No.5, 2013, pp.981-991.
Prabhu, R., Stewart, J and Theraja, R., "Shock Interaction Studies on a Circular Cylinder at Mach 16", AIAA Paper 90-0606, 1990.
Gaitonde, D and Shang, J., "Accuracy of Flux Split Algorithms in High Speed Viscous Flows", AIAA Journal, Vol.31, No.7, 1993, pp.1215-1221.
Peyret, R and Vivind, H., Computational Methods for Fluid Flow, Springer-Verlag, 1993, pp.109-111.
Jameson, A., Schmidt, W and Turkel, E., "Numerical Solution of Euler Equations by Finite Volume Methods Using Runge-Kutta Time Stepping Schemes", AIAA Paper 81-1259, 1981.
Mehta, R. C., "Flow Field Simulation Over Reentry Modules at High Speed", Journal of Aerospace Sciences and Technologies, Vol.62, No.1, February, 2010, pp.55-65.
Mehta, R. C., "Numerical Simulation of the Flow Field Over Conical, Disc and Flat Spiked Body at Mach 6", The Aeronautical Journal of the Royal Aeronautical Society, Vol.114, No.1154, 2010, pp.225-236.
Mehta, R. C., "Block Structured Finite Element Grid Generation Method", Computational Fluid Dynamics Journal, Vol.18, No.2, 2011.
Shang, J. S., "Numerical Simulation of Wing-fuselage Aerodynamic Interaction", AIAA Journal, Vol.22, No.10, 1984, pp.1345-1353.
Lunev, V., Real Gas Flows with High Velocities, CRC Press, USA, 2009, pp.247-249.
Mehta, R. C., "High Speed Flow over Spiked Blunt Body and Representation of Shock Polar", Computational Fluid Dynamics Journal, Vol.18, No.3, 2009, pp.22-30.
Mehta, R. C., "Computations of Flow Field Over Reentry Modules at High Speed", Computational Simulations and Applications, Edited by J. Zho, INTECH Open, Croatia, 2011, pp.347-372.
Edney, B., "Anomalous Heat Transfer and Pressure Distributions on Blunt Bodies at Hypersonic Speeds in the Presence of an Impinging Shock", FFA Report 115, 1968.
Hirschel, E. H., Basics of Aerothermodynamics, Springer (India) Private Limited, New Delhi, 2008.