Experimental Investigation of High-Enthalpy Effects on Attachment-Line Boundary-Layer Transition

A series of experiments was performed on high-enthalpy effects on hypersonic boundary-layer transition using nitrogen, air, and carbon dioxideas test gases in the T5 hypervelocity shock tunnel. Previous experiments on a sharp cone showed significant high enthalpy effects. This series concerns the attachment line boundary layer on swept cylinders with sweep angles of 60 and 45 deg. The observed trend of transition Reynolds number with enthalpy, which is found to be similar to that in the cone results, shows strong transition delay at the larger sweep angle for carbon dioxide, whereas no significant effect is observed in nitrogen and air. The acoustic wave absorption rate due to relaxation shows a quite similar trend in enthalpy dependence to transition Reynolds number for the carbon dioxide case. This suggests that the dominant effect in delaying transition in the case is vibrational relaxation. The comparisons between the magnitude of the strongest amplification rate from an inviscid linear stability analysis and the absorption rate due to relaxation show that they are of the same order of magnitude for carbon dioxide and that absorption is not significant for nitrogen or air, which supports the stated understanding of the effect of relaxation on transition.

[1]  Claudio Bruno,et al.  Real gas effects , 1989 .

[2]  Taoting Hsu,et al.  Viscous hypersonic flow: by William H. Dorrance. 334 pages, diagrams, 6 × 9 in. New York, McGraw-Hill Book Co., Inc., 1962. Price, $12.50 , 1963 .

[3]  D. Poll,et al.  The development of intermittent turbulence on a swept attachment line including the effects of compressibility , 1983 .

[4]  E. Benard,et al.  Influence of roughness on attachment line boundary layer transition in hypersonic flow , 1997 .

[5]  R. G. Morgan,et al.  Transition of compressible high enthalpy boundary layer flow over a flat plate , 1994, The Aeronautical Journal (1968).

[6]  C. Wilke.  A Viscosity Equation for Gas Mixtures , 1950 .

[7]  H. Tong,et al.  Nonequilibrium chemistry boundary layer integral matrix procedure , 1973 .

[8]  T. Teichmann,et al.  Introduction to physical gas dynamics , 1965 .

[9]  M. Malik,et al.  REAL GAS EFFECTS ON HYPERSONIC BOUNDARY-LAYER STABILITY , 1991 .

[10]  R. Reid,et al.  The Properties of Gases and Liquids , 1977 .

[11]  I. E. Beckwith,et al.  Compressible laminar boundary layer over a yawed infinite cylinder with heat transfer and arbitrary Prandtl number , 1957 .

[12]  Hans G. Hornung,et al.  Transition on a slender cone in hypervelocity flow , 1997 .

[13]  Kenneth F. Stetson,et al.  Hypersonic Boundary-Layer Transition , 1992 .

[14]  E. R. V. Driest,et al.  Calculation of the Stability of the Laminar Boundary Layer in a Compressible Fluid on a Flat Plate with Heat Transfer , 1952 .

[15]  A. Rasheed.  Passive hypervelocity boundary layer control using an acoustically absortive surface , 2001 .

[16]  J. F. Clarke,et al.  The Dynamics of Real Gases , 1964 .

[17]  J. Davis.  High-enthalpy shock/boundary-layer interaction on a double wedge , 1999 .

[18]  Yih-Kanq Chen,et al.  Navier-Stokes solutions with surface catalysis for Martian atmospheric entry , 1992 .

[19]  Hans G. Hornung,et al.  ENTHALPY EFFECTS ON HYPERVELOCITY BOUNDARY-LAYER TRANSITION : GROUND TEST AND FLIGHT DATA , 1997 .

[20]  H. Reed,et al.  Linear disturbances in hypersonic, chemically reacting shock layers , 1994 .

[21]  Steven P. Schneider,et al.  Effects of High-Speed Tunnel Noise on Laminar-Turbulent Transition , 2000 .

[22]  I. E. Beckwith,et al.  Local Heat Transfer and Recovery Temperatures on a Yawed Cylinder at a Mach Number of 4.15 and High Reynolds Numbers , 1961 .

[23]  F. Bertolotti.  The influence of rotational and vibrational energy relaxation on boundary-layer stability , 1998, Journal of Fluid Mechanics.

[24]  Trevor G. Seipp,et al.  Numerical study of hypersonic reacting boundary layer transition on cones , 1998 .

[25]  I. E. Beckwith,et al.  Transition on swept leading edges at Mach 3.5 , 1987 .