Aerodynamic design and performance analysis of a two-dimensional variable geometry inlet

2017 ◽  
Author(s):  
Huacheng Yuan ◽  
Yunfei Wang ◽  
Jun Liu ◽  
Zhengxu Hua
Keyword(s):  
Performance Analysis ◽  
Variable Geometry ◽  
Two Dimensional ◽  
Aerodynamic Design ◽  
And Performance ◽  
Dimensional Variable

Performance Analysis of the New Helicopter-Lift Device

2013 ◽  
Vol 380-384 ◽  
pp. 31-34
Author(s):  
Yue Ming Yang ◽  
Qin Yu Yang ◽  
Jin Bo Yao ◽  
Yuan Kai Li
Keyword(s):  
Numerical Simulation ◽  
Performance Analysis ◽  
Fuel Consumption ◽  
Turbulence Model ◽  
Complex Structure ◽  
Aerodynamic Characteristics ◽  
Two Dimensional ◽  
Aerodynamic Design ◽  
Design Technology ◽  
Low Efficiency

Helicopter lift system aerodynamic design is the key to success helicopter design technology. Currently helicopter lift system has complex structure, fuel consumption, low efficiency and many other issues, which greatly limits its potential to play, so the research of new efficient, simple and practical helicopter lift system is imminent. In this paper, a new kind of helicopter-lift device, combined with the whole structure, the specific presentation of the entire lift device works and ways of working. Based on 2D N-S equations and Spalart-Allmaras turbulence model, the device numerical simulation of two-dimensional aerodynamic characteristics. The results showed that: The lift device is feasible, can be applied to the helicopter technology. The results can lift device is designed for the helicopter to provide certain technical reference.

Design and validation of a two-dimensional variable geometry inlet

2021 ◽  
Vol 0 (0) ◽  
Author(s):  
Huacheng Yuan ◽  
Yunfei Wang ◽  
Jun Liu ◽  
Zhengxu Hua
Keyword(s):  
Mach Number ◽  
Wind Tunnel ◽  
Three Dimensional ◽  
Aerodynamic Performance ◽  
Back Pressure ◽  
Variable Geometry ◽  
Two Dimensional ◽  
Validation Experiment ◽  
Mach Numbers ◽  
Dimensional Variable

Abstract The design of a two-dimensional variable geometry inlet which applied to a tandem type turbine-based combined cycle (TBCC) propulsion system was investigated in the present paper through three-dimensional simulations and wind tunnel tests. The operation Mach number range was between 0 and 3. A multi-ramp geometry scheme was adopted to achieve acceptable performance at different inflow Mach number. The first ramp angle was fixed whilst the angles of the second and the third ramps were variable at different inflow Mach numbers. The Mach numbers at throat region were maintained between 1.3 and 1.5 at different inflow Mach numbers according to this variable geometry scheme. A fixed geometry rectangular-to-circular shape diffuser was adopted to improve aerodynamic performance of the inlet. Three-dimensional numerical simulations were carried out between Ma1.5 and Ma3.0. The results indicated that good aerodynamic performance can be achieved at different inflow speed. At the design point, total pressure recovery of the inlet was 0.66 at critical condition. Wind tunnel validation experiment tests were conducted at Ma2.0, showing the movement of terminal shock wave from downstream to upstream as the back pressure increased. The inlet operated at supercritical, critical and subsonic conditions at different back pressure.

Design and performance analysis of GPON-employed two-dimensional multidiagonal OCDMA code

2020 ◽  
Vol 59 (07) ◽  
pp. 1 ◽  
Author(s):  
Kehkashan A. Memon ◽  
Ahmad Atieh ◽  
A. Waheed Umrani ◽  
Mukhtiar A. Unar ◽  
Wajiha Shah
Keyword(s):  
Performance Analysis ◽  
Two Dimensional ◽  
And Performance
Sign in / Sign up

Export Citation Format

Share Document