Computational Fluid Dynamics Investigation of Vortex Breakdown for a Delta Wing at High Angle of Attack

<p>Using the commercially available FLUENT 3-D flow field solver this research effort investigated vortex breakdown over a delta wing at high angle of attack (α) in preparation for investigation of active control of vortex breakdown using steady alongcore blowing. A flat delta-shaped half-wing with sharp leading edge and sweep angle of 60 [degrees] was modeled at α = 18 [degrees] in a wind tunnel at Mach 0.04 and Reynolds number of 3.4 x 10 5. A hybrid (combination of structured and unstructured) numerical mesh was generated to accommodate blowing ports on the wing surface. Results for cases without and with along-core blowing included comparison of various turbulence models for predicting both flow field physics and quantitative flow characteristics. FLUENT turbulence models included Spalart-Allmaras (S-A) Renormalization Group k-ε Reynolds Stress (RSM) and Large Eddy Simulation (LES) as well as comparison with laminar and inviscid models. Mesh independence was also investigated and solutions were compared with experimentally determined results and theoretical prediction. These research results show that excepting the LES model for which the computational mesh was insufficiently refined and which was not extensively investigated none of the turbulence models above as implemented with the given numerical grid generated a solution which was suitably comparable to the experimental data. Much more work is required to find a suitable combination of numerical grid and turbulence model.</p><p>This work has been selected by scholars as being culturally important and is part of the knowledge base of civilization as we know it. This work was reproduced from the original artifact and remains as true to the original work as possible. Therefore you will see the original copyright references library stamps (as most of these works have been housed in our most important libraries around the world) and other notations in the work.</p><p>This work is in the public domain in the United States of America and possibly other nations. Within the United States you may freely copy and distribute this work as no entity (individual or corporate) has a copyright on the body of the work.</p><p>As a reproduction of a historical artifact this work may contain missing or blurred pages poor pictures errant marks etc. Scholars believe and we concur that this work is important enough to be preserved reproduced and made generally available to the public. We appreciate your support of the preservation process and thank you for being an important part of keeping this knowledge alive and relevant.</p><br>