scholarly journals Aerodynamic Characteristic Analysis of Multi-Rotors Using a Modified Free-Wake Method

2009 ◽  
Vol 52 (177) ◽  
pp. 168-179 ◽  
Author(s):  
Jaewon LEE ◽  
Kwanjung YEE ◽  
Sejong OH
Keyword(s):  
Aerodynamic Characteristic ◽  
Characteristic Analysis ◽  
Free Wake

A Method for Aerodynamic Characteristic Analysis of Hypersonic Aircraft Based on Response Surface Model

2013 ◽  
Vol 477-478 ◽  
pp. 277-280 ◽  
Author(s):  
Jie Yang ◽  
Song Ping Wu ◽  
Wen Xin Hou
Keyword(s):  
Flow Field ◽  
Response Surface ◽  
Aerodynamic Characteristic ◽  
Aerodynamic Characteristics ◽  
Surface Model ◽  
Complex Flow ◽  
Characteristic Analysis ◽  
Response Surface Models ◽  
Hypersonic Aircraft ◽  
Surface Models

Aerodynamic characteristic analysis of hypersonic cruise aircraft is more difficult than that of conventional aircraft, for the complex flow field simulation and inadequate amount of results under limited flight conditions. In this paper, numerical schemes applicable for hypersonic flow field are adopted to acquire a set of aerodynamic characteristics of a typical hypersonic cruise aircraft as sample data, based on which response surface models (RSM) are constructed to provide approximation of aerodynamic characteristics under any flight conditions within the design domain, finally the overall approximation performance of the response surface models are analyzed.

Rolling Moment Characteristic Analysis of Wrap-Around Fins

2010 ◽  
Vol 77 (5) ◽  
Author(s):  
Chen Xin-Hong ◽  
Zhao Run-Xiang
Keyword(s):  
Small Perturbation ◽  
Aerodynamic Characteristic ◽  
Pressure Coefficient ◽  
Angle Of Attack ◽  
Experimental Studies ◽  
Theoretical Method ◽  
Characteristic Analysis ◽  
Rolling Moment ◽  
Pressure Distributions ◽  
Perturbation Potential

A lot of numerical and experimental studies indicate that wrap-around fin configuration exhibits a self-induced rolling moment even at angle of attack zero. It depends on the unequal pressure distributions over both sides of the fin. In this paper, we try to prove this special aerodynamic characteristic with a theoretical method. According to the transonic small perturbation potential theory, as well as the transonic small perturbation potential equation, this paper found the expressions of the wrap-around fin convexity and the concave pressure coefficient at subsonic and supersonic by solving the Laplace equation and the Bessel function of imaginary argument, and analyze the phenomena of wrap-around fin rolling moment generation at angle of attack zero, and discuss the reason. The flow field of a projectile with wrap-around fins is solved by numerical method to check the pressure distributions of the two surfaces of the wing at subsonic and supersonic, respectively. The computational result is accordant to the theoretical analysis results. It is proved that the complicated pressure distribution of the wing surfaces leads to the particular characteristic of rolling moment.

Aerodynamic Characteristic Analysis of Flow Structure around the High-Speed Train Equipment Bay

2016 ◽  
Vol 693 ◽  
pp. 11-16 ◽  
Author(s):  
Yong Chang Zhang ◽  
Yu Gong Xu ◽  
Le Le Zhang
Keyword(s):  
Spectral Analysis ◽  
Flow Structure ◽  
Pressure Fluctuation ◽  
High Speed ◽  
Aerodynamic Characteristic ◽  
Influence Factors ◽  
High Speed Train ◽  
Characteristic Analysis ◽  
Train Speed ◽  
Improved Model

An improved train model, which contributes to obtain the aerodynamic characteristic of the high-speed train equipment bay, is established. By building a VEB (vehicle equipment bay) model in it, this improved model can demonstrate air flow around the VEB. The result shows that pressure fluctuation appears around the VEB, which gives visible difference from the classical train model. Applying the spectral analysis, the influence factors (include position and train speed) of the pressure fluctuation is studied.

Aerodynamic Characteristic Analysis of Two-Dimensional Trajectory Corrector Projectile in Mortar

2014 ◽  
Vol 624 ◽  
pp. 236-239
Author(s):  
Tong Zhang ◽  
Xiao Li Zhao ◽  
Zhen Dong Song
Keyword(s):  
Aerodynamic Characteristic ◽  
Lift Coefficient ◽  
Simulation Models ◽  
Future Research ◽  
Pitching Moment ◽  
Two Dimensional ◽  
Characteristic Analysis ◽  
Data Simulation ◽  
Moment Coefficient ◽  
Simulation Results

Aiming at researching aerodynamic characteristic of projectiles. This paper builds three simulation models with fins in different amount and appearance, by using CFD software to generate meshes of each model, it simulates the changing laws of drag coefficient, lift coefficient and pitching moment coefficient and analyses correct ability and flight stability of each model according to the data, simulation results indicate that projectile with folded fins have better aerodynamic appearance and can be studied deeper, it provides aerodynamic reference for future research.

scholarly journals On the aerodynamic interactions analysis between the main rotor and the helicopter fuselage

10.29007/3m41 ◽  
2020 ◽  
Author(s):  
Thanh Dong Pham ◽  
Anh Tuan Nguyen ◽  
Ngoc Thanh Dang ◽  
Vu Uy Pham
Keyword(s):  
Aerodynamic Characteristic ◽  
Vortex Lattice ◽  
Aerodynamic Characteristics ◽  
Main Rotor ◽  
Lattice Method ◽  
Vortex Lattice Method ◽  
Wake Model ◽  
Helicopter Main Rotor ◽  
Flight Regimes ◽  
Free Wake

This paper develops a numerical method that is capable of analyzing the aerodynamic characteristic of the helicopter main rotor in consider the influence of fuselage. The method is based on an unsteady nonlinear vortex-lattice method that can be used to simulate the interactions among the helicopter components efficiently. To clarify the effect of the main rotor-fuselage interaction, the aerodynamic characteristics of the main rotor in consider the influence of fuselage is determined along with those of the combined main rotor-fuselage system. The paper also shows the velocity field and free wake model in several flight regimes. The fuselage is modeled as a streamlined object, which is discretized into the system of quadrilateral vortex panels. The no-penetration boundary condition is satisfied on the fuselage surface, and no vorticity is shed from the fuselage. The results obtained in this paper are validated against experimental data and some from previous numerical methods.

1842: Catheter Free Potassium-Titanyl-Phosphate (KTP) Laser Photoselective Vaporization Prostatectomy (PVP): Patient Characteristic Analysis

2007 ◽  
Vol 177 (4S) ◽  
pp. 612-612
Author(s):  
Motoo Araki ◽  
Po N. Lam ◽  
Daniel J. Culkin ◽  
Pamela E. Fox ◽  
Glenn M. Sulley ◽  
...  
Keyword(s):  
Potassium Titanyl Phosphate ◽  
Ktp Laser ◽  
Characteristic Analysis ◽  
Photoselective Vaporization

Characteristic Analysis of a Micro DC-DC Converter for Portable Electronic Devices and an Improvement of Transient Response Characteristic

2008 ◽  
Vol 128 (12) ◽  
pp. 1373-1380
Author(s):  
Satoshi Sugahara ◽  
Kouhei Yamada ◽  
Haruhiko Nishio ◽  
Masaharu Edo ◽  
Toshiro Sato ◽  
...  
Keyword(s):  
Transient Response ◽  
Electronic Devices ◽  
Response Characteristic ◽  
Characteristic Analysis
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