Thesis--Kungl. Tekniska Högskolan, Stockholm, 1959. / In English. Bibliography: p. 11-12.

Thesis (Ph. D.)--Carleton University, 2001. / Includes bibliographical references (p. 254-257). Also available in electronic format on the Internet.

No description available.

Thesis (M.S.)--University of Notre Dame, 2004. / Thesis directed by Eric J. Jumper for the Department of Aerospace and Mechanical Engineering. "April 2004." Includes bibliographical references (leaves 66-68).

No description available.

No description available.

Thesis (M.S.)--Virginia Polytechnic Institute and State University, 1991. / Vita. Abstract. Includes bibliographical references (leaves 53-56). Also available via the Internet.

Multidisciplinary Design Optimization (MDO) studies show the Strut/Truss Braced Wing (SBW/TBW) concept has the potential to save a significant amount of fuel over conventional designs. For the SBW/TBW concept to achieve these reductions, the interference drag at the wing strut juncture must be small compared to other drag sources. Computational Fluid Dynamics (CFD) studies have concluded the interference drag is small enough for the TBW concept to be practical. However, the turbulence models used in these studies have not been validated for transonic, high Reynolds number, junction flows. This study intends to assess turbulence models by comparing drag and surface streamlines obtained from experiment and CFD. The test model is a NACA 0012 fin at Mach number of 0.75 and a Reynolds number of 6 million with varying angle of attack. The CFD analysis includes both the fin and tunnel test section. The main turbulence model tested is the k-w Shear Stress Transport model. The fin is tested at different Mach numbers and inlet conditions to account for experimental variations. The study shows the CFD over predicts separation. The reasons for this discrepancy is likely the turbulence models employed. / Master of Science

The purpose of this thesis is to study the shock/wave turbulent boundary layer interaction by using delayed-detached-eddy simulation (DDES) model with a low diffusion E-CUSP (LDE) scheme with fifth-order WENO scheme. The results show that DDES simulation provides improved results for the shock wave/turbulent boundary layer interaction compared to those of its predecessor the detached-eddy simulation (DES). The computation of mesh refinement indicates that the grid density has significant effects on the results of DES, while being resolved by applying DDES simulation. Spalart in 1997 developed the Detached-Eddy Simulation (DES) model, which is a hybrid RANS and LES method, to overcome the intensive CPU requirement from LES models. Near the solid surface within a wall boundary layer, the unsteady RANS model is realized. Away from the wall surface, the model automatically converts to LES. The Delayed-Detached-Eddy Simulation (DDES) was suggested by Spalart in 2006 to improve the DES model previously developed. The transition from the RANS model to LES in DES is not grid spacing independent, therefore a blending function is introduced to the recently developed DDES model to make the transition from RANS to LES grid spacing independent. The DDES is validated by computing a 3D subsonic flat plate turbulent boundary layer. The first case studied using DDES is a 3D transonic channel with shock/turbulent boundary layer interaction. It consists of two straight side walls, a straight top wall, and a varying shape in span-wise direction for a bottom wall. The second case studied consists of a 3D transonic inlet-diffuser. Both results are compared with experimental data. The computed results of the transonic channel agree well with experimental data.

The capability for experimental assessment of unsteady shock wave effects on turbine blade performance has been developed. A novel shock-generation system utilizing a shotgun blast has been implemented into the Virginia Tech Wind Tunnel Transonic Cascade Facility. Specialized optical systems and high-performance pressure instrumentation were utilized to obtain both qualitative and quantitative information. Shadowgraph photos of the unsteady shock wave propagation through the cascade indicate presence of a vortical region and its movement from the blade surface into the passage flow. A previously unseen distortion of the trailing edge shock wave is also identified. High-frequency blade surface pressure measurements reveal large fluctuations in surface pressure during shock passage. An estimate of unsteady blade lift is made which reveals a 120 percent peak-peak variation. Furthermore, an approximated loss coefficient was determined to fluctuate as much as 40 percent near the blade passage center. Comparisons are made with previously-published experimental and analytical results. / Master of Science