Scramjet Isolator Shock-Train Leading-Edge Location Modeling

2011 ◽  
Author(s):  
John Hutzel ◽  
Douglas Decker ◽  
Jeffrey Donbar
Keyword(s):  
Leading Edge ◽  
Shock Train ◽  
Edge Location ◽  
Location Modeling

A method for shock train leading edge detection based on differential pressure

2016 ◽  
Vol 231 (1) ◽  
pp. 61-71 ◽  
Author(s):  
B Xiong ◽  
Z-G Wang ◽  
X-Q Fan ◽  
Y Wang
Keyword(s):  
Standard Deviation ◽  
Edge Detection ◽  
Detection Method ◽  
Pressure Ratio ◽  
Leading Edge ◽  
Differential Pressure ◽  
Shock Train ◽  
Pressure Method ◽  
Operational Application ◽  
Deviation Method

In order to make the shock train leading edge detection method more possible for operational application, a new detection method based on differential pressure signals is introduced in this paper. Firstly, three previous detection methods, including the pressure ratio method, the pressure increase method, and the standard deviation method, have been examined whether they are also applicable for shock train moving at different speeds. Accordingly, three experimental cases of back-pressure changing at different rates were conducted in this paper. The results show that the pressure ratio and the pressure increase method both have acceptable detection accuracy for shock train moving rapidly and slowly, and the standard deviation method is not applicable for rapid shock train movement due to its running time window. Considering the operational application, the differential pressure method is raised and tested in this paper. This detection method has sufficient temporal resolution for rapidly and slowly shock train moving, and can make a real-time detection. In the end, the improvements brought by the differential pressure method have been discussed.

Mechanism of Sequential Swallowing During Straw Drinking in Healthy Young and Older Adults

2004 ◽  
Vol 47 (1) ◽  
pp. 33-45 ◽  
Author(s):  
Stephanie K. Daniels ◽  
David M. Corey ◽  
Leslie D. Hadskey ◽  
Calli Legendre ◽  
Daniel H. Priestly ◽  
...  
Keyword(s):  
Older Adults ◽  
Young Adults ◽  
Movement Patterns ◽  
Leading Edge ◽  
Normal Aging ◽  
Significant Relation ◽  
Age Related ◽  
Laryngeal Penetration ◽  
Airway Invasion ◽  
Edge Location

Recent research has revealed differences between isolated and sequential swallowing in healthy young adults; however, the influence of normal aging on sequential swallowing has not been studied. Thus, the purpose of this investigation was to examine the effects of normal aging on deglutition during sequential straw drinking. Videofluoroscopic samples of two 10-s straw drinking trials were obtained for 20 healthy young men (age 29±3 years) and 18 healthy older men (age 69±7 years). Hyolaryngeal complex (HLC) movement patterns, leading edge of the bolus location at swallow onset, and occurrences of airway invasion were determined. Two HLC patterns were identified: (a) HLC lowering with the epiglottis returned to upright between swallows and (b) partially maintained HLC elevation with the epiglottis inverted between swallows. The bolus was frequently in the hypopharynx at swallow onset. Strong associations were identified between age and HLC pattern, age and leading edge of the bolus location, and HLC pattern and leading edge location. Laryngeal penetration was uncommon overall; however, it occurred more frequently in the older adults than in the young adults. A significant relation was identified between age and the average Penetration-Aspiration Scale score. Laryngeal penetration was associated with both HLC movement patterns and hypopharyngeal bolus location, particularly in older adults. Results indicate that subtle age-related differences are evident in healthy young and older adults with sequential straw drinking. These data suggest that specific inherent swallowing patterns may increase the risk of laryngeal penetration with normal aging.

Elliptic Airfoil Stall Analysis With Trailing Edge Slots

2010 ◽  
Author(s):  
Jonathan Kweder ◽  
Mary Ann Clarke ◽  
James E. Smith
Keyword(s):  
Lift Coefficient ◽  
Leading Edge ◽  
Surface Velocity ◽  
Circulation Control ◽  
West Virginia University ◽  
Trailing Edge ◽  
Near Surface ◽  
Wind Speeds ◽  
Edge Location ◽  
Stall Angle

Circulation control (CC) is a high-lift methodology that can be used on a variety of aerodynamic applications. This technology has been in the research and development phase for over sixty years primarily for fixed wing aircraft where the early models were referred to as “blown flaps”. Circulation control works by increasing the near surface velocity of the airflow over the leading edge and/or trailing edge of a lifting surface This phenomenon keeps the boundary layer jet attached to the wing surface thus increasing the lift generated on the surface. The circulation control airflow adds energy to the lift force through conventional airfoil lift production and by altering the circulation of stream lines around the airfoil. For this study, a 10:1 aspect ratio elliptical airfoil with a chord length of 11.8 inches and a span of 31.5 inches was inserted into the West Virginia University Closed Loop Wind Tunnel and was tested at varying wind speeds (80, 100, and 120 feet per second), angle of attack (zero to sixteen degrees), and blowing coefficients, ranging from 0.0006 to 0.0127 depending on plenum pressure. By comparing the non-circulation controlled wing with the active circulation control data, a trend was found as to the influence of circulation control on the stall characteristics of the wing for trailing edge active control. For this specific case, when the circulation control is in use on the 10:1 elliptical airfoil, the stall angle decreased, from eight degrees to six degrees, while providing a 70% increase in lift coefficient. It should be noted that due to the trailing edge location of the circulation control exit jet, a “virtual” camber is created with the free stream air adding length to the overall airfoil. Due to this phenomena, the actual stall angle measured increased from eight degrees on the un-augmented airfoil, to a maximum of twelve degrees.

