Laminar-Turbulent Transition in a Mach 8 Elliptic Cone Flow

To examine the influence of crossflow on transition in a hypersonic boundary layer, an experimental and computational study was made of a Mach 8 flow over a sharp-nosed elliptic cone of 2:1 cross section. Extensive flow visualization was carried out experimentally, including schlieren photography and surface oil-flow visualization. Mean pressure and heat flux were measured at the wall of the wind-tunnel model. For comparison with the experiments, a computation of the basic state flow was carried out using the parabolized Navier-Stokes equations. The basic state laminar flow was found to be relatively complex, with highly skewed velocity profiles and a pair of symmetric vortices on the top centerline of the cone. Transition in the elliptic cone flow was found to be significantly different than transition in hypersonic flow over planar and axisymmetric configurations, which is driven by the second mode instability. In the elliptic cone flow the transition front was nonuniform, with early transition near the top centerline and delayed transition near the leading edge. Rope waves were observed on both the leading edge and top centerline; unusual elongated streaks were observed on the top centerline

[1]  R. Kimmel,et al.  Disturbance evolution and breakdown to turbulence in a hypersonic boundary layer - Instantaneous structure , 1997 .

[2]  M. Malik,et al.  Waves produced from a harmonic point source in a supersonic boundary-layer flow , 1992, Journal of Fluid Mechanics.

[3]  M. Malik.  Prediction and control of transition in supersonic and hypersonic boundary layers , 1989 .

[4]  M. Malik,et al.  Instability and transition in three-dimensional supersonic boundary layers , 1992 .

[5]  R. G. Voigt,et al.  Instability and Transition , 1990 .

[6]  Roger L. Kimmel,et al.  Three-Dimensional Hypersonic Laminar Boundary-Layer Computations for Transition Experiment Design , 1997 .

[7]  Ndaona Chokani,et al.  Effect of angle of attack on hypersonic boundary-layer stability , 1997 .

[8]  A H Boudreau.  Performance and Operational Characteristics of AEDC/VKF Tunnels A, B, and C , 1981 .

[9]  J Donaldson,et al.  A review of free-stream flow fluctuation and steady-state flow quality measurements in the AEDC/VKF Supersonic Tunnel A and Hypersonic Tunnel B , 1995 .

[10]  Ndaona Chokani,et al.  Effect of Angle of Attack on Hypersonic , 1997 .

[11]  R. Kimmel,et al.  Space-time correlation measurements in a hypersonic transitional boundary layer , 1995 .

[12]  R. Kimmel,et al.  On hypersonic boundary-layer stability , 1992 .

[13]  M. Holden,et al.  Attachment line transition studies on swept cylindrical leading edges at Mach numbers from 10 to 12 , 1995 .

[14]  Ardeshir Hanifi,et al.  An experimental and theoretical investigation of instabilities in hypersonic flat plate boundary layer flow , 1995 .

[15]  Xiaolin Zhong,et al.  Direct numerical simulation of hypersonic boundary-layer transition over blunt leading edges. II - Receptivity to sound , 1997 .

[16]  Helen L. Reed,et al.  Transition correlations in three-dimensional boundary layers , 1994 .

[17]  H. Reed,et al.  Stability of three‐dimensional supersonic boundary layers , 1991 .

[18]  Ndaona Chokani,et al.  Boundary-layer stability measurements in a hypersonic quiet tunnel , 1996 .

[19]  Helen L. Reed,et al.  Use of transition correlations for three-dimensional boundary layers within hypersonic flows , 1995 .

[20]  William S. Saric,et al.  Stability of three-dimensional boundary layers , 1989 .

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

[22]  D. Chaussee,et al.  An upwind algorithm for the parabolized Navier-Stokes equations , 1986 .

[23]  R. Kimmel,et al.  Disturbance evolution and breakdown to turbulence in a hypersonic boundary layer - Ensemble-averaged structure , 1997 .

[24]  Anthony Demetriades,et al.  An experiment on the stability of hypersonic laminar boundary layers , 1960, Journal of Fluid Mechanics.

[25]  Leslie M Mack.  Boundary-Layer Stability Analysis for Sharp Cones at Zero Angle-of-Attack , 1986 .

[26]  Alexander J. Smits,et al.  Turbulent Shear Layers in Supersonic Flow , 1996 .

[27]  Roger L. Kimmel,et al.  The Effect of Pressure Gradients on Transition Zone Length in Hypersonic Boundary Layers. , 1997 .

[28]  J. Anderson,et al.  Hypersonic and High-Temperature Gas Dynamics , 2019 .

[29]  C. David Pruett,et al.  Spatial direct numerical simulation of high-speed boundary-layer flows Part II: Transition on a cone in Mach 8 flow , 1995 .

[30]  Roger L. Kimmel,et al.  Traveling Instability Waves in a Mach 8 Flow over an Elliptic Cone , 2000 .

[31]  L. Mack.  On the inviscid acoustic-mode instability of supersonic shear flows , 1990, Theoretical and Computational Fluid Dynamics.

[32]  Kenneth F. Stetson,et al.  Laminar boundary layer stability experiments on a cone at Mach 8. III - Sharp cone at angle of attack , 1985 .

[33]  L. Mack.  Linear Stability Theory and the Problem of Supersonic Boundary- Layer Transition , 1975 .

[34]  J. Kendall.  Wind Tunnel Experiments Relating to Supersonic and Hypersonic Boundary-Layer Transition , 1974 .