Impulse facilities for the simulation of hypersonic radiating flows

At high flight speeds, radiation becomes an important component of aerodynamic heat transfer, and its coupling with the flow field can significantly change macroscopic features of the flow. As radiating flight conditions are typically encountered in reentry trajectories, the associated flight regimes range from rarefied to continuum, and may have many levels of thermal, chemical and electronic non-equilibrium.

[2]  Gregory J. Wilson,et al.  Computations of axisymmetric flows in hypersonic shock tubes , 1996 .

[3]  Halina Rubinsztein-Dunlop,et al.  Comparison of Experimental and Numerical Studies of Ionizing Flow over a Cylinder , 2003 .

[4]  T. Mcintyre,et al.  Simultaneous two-wavelength holographic interferometry in a superorbital expansion tube facility. , 1997, Applied optics.

[5]  Peter A. Jacobs.  MB_CNS: A Computer Program for the Simulation of Transient Compressible Flows , 1996 .

[6]  Peter A. Jacobs,et al.  Radiation measurements in nonreflected shock tunnels , 2006 .

[7]  Deepak Bose,et al.  Impact of Flowfield-Radiation Coupling on Aeroheating for Titan Aerocapture , 2005 .

[8]  Halina Rubinsztein-Dunlop,et al.  Experimental and numerical studies of ionizing flow in a super-orbital expansion tube , 2001 .

[9]  Peter A. Jacobs,et al.  Nozzle development for an expansion tunnel , 2005 .

[10]  Peter A. Jacobs,et al.  A simulation technique for radiating shock tube flows , 2009 .

[11]  Peter A. Jacobs,et al.  Expansion tube operating conditions for studying nonequilibrium radiation relevant to Titan Aerocapture , 2006 .

[12]  Peter A. Jacobs,et al.  Superorbital expansion tube operation: Estimates of flow conditions via numerical simulation , 2005 .

[13]  Rowan J. Gollan,et al.  Computational Modelling of High-Temperature Gas Effects with Application to Hypersonic Flows , 2008 .

[14]  Bianca R. Capra,et al.  Radiative and Total Heat Transfer Measurements to a Titan Explorer Model , 2012 .

[15]  Peter A. Jacobs,et al.  Simulation of CO2-N2 Expansion Tunnel Flows for the Study of Radiating Shock Layers , 2008 .

[16]  Bianca R. Capra.  Aerothermodynamic Simulation of Subscale models of the FIRE II and Titan Explorer Vehicles in Expansion Tubes , 2007 .

[17]  Bianca R. Capra,et al.  Subscale testing of the Fire II vehicle in a superorbital expansion tube , 2004 .

[18]  Bianca R. Capra,et al.  New gauge design to measure radiative heat transfer to a Titan aerocapture vehicle in expansion tubes , 2005 .

[19]  David W. Bogdanoff,et al.  Modeling and Experimental Validation of CN Radiation Behind a Strong Shock Wave , 2005 .

[20]  P. Gnoffo.  Planetary-Entry Gas Dynamics , 1999 .

[21]  R. G. Morgan,et al.  The Superorbital Expansion Tube concept, experiment and analysis , 1994, Aeronautical Journal.

[22]  Harold Mirels,et al.  TEST TIME IN LOW PRESSURE SHOCK TUBES , 1963 .

[23]  Peter A. Jacobs.  Shock Tube Modelling With L1d , 1998 .