scholarly journals Numerical Investigation of the Shock Train in a Scramjet with the Effects of Back-Pressure and Divergent Angles

2020 ◽  
Author(s):  
Santhosh Kumar Gugulothu ◽  
B. Bhaskar ◽  
V.V. Phani Babu
Keyword(s):  
Shock Wave ◽  
Transport Model ◽  
Wave Train ◽  
Leading Edge ◽  
Single Step ◽  
Back Pressure ◽  
Divergence Angle ◽  
Shock Train ◽  
Navier Stokes Equation ◽  
Ansys Fluent

Numerical simulations are carried out to study the effect of divergence angle and adverse pressure gradient on the movement of shock wave train in a scramjet isolator. The commercial software tool ANSYS Fluent 16 was used to simplify two dimensional Reynolds averaged Navier Stokes equation with compressible fluid flow by considering the density-based solver with standard K-ε turbulence model. The species transport model with single step volumetric reaction mechanism is employed. Initially, the simulated results are validated with experimental results available in open literature. The obtained results show that the variation of the divergence angle and back pressure on the scramjet isolator has greater significance on the flow field. Also, with an increase in the back pressure, due to the intense turbulent combustion, the shock wave train developed should expand along the length and also moves towards the leading edge of the isolator leading to rapid rise in the pressure so that the pressure at the entrance of the isolator can match the enhanced back pressures.

Shock Train Leading Edge Detection in a Dual-Mode Scramjet

2006 ◽  
Author(s):  
Daniel Le ◽  
Christopher Goyne ◽  
Roland Krauss ◽  
James McDaniel
Keyword(s):  
Edge Detection ◽  
Leading Edge ◽  
Shock Train ◽  
Dual Mode

scholarly journals Aerodynamic Design Optimization of a Micro Radial Compressor of a Turbocharger

Energies ◽  
2018 ◽  
Vol 11 (7) ◽  
pp. 1827 ◽  
Author(s):  
Omer Atac ◽  
Jeong-Eui Yun ◽  
Taehyun Noh
Keyword(s):  
Design Optimization ◽  
Beta Distribution ◽  
Gasoline Engine ◽  
Leading Edge ◽  
Meridional Plane ◽  
Total Efficiency ◽  
Aerodynamic Design ◽  
Radial Compressor ◽  
Aerodynamic Design Optimization ◽  
Edge Location

This study presents an aerodynamic design optimization of a micro radial compressor impeller on a turbocharger used in a 0.8 L two-cylinder gasoline engine. In the conventional design optimization of the impeller, the hub and shroud curve of the main blade is commonly parameterized with a beta distribution, and splitter blades are generally considered short versions of the full blade. However, geometrical parameterizations in our study mainly focus on the beta distribution of a full blade, and it is parameterized differently from the conventional way. Eight parameters are selected as design variables for the beta distribution. To maximize the isentropic efficiency, design points that are created by Design of Experiment (DOE) are evaluated through single-objective optimization coupled with a non-parametric regression surrogate model. Furthermore, the splitter leading edge location on the meridional plane is investigated to enhance the performance of the impeller after the optimization process. The results show that total efficiency enhancement of approximately 2.2% is achieved. Furthermore, the findings show that a full blade beta distribution and the splitter leading edge location are sufficient parameters to optimize the impeller, and, with the proposed optimization, splitter blades are no longer copies of the full blade for each application.

Analysis of Noise Generated by Low Solidity Cascade Diffuser in a Centrifugal Blower

2008 ◽  
Author(s):  
Daisaku Sakaguchi ◽  
Masahiro Ishida ◽  
Hironobu Ueki ◽  
Hiroshi Hayami ◽  
Yasutoshi Senoo
Keyword(s):  
Flow Rate ◽  
Leading Edge ◽  
Broadband Noise ◽  
Frequency Noise ◽  
Centrifugal Blower ◽  
Discrete Frequency ◽  
Edge Location ◽  
Rotating Impeller ◽  
Low Solidity Cascade Diffuser ◽  
Blade Leading Edge

This paper deals with the effect of the blade leading edge location (RLSD) of a low solidity cascade diffuser (LSD) on noise and diffuser performance in a centrifugal blower. The noise of the LSD was measured and analyzed comparing with that of vaneless diffuser (VLD) in view points of overall noise, discrete frequency noise and broadband noise. The numerical flow analysis was conducted in the impeller and the diffuser by using a Navier-Stokes solver. The noise of the VLD varied little in a wide flow rate range, on the other hand, that of the LSD increased remarkably in the small flow rate by about 7 dB. The noise of the LSD did not increase near the design flow and was almost equal to that of the VLD. It was found that the increase in noise due to LSD is dependent mainly on the broadband noise between 600∼1000Hz, which was closely correlated to the lift force of the LSD blade. The two kinds of discrete frequency noise appeared due to an interaction between the rotating impeller and the LSD blade and another interaction between the rotating impeller blades and the reverse flow toward the impeller exit, but their influence on the overall noise were relatively small. By shifting the LSD blade leading edge location downstream from RLSD = 1.1 to 1.2, the noise was reduced by about 3 dB at the maximum without deterioration of the diffuser performance. The maximum lift coefficient of the LSD blade was achieved as high as 1.5 at the high attack angle of 17 degrees even in the case of RLSD = 1.2, resulting in improvement of the diffuser performance by about 40% and in reduction of the unstable flow range by about 11%.

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