Results 251 to 260 of about 11,847,871 (295)
Some of the next articles are maybe not open access.
Total pressure loss in vortical solutions of the conical Euler equations
AIAA Journal, 1985A technique for the solution of the conically self-similar form of the Euler equations is described. Solutions for the flow past a flat-plate delta wing at angle of attack are presented. These solutions show strong leading edge vortices with large total pressure losses in the cores.
K. POWELL, E. MURMAN, E. PEREZ, J. BARON
openaire +1 more source
The minimization of the total pressure loss accompanying the breakdown of a supersonic flow
Journal of Applied Mathematics and Mechanics, 1998Abstract The problem of minimizing the total pressure loss accompanying the breakdown of a supersonic flow to subsonic velocities through a system of successively ordered shock waves is considered. By changing to the corresponding problem of non-linear programming with non-linear constraints in the form of inequalities, a point which is suspected of ...
V.N. Malozemov +2 more
openaire +1 more source
Total Loss of Feedwater Analysis of Pressurized Water Reactor Using RELAP5
Journal of Nuclear Engineering and Radiation Science, 2023Abstract In Europe, the design extension conditions (DEC) were introduced after the Fukushima Dai-ichi accident as preferred method for giving due consideration to the complex sequences and severe accidents without including them in the design basis conditions. The objective of the study is to determine available elapsed time before core
openaire +1 more source
Leading-edge vortex solutions with large total pressure losses
25th AIAA Aerospace Sciences Meeting, 1987Computations are presented for a Lambda = 75 deg delta wing in a supersonic freestream under two conditions which lead to leading-edge vortices. For one condition, analysis of the computed vortical flow reveals a closed streamline in the core. From varying computational parameters, it appears that this is due to truncation error of the convective ...
EARLL MURMAN +3 more
openaire +1 more source
Research on Mixing Characteristics and Total Pressure Loss of the Jet in Supersonic Crossflow
49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, 2013Jet from wall orifice is the simplest and commonest way of injection in the scramjet engine. The mixing characteristics and total pressure loss of jet in supersonic crossflow (JISC) are very complex but important to the combustion in chamber and the performance of scramjet engine.
Yan-Hui Zhao +3 more
openaire +1 more source
Slender wing theory including regions of embedded total pressure loss
26th Aerospace Sciences Meeting, 1988An aerodynamic theory of the flow about slender delta wings is described. The theory includes a treatment of the self-consistent development of the vortex wake patterns above the wing necessary to maintain smooth flow at the wing edges. The paper focuses especially on the formation within the wake of vortex 'cores' as embedded regions of total pressure
McCune, James E. +3 more
openaire +2 more sources
Total pressure losses minimization in turbomachinery cascades using the exact Hessian
Computer Methods in Applied Mechanics and Engineering, 2010zbMATH Open Web Interface contents unavailable due to conflicting licenses.
Zervogiannis, T. +2 more
openaire +1 more source
On estimation of total pressure internal losses in the axial-inlet annular diffuser channels
Russian Aeronautics (Iz VUZ), 2008Based on the numerical simulation data, it is shown that the techniques for determining internal losses of total pressure in the axial-inlet annular diffusers with the rectilinear generatrices through the overall losses (assuming that the nonuniformity of the turbulent flow in the radial direction along the channel length is invariable) lead to ...
E. N. Bogomolov, A. V. Kashcheev
openaire +1 more source
Strut Injectors for Scramjets: Total Pressure Losses in Two Streamwise Vortex Interactions
Journal of Propulsion and Power, 2017Pressure losses and mixing effectiveness are key parameters in the performance of an injection system suitable for scramjet engines.
Fabrizio Vergine +2 more
openaire +1 more source
Second Vane Total Pressure Loss Due to Endwall Iceform Contouring
Volume 6: Turbomachinery, Parts A, B, and C, 2008The iceformation design method generates an endwall contour, altering the secondary flows that produce elevated endwall heat transfer load and total pressure losses. Iceformation is an analog to regions of metal melting where a hot fluid alters the isothermal surface shape of a part as it is maintained by a cooling fluid.
openaire +1 more source