Results 11 to 20 of about 116 (92)
Intelligent Controller Design for a Blowdown Supersonic Wind Tunnel
International Journal of Control and Automation, 2014 In this paper, first, the nonlinear mathematical model of special Blowdown Supersonic Wind Tunnel (BSWT) consisting of a set of ordinary differential and algebraic equations is developed in Matlab/Simulink software environment. At the second step, an Artificial Neural Network (ANN) is used for finding the optimum membership functions of the Fuzzy Logic
A. Nazarian Shahrbabaki +3 more
wiley +3 more sources
Dynamic responses and vibration control of the transmission tower-line system: a state-of-the-art review. [PDF]
ScientificWorldJournal, 2014 This paper presented an overview on the dynamic analysis and control of the transmission tower‐line system in the past forty years. The challenges and future developing trends in the dynamic analysis and mitigation of the transmission tower‐line system under dynamic excitations are also put forward.
Chen B, Guo WH, Li PY, Xie WP.
europepmc +2 more sources
Inviscid and viscous interactions in subsonic corner flows. [PDF]
ScientificWorldJournal, 2013 A flap can be used as a high‐lift device, in which a downward deflection results in a gain in lift at a given geometric angle of attack. To characterize the aerodynamic performance of a deflected surface in compressible flows, the present study examines a naturally developed turbulent boundary layer past the convex and concave corners.
Chung KM, Chang PH, Chang KC.
europepmc +2 more sources
International Journal of Aerospace Engineering, Volume 2023, Issue 1, 2023., 2023 To examine the impact of oxidative jets on the thrust vector angle, secondary combustion efficiency, and combustion chamber pressure, inert gas (nitrogen) and pure oxygen are injected into the primary flow, which includes combustible components, at various locations in the divergence section and throat using different injection techniques.
Dongfeng Yan +5 more
wiley +1 more source
Dusting Hole Film Cooling Heat Transfer on a Transonic Turbine Blade Tip
International Journal of Rotating Machinery, Volume 2022, Issue 1, 2022., 2022 Investigated is a transonic turbine blade tip with a squealer rim and a squealer recess, with a single dusting film cooling hole contained within the leading edge region of the squealer recess. Data are provided for transonic flow conditions for a range of film cooling blowing ratios for two tip gap values, using a linear cascade, with no relative ...
Ward Manneschmidt +7 more
wiley +1 more source
Separation Control for a Transonic Convex Corner Flow Using Ramp‐Type Vortex Generators
International Journal of Aerospace Engineering, Volume 2022, Issue 1, 2022., 2022 A flap can be used to control wing camber and as a high‐lift device. A convex corner is a simplified model of the upper surface of a flap. At transonic speeds, shock‐induced boundary layer separation (SIBLS) occurs at greater freestream Mach numbers and deflection angles. This results in energy losses and a reduction in aerodynamic performance.
Kao-Chun Su +3 more
wiley +1 more source
Geofluids, Volume 2022, Issue 1, 2022., 2022 This paper presents a fluid sloshing model using the artificial neural network method (ANN). Determining the fluid sloshing model in the tank is a challenging task due to its nonlinearity and complexity of behavior to its environmental and operational conditions.
Hossein Goudarzvand Chegini +2 more
wiley +1 more source
Aquatic and riparian ecosystem recovery from debris flows in two western Washington streams, USA
Ecology and Evolution, Volume 10, Issue 6, Page 2749-2777, March 2020., 2020 An exceptionally powerful storm caused large debris flows in two adjacent streams. The two affected streams had been studied prior to the storm providing a rare opportunity to examine ecosystem recovery. We monitored the streams and their riparian zones for 6 years after the disturbances to determine whether recovery rates of biota, physical habitat ...
Alex D. Foster +3 more
wiley +1 more source
Design and preliminary experiment of a 0.3 × 0.15 m2 low-disturbance supersonic wind tunnel [PDF]
AIP AdvancesTo meet the requirement for the low disturbance of wind tunnel flow in supersonic boundary layer transition simulation tests, a low-disturbance supersonic research wind tunnel with a nozzle size of 0.3 × 0.15 m2 and test Mach number of 3.0 was built.
Xingyou Yi +13 more
doaj +1 more source
Model-based stagnation pressure control in a supersonic wind tunnel [PDF]
FME Transactions, 2016 The flow parameters control in wind tunnels is an area of intense research in recent years, with the aim of improving quality and efficiency of the wind tunnel operation.
Ilić Biljana +3 more
doaj