Aerothermal Design for the HIFiRE-1 Flight Vehicle

This paper summarizes aerothermal computations and ground tests of the Hypersonic International Flight Research and Experimentation (HIFiRE) 1 flight vehicle. The HIFiRE1 vehicle incorporates boundary-layer transition and shock-boundary-layer interaction experiments. The test geometry consists of a 7-degree half angle cone with 2.5 mm nose radius followed by a cylinder and flare. The experiment test window is between Mach 7.2 and 7.4. Results of ground testing show good agreement between laminar CFD and ground test data for this configuration at zero angle of attack. Reynolds-averaged Navier Stokes (RANS) calculations for the shock-boundary-layer interaction are highly-sensitive to details of the turbulence modeling. Fine-tuning of coefficients in the turbulence models can improve agreement of the computations with experiment, but the generality of these modifications remains an open issue. RANS prediction of turbulent heating downstream of transition also requires careful attention to turbulence modeling for best results. Boundarylayer transition wind tunnel results at zero angle of attack are well-correlated with linear parabolized stability equation computations.

[1]  Miguel R. Visbal,et al.  High-Order Schemes for Navier-Stokes Equations: Algorithm and Implementation Into FDL3DI , 1998 .

[2]  Roger L. Kimmel,et al.  Aerothermodynamic Testing and Boundary-Layer Trip Sizing of the HIFiRE Flight 1 Vehicle , 2008 .

[3]  Steven P. Schneider,et al.  The Development of Hypersonic Quiet Tunnels , 2007 .

[4]  K. Stetson.  Nosetip bluntness effects on cone frustum boundary layer transition in hypersonic flow , 1983 .

[5]  Graham V. Candler,et al.  Boundary-Layer Stability Analysis of the Hypersonic International Flight Research Transition Experiments , 2008 .

[6]  Graham V. Candler,et al.  Boundary Layer Stability Calculations of the HIFiRE Flight 1 Vehicle in the LaRC 20-Inch Mach 6 Air Tunnel , 2008 .

[7]  Mujeeb R. Malik,et al.  Hypersonic Flight Transition Data Analysis Using Parabolized Stability Equations with Chemistry Effects , 2003 .

[8]  C. Hoke,et al.  Aerodynamic Analysis of Complex Missile Configurations Using AVUS (Air Vehicles Unstructured Solver) , 2004 .

[9]  Gary S. Settles,et al.  Incipient Separation of a Supersonic Turbulent Boundary Layer at High Reynolds Numbers , 1976 .

[10]  Katya M. Casper,et al.  Effect of freestream noise on roughness-induced transition at mach 6 , 2008 .

[11]  Frank T. Smith,et al.  Boundary-Layer Separation , 1987 .

[12]  G. Candler,et al.  Hypersonic Boundary Layer Stability Analysis Using PSE-Chem , 2005 .

[13]  M. Holden,et al.  Shock Wave Turbulent Boundary Layer Interaction in Hypersonic Flow , 1972 .

[14]  Graham V. Candler,et al.  Analysis of laminar-turbulent transition in hypersonic flight using PSE-chem , 2006 .

[15]  Timothy Wadhams,et al.  A Computational Analysis of Ground Test Studies of the HIFiRE-1 Transition Experiment , 2008 .

[16]  K. Kontis,et al.  Incipient separation on flared bodies at hypersonic speeds , 1999, The Aeronautical Journal (1968).

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

[18]  S. C. Praharaj,et al.  MINIVER upgrade for the AVID system. Volume 1: LANMIN user's manual , 1983 .

[19]  D. Frew,et al.  A study of incipient separation limits for shock-induced boundary layer separation for Mach 6 high Reynolds flow , 1993 .

[20]  T Wadhams,et al.  Pre-Flight Ground Testing of the Full-Scale HIFiRE-1 Vehicle at Fully Duplicated Flight Conditions: Part II , 2008 .

[21]  F. Menter.  Two-equation eddy-viscosity turbulence models for engineering applications , 1994 .

[22]  Timothy Wadhams,et al.  Pre-Flight Ground Testing of the Full-Scale FRESH FX- 1 at Fully Duplicated Flight Conditions , 2007 .

[23]  Juan J. Alonso,et al.  Applications of a Cartesian Mesh Boundary-Layer Approach for Complex Configurations , 2006 .

[24]  D. Needham,et al.  Boundary layer separation in hypersonic flow , 1966 .

[25]  Roger L. Kimmel,et al.  Roughness Considerations for the HIFiRE-1 Vehicle , 2008 .

[26]  Graham V. Candler,et al.  PSE analysis of reacting hypersonic boundary layer transition , 1999 .

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

[28]  Noel T. Clemens,et al.  Planar imaging measurements to study the effect of spanwise structure of upstream turbulent boundary layer on shock induced separation , 2006 .

[29]  Roger L. Kimmel,et al.  HIFiRE-1 Boundary Layer Transition Experiment Design , 2007 .

[30]  Robert Tomaro,et al.  The defining methods of Cobalt-60 - A parallel, implicit, unstructured Euler/Navier-Stokes flow solver , 1999 .

[31]  T. Herbert.  PARABOLIZED STABILITY EQUATIONS , 1994 .

[32]  Reece E. Neel,et al.  Turbulence Model Validation in GASP Version 4 , 2003 .

[33]  Roger L. Kimmel,et al.  CFD Analysis in Development of Flight Test Article for Basic Research , 2006 .

[34]  Roger L. Kimmel,et al.  Effect of Total Temperature on Boundary-Layer Stability at Mach 6 , 2000 .

[35]  Steven P. Schneider,et al.  Development of Hypersonic Quiet Tunnels , 2008 .