Leading-Edge Geometry Effects on the Vortex Formation of a Diamond-Wing Configuration

The effects of spanwise-varying leading-edge contours with respect to vortex formation are investigated on a diamond-wing configuration named SAGITTA. At low-speed conditions, three different leading-edge configurations are considered for which the spanwise leading-edge contours can be of a sharp or rounded type. In a combined approach, both numerical computations and experimental investigations are therefore conducted. On the one hand, both steady and unsteady Reynolds-averaged Navier–Stokes equations are applied to compute numerical results for all three different leading-edge configurations. On the other hand, wind-tunnel experiments are performed for the reference configuration to study the overall aerodynamic characteristics. It turns out that the agreement between the numerics and experiment is very good. Depending on the chosen leading-edge contours, the numerical analyses show a different vortex formation on the SAGITTA diamond-wing configuration, which results in diverse flow topologies. Both the...

[1]  Russell M. Cummings,et al.  An integrated computational/experimental approach to X-31 stability & control estimation , 2012 .

[2]  Thomas Gerhold,et al.  Overview of the Hybrid RANS Code TAU , 2005 .

[3]  Christian Breitsamter,et al.  Turbulent and unsteady flow characteristics of delta wing vortex systems , 2013 .

[4]  Stephan M. Hitzel,et al.  Flow Physics Analyses of a Generic Unmanned Combat Aerial Vehicle Configuration , 2012 .

[5]  Antony Jameson,et al.  Multigrid solution of the Euler equations using implicit schemes , 1985 .

[6]  Ralf Heinrich,et al.  COMPARISON AND EVALUATION OF CELL-CENTERED AND CELL-VERTEX DISCRETIZATION IN THE UNSTRUCTURED TAU-CODE FOR TURBULENT VISCOUS FLOWS , 2010 .

[7]  Simone Crippa,et al.  Lessons Learned from Numerical Simulations of the F-16XL Aircraft at Flight Conditions , 2009 .

[8]  Russell M. Cummings,et al.  Integrated Computational/Experimental Approach to Unmanned Combat Air Vehicle Stability and Control Estimation , 2012 .

[9]  Antony Jameson,et al.  Lower-upper implicit schemes with multiple grids for the Euler equations , 1987 .

[10]  Steve L. Karman,et al.  Reynolds-Averaged Navier-Stokes Solutions for the CAWAPI F-16XL Using Different Hybrid Grids , 2009 .

[11]  P. Spalart.  A One-Equation Turbulence Model for Aerodynamic Flows , 1992 .

[12]  Willy Fritz.  Numerical simulation of the peculiar subsonic flow-field about the VFE-2 delta wing with rounded leading edge☆ , 2013 .

[13]  Russell M. Cummings,et al.  What Was Learned From the Numerical Simulations for the VFE-2 , 2008 .

[14]  B. Şahin,et al.  Yaw Angle Effect on Flow Structure over the Nonslender Diamond Wing , 2010 .

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

[16]  A. Jameson,et al.  Numerical solution of the Euler equations by finite volume methods using Runge Kutta time stepping schemes , 1981 .

[17]  James M. Luckring,et al.  Experimental Surface Pressure Data Obtained on 65 deg Delta Wing Across Reynolds Number and Mach Number Ranges. Volume 1; Sharp Leading Edge; [conducted in the Langley National Transonic Facility (NTF)] , 1996 .

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

[19]  Christian Breitsamter,et al.  Aerodynamic Characteristics of the SAGITTA Diamond Wing Demonstrator Configuration , 2012 .

[20]  Heinrich Lüdeke,et al.  Numerical investigations on the VFE-2 65-degree rounded leading edge delta wing using the unstructured DLR TAU-Code , 2013 .

[21]  Miguel R. Visbal,et al.  Unsteady aerodynamics of nonslender delta wings , 2005 .

[22]  Christian Breitsamter,et al.  Unsteady flow phenomena associated with leading-edge vortices , 2008 .

[23]  Ralf Heinrich,et al.  The DLR TAU-Code: Recent Applications in Research and Industry , 2006 .

[24]  O. J. Boelens,et al.  Prediction of the flow around the X-31 aircraft using three different CFD methods , 2012 .