scholarly journals Comparative flow path analysis and design assessment of an axisymmetric hydrogen fueled scramjet flight test engine at a Mach number of 6.5

1996 ◽  
Author(s):  
C. McClinton ◽  
A. Roudakov ◽  
V. Semenov ◽  
V. Kopehenov
Keyword(s):  
Mach Number ◽  
Path Analysis ◽  
Flight Test ◽  
Flow Path ◽  
Design Assessment ◽  
Analysis And Design ◽  
Test Engine

scholarly journals Interpolation of Turbulent Boundary Layer Profiles Measured in Flight Using Response Surface Methodology

2018 ◽  
Vol 8 (11) ◽  
pp. 2320 ◽  
Author(s):  
Hidemi Takahashi ◽  
Mitsuru Kurita ◽  
Hidetoshi Iijima ◽  
Monami Sasamori
Keyword(s):  
Boundary Layer ◽  
Mach Number ◽  
Turbulent Boundary Layer ◽  
Response Surface ◽  
Flight Test ◽  
Response Surface Model ◽  
Surface Model ◽  
Number Range ◽  
Independent Variables ◽  
Surface Method

Turbulent boundary layer profiles on the aircraft surface were characterized by pitot-rake measurements conducted in flight experiments at high subsonic Mach number ranges. Due to slight variations in atmospheric air conditions or aircraft attitudes, such as angles of attack and absolute flight speeds at different flights even under the same premised flight conditions, the boundary layer profiles measured at different flights can exhibit different shape and velocity values. This concern leads to difficulty in evaluating the efficiency of using some kind of drag-controlling device such as riblets in the flight test, since the evaluation would be conducted by comparing the profiles measured with and without using riblets at different flights. An approach was implemented to interpolate the boundary layer profile for a flight condition of interest based on the response surface method, in order to eliminate the influence of the flight conditional difference. Results showed that the interpolation with the 3rd-degree response surface model with a combination of two independent variables of flight Mach number and total pressure successfully eliminated the influence of the flight conditional difference, and interpolated the boundary layer profiles measured at different flights within an inaccuracy of 4.1% for the flight Mach number range of 0.5 to 0.78.

Aerodynamic analysis and design of Busemann biplane: towards efficient supersonic flight

2011 ◽  
Vol 226 (2) ◽  
pp. 217-238 ◽  
Author(s):  
D Maruyama ◽  
K Kusunose ◽  
K Matsushima ◽  
K Nakahashi
Keyword(s):  
Mach Number ◽  
Design Method ◽  
Three Dimensional ◽  
Aerodynamic Characteristics ◽  
Aerodynamic Performance ◽  
The Body ◽  
Analysis And Design ◽  
Expansion Waves ◽  
Mach Numbers ◽  
Inverse Design Method

Aiming to realize a low-drag supersonic transport, Busemann biplane concept was adopted in this study. Two- and three-dimensional (2D and 3D) biplanes were analysed and designed to improve their aerodynamic performance using computational fluid dynamics. It was confirmed that 3D biplane wings have better aerodynamic-performance areas than 2D biplane airfoils. A winglet is also useful for improvement of their aerodynamic performance. Aerodynamic characteristics of these biplanes at their off-design conditions were also analysed. In 3D wings, a flow choking and its attendant hysteresis as starting problems, which arise when the biplanes accelerate from low Mach numbers, disappear at lower Mach numbers than those in 2D airfoils. It was confirmed that hinged slats and flaps are effective to settle these issues. Finally, interference effects of a body with the biplanes were investigated. When the biplane wings are affected by the expansion waves from the body, their aerodynamic performance at the design Mach number and the starting Mach number are better and lower than those of their isolated wings, respectively. A 3D biplane wing obtained by an inverse-design method was applied to the body. The wing of this wing–body configuration achieves higher aerodynamic performance than the 2D flat-plate airfoil at sufficient lift conditions, which is the almost identical performance of 2D biplane airfoils.

scholarly journals Airborne Real Time Instrumentation System (ARTISt): Studi Analisis dan Perancangannya

2011 ◽  
Vol 2 (1) ◽  
Author(s):  
Imam M. Shofi
Keyword(s):  
Real Time ◽  
Test Data ◽  
Mixed Mode ◽  
Flight Test ◽  
Requirements Analysis ◽  
Pulse Code Modulation ◽  
Graphic Mode ◽  
Analysis And Design ◽  
Time Table ◽  
Code Modulation

ARTISt is an instrumentation system based on Personal Computer (PC) which is installed on board the prototype aircraft to perform presentation of flight test data in real time. The presentation consists of display the data in table mode, graphic mode, mixed mode (table and graphic), and  xplot mode (graphic between 2 parameters), and also print and record the data. The data which has been recorded by ARTISt, can be used by other software through the Disk Management System (DMS). The PC equipped with an interface for Pulse Code Modulation  (PCM) decoder called ARTISt Card.In this paper, we are discussing about requirements analysis and design the ARTISt.   Keywords: ARTISt, flight test data, real time, table mode, graphic mode, mixed mode, xplot mode, requirements analysis and design

Optimal Design of Complex Switched-Capacitor Converters Via Energy-Flow-Path Analysis

2017 ◽  
Vol 32 (2) ◽  
pp. 1170-1185 ◽  
Author(s):  
Song Xiong ◽  
Siu-Chung Wong ◽  
Siew-Chong Tan ◽  
Chi K. Tse
Keyword(s):  
Optimal Design ◽  
Path Analysis ◽  
Energy Flow ◽  
Flow Path ◽  
Switched Capacitor

Effects of Parameters Variation of Fractal Flow Path on the Emitter Hydraulic Performance with Path Analysis

2013 ◽  
Vol 397-400 ◽  
pp. 222-229
Author(s):  
Peng Song ◽  
Pei Ling Yang ◽  
Fei Peng Xu ◽  
Chun Fa Zhou
Keyword(s):  
Path Analysis ◽  
Drip Irrigation ◽  
Hydraulic Performance ◽  
Flow Path ◽  
Flow Coefficient ◽  
Performance Parameters ◽  
Section Area ◽  
Tooth Number ◽  
Drip Irrigation Emitter ◽  
Main Factor

Flow path is one of the key components of drip irrigation emitter. Four factors of fractal flow path section area, length, tooth highness and tooth number are interosculated nearly each other, and the influencing process of flow path to hydraulic performance parameters was analyzed with path analysis. The section area and length of the flow path were the main factor affecting on the flow exponent and flow coefficient of drip irrigation emitter, and other ones less. Reducing the section area could debase the emitter flow exponent, and reducing section area and increasing the length of fractal flow path could debase the flow coefficient.

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