The book discusses the behavior of vortices over sharp and highly swept wing configurations used for current and future military aircraft. Special attention is paid to the effects of critical flow phenomenon such as vortex breakdown occurring at high angles of attack or high angular rates. The wind tunnel experiments conducted on delta-wing configurations in wind tunnels in Canada, Europe, Russia and the United States are given in eight chapters. The experiments provide an extended data base that gives insight into the effects of the angle of attack, angular rate, Reynolds number and Mach number on the behavior of vortices over several slender delta wings in stationary and instationary flights. A critical assessment is given in a separated chapter of the available experimental data bases and out of these data, one and the same data set is selected for the validation and verification of analytical and numerical solutions.Comprehensive computational results are given in another ten chapters. Steady-state and time-accurate solutions for the steady and unsteady flow over the selected delta-wing configuration are discussed.
These solutions are generated using structured and unstructured grid methods. The analytical solutions for the flow over a delta wing are discussed and compared with experimental data in three more chapters. In the final chapter a validation and verification of the analytical and CFD solutions is given.
Tentative ToCExecutive SummarySynthesePublications of the RTO Applied Vehicle Technology PanelTable 1 Participants of the Applied Vehicle Technology Task Group AVT-080Table 2 Experimental, CFD and Analytical Cases1. Introduction and HighlightsX. Z. Huang and N. Verhaagen2. Critical Assessment of Experimental Cases of Vortex Behavior over Slender Military Wing ConfigurationsX. Z. Huang3. Experimental Data Base Selected for Numerical and Analytical Validation and Verification: ONERA 70-deg Delta WingA. Mitchell, et al.4. NARA LaRC 65 Delta Wing Test CasesJ. Luckring et al.5. Comprehensive Experimental Studies on Vortex Dynamics over Military Wing Configurations in IARX. Z. Huang6. Unsteady Aspects of Leading-Edge VorticesI. Gursul7. Leading Edge Vortex Flow Studies at the Univ. of Notre Dame - Steady and Unsteady Investigations 1983 - 2000F.M. Payne, K.D. Visser and R.C. Nelson8. Topology of the Flow on a 65 Delta WingN. Verhaagen and X. Z. Huang9. TsAGI 70 and 65 Delta Wing Test CasesA. Khrabrox and D. Greenwell10. Experimental Investigation of Vortex Dynamics on a 65 Delta WingG. Guglien and F.B. Quagliotti11. Vortical Flow Prediction Using an Adaptive Unstructured Grid MethodS. Z. Pirzadeh12. Origin of Stationary Shear-Layer Sub-Structures above Delta WingM.R.Visbal and E.G. Raymond13. Time-Accurate Euler Simulations of a Full-Span Delta Wing at High IncidenceS. Goertz14. Grid Study for Euler Simulations of 70 Delta Wing - with the Unstructured Flow Solver EDGEY. Le Moigne and A. Rizzi15. High Reynolds Number DES Simulations of Vortex Breakdown over 70 Delta WingS. Morton et al.16. RANS Solutions of 70 Delta Wing in Steady FlowJ.-F. Le Roy and O. Rodriguez17. Steady RANS Simulation of a 70 Delta Wing-with Tunnel EffectsM. Allen, K. Badcock, G.N. Barakos and B.E. Richards18. Simulation of Vortical Flow over ONERA 70 Delta Wing Experiencing Vortex BreakdownB. Soemarwoto et al.19. Unsymmetrical Vortex breakdown for Symmetric Free Stream ConditionsD. Hummel and M. Estorf20. RANS Solutions of 65 Delta WingA. Benmeddours21. Engineering Models of Delta Wing Vortex Breakdown and its Effect on Aerodynamic CharacteristicsD. Greenwell22. Non-Linear Indicial Response and Internal State-Space Representation and Its Application on Delta Wing ConfigurationsX. Z. Huang23. Applying Vortex Breakdown Empiricisms to Predict Aerodynamic Characteristics in Symmetric and Asymmetric SituationsR. Nangia24. Conclusions and RecommendationsX. Z. Huang, N. Verhaagen et al.
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