A Unit-Problem Investigation of Blunt Leading-Edge Separation Motivated by AVT-161 SACCON Research

A research effort has been initiated to examine in more detail some of the challenging flow fields discovered from analysis of the SACCON configuration aerodynamics. This particular effort is oriented toward a diamond wing investigation specifically designed to isolate blunt leading-edge separation phenomena relevant to the SACCON investigations of the present workshop. The approach taken to design this new effort is reviewed along with the current status of the program.

[1]  Neal T. Frink,et al.  Upwind Scheme for Solving the Euler Equations on Unstructured Tetrahedral Meshes , 1992 .

[2]  S. P. Spekreijse,et al.  ENFLOW a full-functionality system of CFD codes for industrial Euler/Navier-Stokes flow computations , 1996 .

[3]  Peter A. Gnoffo,et al.  Uncertainty Assessment of Hypersonic Aerothermodynamics Prediction Capability , 2011 .

[4]  Russell M. Cummings,et al.  An Integrated Computational/Experimental Approach to UCAV Stability & Control Estimation: Overview of NATO RTO AVT-161 , 2010 .

[5]  James M. Luckring,et al.  Reynolds Number, Compressibility, and Leading-Edge Bluntness Effects on Delta-Wing Aerodynamics , 2004 .

[6]  Stephan M. Hitzel,et al.  Numerical and Experimental Analyses of the Vortical Flow Around the SACCON Configuration , 2010 .

[7]  R. M. Wood,et al.  Leeside flows over delta wings at supersonic speeds , 1984 .

[8]  Dietrich Hummel.  Effects of Boundary Layer Formation on the Vortical Flow above Slender Delta Wings , 2004 .

[9]  Michael J. Hemsch,et al.  Connection between leading-edge sweep, vortex lift, and vortex strength for delta wings , 1990 .

[10]  Dr. Ben H. Thacker,et al.  Model Validation and Uncertainty Quantification Applied to Cervical Spine Injury Assessment , 2008 .

[11]  Farhad Ghaffari,et al.  On the Vortical-Flow Prediction Capability of an Unstructured-Grid Euler Solver , 1994 .

[12]  M Hall Robert.  Impact of Fuselage Cross Section on the Stability of a Generic Fighter , 1998 .

[13]  Karl T. Edquist,et al.  Toward Supersonic Retropropulsion CFD Validation , 2011 .

[14]  N. G. Verhaagen,et al.  INTRODUCTION AND EXPERIMENTAL ASPECTS OF THE NATO RTO TASK GROUP AVT-080: "STUDY OF VORTEX BREAKDOWN OVER SLENDER WINGS" , 2004 .

[15]  Farhad Ghaffari,et al.  Navier-Stokes solutions about the F/A-18 forebody-leading-edge extension configuration , 1990 .

[16]  Anthony Mitchell,et al.  Experimental Data Base Selected for RTO/AVT Numerical and Analytical Validation and Verification: ONERA 70-deg Delta Wing , 2003 .

[17]  Timothy G. Trucano,et al.  Verification and Validation in Computational Fluid Dynamics , 2002 .

[18]  Christian Klein,et al.  PSP and PIV Investigations on the VFE-2 Configuration in Sub- and Transonic Flow , 2008 .

[19]  Melissa B. Rivers,et al.  Experimental Investigations of the NASA Common Research Model in the NASA Langley National Transonic Facility and NASA Ames 11-Ft Transonic Wind Tunnel (Invited) , 2011 .

[20]  Kristian Petterson,et al.  CFD Analysis of the Low-Speed Aerodynamic Characteristics of a UCAV , 2006 .

[21]  J. Benek.  Lessons Learned from the 2010 AIAA Shock Boundary Layer Interaction Prediction Workshop , 2010 .

[22]  G. E. Wilson,et al.  The role of the PIRT process in experiments, code development and code applications associated with Reactor Safety analysis , 1998 .

[23]  D. W. Bryer.  The Bursting of Leading-Edge Vortices Some Observations and Discussion of the Phenomenon , 2002 .

[24]  William L. Oberkampf,et al.  Guide for the verification and validation of computational fluid dynamics simulations , 1998 .

[25]  M J Hemsch,et al.  Langley Wind Tunnel Data Quality Assurance - Check Standard Results , 2000 .

[26]  Ken Badcock,et al.  Shock effects on delta wing vortex breakdown , 2008 .

[27]  Michael J. Hemsch,et al.  Statistical Analysis of CFD Solutions from the Drag Prediction Workshop , 2002 .

[28]  Edward C. Polhamus,et al.  A Survey of Reynolds Number and Wing Geometry Effects on Lift Characteristics in the Low Speed Stall Region , 1996 .

[29]  A. Stanbrook,et al.  Possible Types of Flow at Swept Leading Edges , 1964 .

[30]  D. I. A. Poll.  Spiral vortex flow over a swept-back wing , 1986, The Aeronautical Journal (1968).

[31]  James M. Luckring,et al.  A Survey of Factors Affecting Blunt Leading-Edge Separation for Swept and Semi-Slender Wings , 2010 .

[32]  J. H. B. Smith,et al.  Improved calculations of leading-edge separation from slender, thin, delta wings , 1968, Proceedings of the Royal Society of London. Series A. Mathematical and Physical Sciences.

[33]  Neal Frink,et al.  Strategy for Dynamic CFD Simulations on SACCON Configuration , 2010 .

[34]  Leonard E. Schwer,et al.  An overview of the PTC 60/V&V 10: guide for verification and validation in computational solid mechanics , 2007, Engineering with Computers.

[35]  Christopher J. Roy,et al.  Verification and Validation in Scientific Computing , 2010 .

[36]  Neal T. Frink,et al.  Unstructured CFD Aerodynamic Analysis of a Generic UCAV Configuration , 2011 .