Titlebook: Boundary Element Methods in Engineering; Proceedings of the I Balkrishna S. Annigeri,Kadin Tseng Conference proceedings 1990 Springer-Verla

欺侮

書目名稱Boundary Element Methods in Engineering影響因子(影響力)




書目名稱Boundary Element Methods in Engineering影響因子(影響力)學(xué)科排名




書目名稱Boundary Element Methods in Engineering網(wǎng)絡(luò)公開(kāi)度




書目名稱Boundary Element Methods in Engineering網(wǎng)絡(luò)公開(kāi)度學(xué)科排名




書目名稱Boundary Element Methods in Engineering被引頻次




書目名稱Boundary Element Methods in Engineering被引頻次學(xué)科排名




書目名稱Boundary Element Methods in Engineering年度引用




書目名稱Boundary Element Methods in Engineering年度引用學(xué)科排名




書目名稱Boundary Element Methods in Engineering讀者反饋




書目名稱Boundary Element Methods in Engineering讀者反饋學(xué)科排名

放逐

Time and Frequency Domain Aerodynamics for Flutter of Helicopter Rotors in Hovery-element formulation for unsteady potential incompressible flows is introduced. The results obtained for the aerodynamic forces, for pitch and flap, are compared with those typically used in the flutter analysis of rotors, (which are obtained using a strip-theory extension of Loewy’s formulation [3

Canyon

凝結(jié)劑

A General Purpose Fixed-Wing and Rotary-Wing Compressible Aerodynamics Analysis Method in which the wake and/or field influence is coupled into the linear Laplace solver through the boundary conditions. There are a number of advantages in using this approach. For instance, since the wake effect is “seen” as an induced velocity, any methodology that can provide this information may be

揭穿真相

機(jī)密

Panel Methods for Multiple-Rotor Aerodynamicson. The earlier of the two is a full surface, time marching panel scheme based on Morino’s formulation. It has been implemented only for low speed (incompressible) flow. The second scheme uses an iterative coupling of the rotor velocity fields, decomposed into harmonics. Each field harmonic is compu

推崇

Salivary-Gland

A Vortex Method for Predicting Unsteady Flow and Boundary Layer Development Around an Airfoilminar and turbulent boundary layers are treated. By using even a rather small computer, reasonable prediction of starting flows around an airfoil of NACA23012 are obtained for various angles of attack either with or without boundary layer separation. The emphasis in the following article will be on

ORE

蝕刻術(shù)

A Unified Approach for Potential and Viscous Flows in Fixed-Wing and Rotary-Wing Aerodynamicsential aerodynamics and to introduce an extension of the formulation to compressible viscous flows. For the sake of simplicity, details of the formulation are given only for incompressible flows. For compressible flows, the formulations are only outlined. Also, because of space limitations no numeri