Controlling Aerodynamic Characteristics of High-Velocity Airfoils by External Energy Supply

2010 ◽  
Vol 5 (3) ◽  
pp. 47-512
Author(s):  
Sergey M. Aulchenko ◽  
Vladimir P. Zamuraev ◽  
Anna P. Kalinina
Keyword(s):  
Boundary Layer ◽  
High Velocity ◽  
Energy Supply ◽  
Aerodynamic Characteristics ◽  
External Energy ◽  
Gas Density ◽  
Boundary Layer Approximation

The influence of pulsed-periodic (proportional to gas density) energy supply on the aerodynamic characteristics of high-velocity airfoils was studied. The value of the period of the energy supply was varied. The influence of viscosity in the boundary layer approximation has been taken into consideration as well

Effect of boundary-layer removal on high velocity flame stabilization

AIAA Journal ◽  
1964 ◽  
Vol 2 (11) ◽  
pp. 2030-2031
Author(s):  
JAMES R. MAUS ◽  
WILLIAM T. SNYDER
Keyword(s):  
Boundary Layer ◽  
High Velocity ◽  
Flame Stabilization ◽  
Layer Removal

A Simple and Robust Subsonic Boundary Layer Method to Be Used with the Panel Method for Wing Calculations Using a Wing Strip Approach

2015 ◽  
Vol 798 ◽  
pp. 596-601
Author(s):  
R.F. Francisco Reis ◽  
Guilherme A. Santana ◽  
Paulo Iscold ◽  
Carlos A. Cimini
Keyword(s):  
Boundary Layer ◽  
Lift Coefficient ◽  
Aircraft Design ◽  
Aerodynamic Characteristics ◽  
Viscous Drag ◽  
Layer Method ◽  
Boundary Layer Method ◽  
Dimensional Boundary ◽  
Classical Integral ◽  
Empirical Corrections

This paper will present the development of a simple subsonic boundary layer method suitable to be used coupled with panel methods in order to estimate the aerodynamic characteristics, including viscous drag and maximum lift coefficient, of 3D wings. The proposed method does not require viscous-inviscid iterations and is based on classical integral bi-dimensional boundary layer theory using Thwaites and Head ́s models with bi-dimensional empirical corrections applied to each wing strip being therefor robust and efficient to be used in the early conceptual stage of aircraft design. Presented results are compared to the Modified CS Method in an IBL scheme and experimental data and are shown to provide good results.

PWM Design for Active Suspension without External Energy Supply Based on LQG Control

2012 ◽  
Vol 268-270 ◽  
pp. 1478-1481
Author(s):  
Shian Chen ◽  
Xuan Li ◽  
Sheng Wang ◽  
Jian Lian Zhao ◽  
Ze He Tang
Keyword(s):  
Energy Flow ◽  
Energy Supply ◽  
Control Method ◽  
Active Suspension ◽  
Flow Equation ◽  
External Energy ◽  
Passive Suspension ◽  
Quadratic Performance Index ◽  
Lqg Control ◽  
Quadratic Performance

A PWM controller is designed for the active suspension without external energy supply (ASWEES) using the LQG control method. Based on the quarter-vehicle ASWEES model, Energy flow equation between the suspension and the accumulator with a 2 kW load was deduced and a PWM controller was designed. When 200Hz solenoid valves were adopted, the carrier frequency and series value of the carrier signal were set as 40 and 5 respectively. Simulation results show the suspension quadratic performance index of ASWEES decreases 24.97% than that of the passive suspension. The passive suspension consumes 2.211kW power, but ASWEES reclaims energy of 2 kW.

On the flow near the trailing edge of a flat plate

1968 ◽  
Vol 306 (1486) ◽  
pp. 275-290 ◽  
Keyword(s):  
Boundary Layer ◽  
Flat Plate ◽  
Stokes Equations ◽  
Navier Stokes ◽  
Governing Equations ◽  
Trailing Edge ◽  
Navier Stokes Equations ◽  
Multiplicative Constant ◽  
Boundary Layer Approximation ◽  
Uniform Shear

It is shown that the boundary layer approximation to the flow of a viscous fluid past a flat plate of length l , generally valid near the plate when the Reynolds number Re is large, fails within a distance O( lRe -3/4 ) of the trailing edge. The appropriate governing equations in this neighbourhood are the full Navier- Stokes equations. On the basis of Imai (1966) these equations are linearized with respect to a uniform shear and are then completely solved by means of a Wiener-Hopf integral equation. The solution so obtained joins smoothly on to that of the boundary layer for a flat plate upstream of the trailing edge and for a wake downstream of the trailing edge. The contribution to the drag coefficient is found to be O ( Re -3/4 ) and the multiplicative constant is explicitly worked out for the linearized equations.

A New Method to Measure Prandtl Number and Thermal Conductivity of Fluids

1957 ◽  
Vol 24 (1) ◽  
pp. 25-28
Author(s):  
E. R. G. Eckert ◽  
T. F. Irvine
Keyword(s):  
Thermal Conductivity ◽  
Boundary Layer ◽  
Prandtl Number ◽  
High Velocity ◽  
Atmospheric Pressure ◽  
New Method ◽  
Test Results ◽  
Test Setup ◽  
Velocity Boundary Layer ◽  
Layer Flow

Abstract A new method is described by which the Prandtl number and indirectly the thermal conductivity of fluids can be measured. The method is based on the fact that a well-established, unique relation exists between the Prandtl number and the recovery factor for laminar high-velocity boundary-layer flow. The test setup is described which has been devised for such measurements, and test results are presented for air at atmospheric pressure and temperatures between 60 and 350 F.

Self-contained Electrochemical Process to Produce Pure Compressed Hydrogen from Hydrocarbons and Steam Without an External Energy Supply

2020 ◽  
Vol 167 (10) ◽  
pp. 104512
Author(s):  
Huayang Zhu ◽  
W. Grover Coors ◽  
Sandrine Ricote ◽  
Canan Karakaya ◽  
Robert J. Kee
Keyword(s):  
Energy Supply ◽  
Electrochemical Process ◽  
External Energy
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