Transition Within Leeward Plane of Axisymmetric Bodies at Incidence in Supersonic Flow

Boundary layer transition along the leeward symmetry plane of axisymmetric bodies at nonzero angle of attack in supersonic flow was investigated experimentally and numerically as part of joint research between the Japan Aerospace Exploration Agency (JAXA) and National Aeronautics and Space Administration (NASA). Transition over four axisymmetric bodies (namely, Sears-Haack body, semi-Sears-Haack body, straight cone and flared cone) with different axial pressure gradients was measured in two different facilities with different unit Reynolds numbers. The semi-Sears-Haack body and flared cone were designed at JAXA to broaden the range of axial pressure distributions. For a body shape with an adverse pressure gradient (i.e., flared cone), the experimentally measured transition patterns show an earlier transition location along the leeward symmetry plane in comparison with the neighboring azimuthal locations. For nearly zero pressure gradient (i.e., straight cone), this feature is only observed at the larger unit Reynolds number. Later transition along the leeward plane was observed for the remaining two body shapes with a favorable pressure gradient. The observed transition patterns are only partially consistent with the numerical predictions based on linear stability analysis. Additional measurements are used in conjunction with the stability computations to explore the phenomenon of leeward line transition and the underlying transition mechanism in further detail.

[1]  Chau-Lyan Chang.  LASTRAC.3d: Transition Prediction in 3D Boundary Layers , 2004 .

[2]  Lewis R. Owens,et al.  Off-Body Boundary-Layer Measurement Techniques Development for Supersonic Low-Disturbance Flows , 2011 .

[3]  W. Cook,et al.  Reduction of data from thin-film heat-transfer gages - A concise numerical technique. , 1966 .

[4]  T. Lin,et al.  Viscous flow over a cone at moderate incidence. Part 2. Supersonic boundary layer , 1973, Journal of Fluid Mechanics.

[5]  J. A. Masad,et al.  Three-dimensional boundary-layer transition on a swept wing at Mach 3.5 , 1995 .

[6]  I Kroo,et al.  VKI lecture series on Innovative Configurations and Advanced Concepts for Future Civil Aircraft , 2005 .

[7]  N. S. Dougherty,et al.  Boundary-Layer Transition Correlation on a Slender Cone in Wind Tunnels and Flight for Indications of Flow Quality , 1982 .

[8]  William Saric,et al.  Laminar Flow Control on a Swept Wing with Distributed Roughness , 2008 .

[9]  Graham V. Candler,et al.  Transition Analysis for the HIFiRE-5 Vehicle , 2009 .

[10]  Jeffery A. White,et al.  Algorithmic Enhancements to the VULCAN Navier-Stokes Solver , 2003 .

[11]  H. Ishikawa,et al.  THREE DIMENSIONAL BOUNDARY LAYER TRANSITION ANALYSIS IN SUPERSONIC FLOW USING A NAVIER-STOKES CODE , 2004 .

[12]  D. Nestler.  Hypersonic boundary layers , 1969 .

[13]  T. Lin,et al.  Viscous flow over a cone at moderate incidence—I , 1973 .

[14]  Takashi Kohno,et al.  Pressure fluctuation measurements in the NAL 0.2-m supersonic wind tunnel , 1998 .

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

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

[17]  Kazuomi Yamamoto,et al.  A Common CFD Platform UPACS , 2000, ISHPC.

[18]  R. King,et al.  Three-dimensional boundary-layer transition on a cone at Mach 3.5 , 1992 .

[19]  Roger L. Kimmel,et al.  Aerothermodynamic Characteristics of Boundary Layer Transition and Trip Effectiveness of the HIFiRE Flight 5 Vehicle , 2009 .

[20]  I. E. Beckwith,et al.  Boundary-layer transition on a cone and flat plate at Mach 3.5 , 1989 .

[21]  Jeffery A. White,et al.  Computational Investigation of Supersonic Boundary Layer Transition Over Canonical Fuselage Nose Configurations , 2012 .