Numerical Investigation of Hypersonic Double-Cone Flow


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Hypersonic flow of Mach number 8 past a 25°-50° double cone geometry is numerically simulated at ReD=4.8E5. Complicated flow structures, including Type V shock-shock interaction, shock-boundary layer interaction, separation and reattachment at the corner are presented and discussed. The surface pressure and heat transfer rate distributions are also calculated and compared with the experimental data. Results show that both the 2nd order MUSCL and 5th order WENO could accurately reproduce the shock structures, while the higher order scheme could predict a more accurate size of separation zone. Generally, the size of the separation zone is underestimated with an overvalued pressure distribution after reattachment employing the full turbulent models. On the other hand, transition induced by the reattachment shock has been calculated using transition model and the results of pressure peak and the size of separation zone show good agreement with the experimental measurements.



Edited by:

Amanda Wu




W. X. Kong et al., "Numerical Investigation of Hypersonic Double-Cone Flow", Applied Mechanics and Materials, Vol. 232, pp. 240-245, 2012

Online since:

November 2012




[1] P. Gnoffo, CFD Validation Studies for Hypersonic Flow Prediction. AIAA 2001-1025. (2001).

[2] J. Harvey and M. Holden, et al., Code Validation Study of Laminar Shock/Boundary Layer and Shock/Shock Interactions in Hyper-sonic Flow Part B: Comparison with Navier-Stokes and DSMC Solutions. AIAA 2001-1031. (2001).


[3] G. Candler and I. Nompelis, CFD Validation for Hypersonic Flight: Hypersonic Double-Cone Flow Simulations. AIAA 2002-0581. (2002).


[4] M. Holden, T. Wadhams and G. Candler, et al., Measurements in Regions of Low Density Laminar Shock Wave/Boundary Layer Interacition in Hypervelocity Flows and Comparison with Navier-Stokes Predictions. AIAA 2003-1131. (2003).


[5] M. Holden and T. Wadhams, A Review of Experimental Studies for DSMC and Navier-Stocks Code Validation in Laminar Regions of Shock/Shock and Shock/Boundary Layer Interaction Including Real Gad Effects in Hypervelocity Flows. AIAA 2003-3641. (2003).


[6] M-C. Drugguet, et al., Effect of Numerics on Navier-Stokes Computations of Hypersonic Double-Cone Flows. AIAA Journal. 43(3) (2005) 616-623.


[7] D. Gaitonde, P. Canupp, et al., Heat Transfer Predictions in a Laminar Hypersonic Viscous/Inviscid Interaction. Journal of Thermo-physics and Heat Transfer. 16(4) (2002) 481-489.


[8] J. Yu, C. Yan and Z. Jiang, A High Resolution Low Dissipation Hybrid Scheme for Compressible Flows. Chinese Journal of Aeronautics. 24(4) (2011) 417-424.


[9] P. Spalart and S. Allmaras, A One-Equation Turbulence Model for Aerodynamic Flows. AIAA 1992-0439. (1992).


[10] F. Meter, Zonal Two Equation k-w Turbulence Models for Aerodynamic Flows. AIAA 1993-2906. (1993).

[11] R. Langtry and F. Menter, Correlation-Based Transition Modeling for Unstructured Parallelized Computational Fluid Dynamics Codes. AIAA Journal. 47(12) (2009) 2894-2906.


[12] M. Baumgartner, A. Smits, T. Nau and C. Rowley, A New Hypersonic Boundary Layer Facility. AIAA 1995-0787. (1995).

[13] M. Wright, J. Olejniczak, G. Candler et al., Numerical and experimental investigation of double-cone shock interactions. AIAA-1997-0063. (1997).