On a Numerical Method for the Simulation of Steady Jet Array Interaction With Rotating Components

2011 ◽  
Author(s):  
Valery Kostege ◽  
Sergey Chernyshev ◽  
Vladimir Vassiliev
Keyword(s):  
Thermal State ◽  
Aerodynamic Characteristics ◽  
Computer Memory ◽  
Tip Vortices ◽  
Elapsed Time ◽  
Theoretical Investigations ◽  
Simplified Method ◽  
Unsteady Effects ◽  
Accurate Computations ◽  
Computing Capacity

Experimental and theoretical investigations show that unsteady effects like moving wakes, tip vortices, passing shocks, pulsating injections and other similar structures significantly affect the aerodynamic characteristics of turbines and compressors. They also influence the thermal state and lifetime of components. Therefore it is very important for designers of turbomachines to properly simulate these effects. On the other hand, time-accurate computations are still expensive and require substantial resources in CPU and computer memory. Moreover the elapsed time is high. However in certain cases the numerical model for unsteady calculations can be simplified, allowing proper capture of the unsteadiness impact, but with much less required computing capacity. This makes the approach acceptable for design applications. Such a simplified method, applicable to a simulation of a steady jets array interaction with rotating components, is described in this paper. The advantages and limitations are discussed, and the validation results and application examples are presented.

scholarly journals Analisis karakteristik aerodinamika telescopic wing dengan konfigurasi sayap flying wing dan glider menggunakan metode pendekatan simulasi CFD

2021 ◽  
Vol 10 (1) ◽  
Author(s):  
Azhim Asyratul Azmi ◽  
Satriawan Dini Hariyanto ◽  
Arif Hidayat
Keyword(s):  
Cfd Simulation ◽  
Fluid Dynamic ◽  
Angle Of Attack ◽  
Leading Edge ◽  
Aerodynamic Characteristics ◽  
Morphing Wing ◽  
Aircraft Wing ◽  
High Lift ◽  
Tip Vortices ◽  
Wing Tip

A telescopic wing is a shape-changing method of the aircraft wing known as the morphing wing system. Wingspan extends capability on telescopic wing increasing the aspect ratio to get a high lift force. The telescopic wing on a flying wing configuration as an external wing and glider wing as an internal wing can be used to increase the coefficient lift (CL) when carrying out special missions. The aerodynamic characteristics using the Computational Fluid Dynamic (CFD) simulation approach is presented. For the 40% internal wingspan, the highest CL increment was 12.9% at a 10o angle of attack. For the 50% internal wingspan, the highest CL increment was 14.9% at a 10o angle of attack. on the 40% internal wing, the highest coefficient drag (CD) increment was 4.7%, and the largest CD increment on 50% internal was 9.5% at the angle of attack of 20o. The pressure distribution along the internal wingspan was uneven from an angle of attack of 15o due to the wing tip vortices of the external wing. Streamline pattern shown a bubble separation from the leading edge at an internal wing root by external wing tip vortices.Keywords: Morphing wing, telescopic wing, flying wing, glider

scholarly journals Investigation of Aerodynamic Characteristics of a Wing Model With RGV Winglet

2020 ◽  
Author(s):  
Sivaraj Gopal Krishnan ◽  
Mohammad Hafifi Ishak ◽  
Mohammad Azwan Nasirudin ◽  
Farzad Ismail
Keyword(s):  
Drag Coefficient ◽  
Lift Coefficient ◽  
Vortex Formation ◽  
Aerodynamic Characteristics ◽  
Contour Plot ◽  
Tip Vortices ◽  
Wing Model ◽  
Plot Analysis ◽  
Computational Fluid Dynamics Cfd ◽  
Drag Ratio

This work describes the aerodynamic characteristics of an aircraft wing model with a Rüppell’s griffon vulture (RGV)-type winglet. A computational fluid dynamics (CFD) study using ANSYS 15.0 was conducted to study the effect of the RGV winglet on a rectangular wing. The NACA 65(3)-218 wing consists of 660 mm span and 121 mm chord length where the aspect ratio is 5.45. Eight different winglet configurations have been studied. Furthermore, the study is extended to study effect of cant angle and different angles of attack (AOA) to the winglet. A comparative study is done on aerodynamic features such as lift coefficient (CL), drag coefficient (CD), lift/drag ratio (CL/CD) and tip vortices to get the best RGV winglet design. The RGV winglet achieved highest CL compared to other types of winglets configuration. Based on contour plot analysis, the RGV winglet shows lower vortex formation compared to without winglet. The results show about 15 to 30% reduction in drag coefficient and 5 to 25% increase in lift coefficient by using an RGV winglet.

Simplified Method to Measure Mouse Fertility

Endocrinology ◽  
2020 ◽  
Vol 161 (8) ◽  
Author(s):  
David J Handelsman ◽  
Kirsty A Walters ◽  
Lam P Ly
Keyword(s):  
Cumulative Number ◽  
Breeding Performance ◽  
Statistical Software ◽  
Fertility Index ◽  
Elapsed Time ◽  
Mating Trial ◽  
Simplified Method ◽  
The Many ◽  
Mouse Lines

Abstract Estimating breeding performance from mouse mating trials has focused on lifetime mating trials, which are too slow and costly for characterizing the many novel genetic mouse lines produced in fertility research, an underpinning of reproductive pathophysiology research. This study introduces the fertility index, defined as the slope of the regression of cumulative number of pups produced by a female over elapsed time in a monogamous mating trial. By using a robust resampling technique, the Theil-Sen estimator (widely available in free or niche statistical software), to estimate the fertility index, the present study of 410 mating trials of mice from 7 genotypes lasting a median of 10 litters shows that it is possible to estimate the fertility index reliably over as few as 4 litters.

Thickness Effect on Low-Aspect-Ratio Wing Aerodynamic Characteristics at a Low Reynolds Number

2008 ◽  
Vol 24 (3) ◽  
pp. 223-228 ◽  
Author(s):  
F. B. Hsiao ◽  
C. Y. Lin ◽  
Y. C. Liu ◽  
D. B. Wang ◽  
C. C. Hsu ◽  
...  
Keyword(s):  
Reynolds Number ◽  
Aspect Ratio ◽  
Low Reynolds Number ◽  
Aerodynamic Characteristics ◽  
Thickness Effect ◽  
Tip Vortices ◽  
Low Aspect Ratio ◽  
Aerodynamic Properties ◽  
Low Reynolds ◽  
Wing Tips

AbstractThis paper presents the study of aerodynamic performance about low-aspect-ratio wings at a low Reynolds number in wind tunnel testing. The aerodynamic properties, including lift, total drag, lift-to-drag ratio and induced drag were measured and analyzed for detailed investigations. Two forms of nonlinear equations of lift curves were reported for comparison. The effect of airfoil thickness was found to be significant on aerodynamic characteristics for all wings tested. The lift due to tip vortices was prominent for wings of AR =1.0 and their stall angles were all larger than 20°, which was mainly augmented by tip vortices shed from the wing tips.

The Effects of Wakes on Aerodynamic Characteristics of Flapping Wings in Clap-and-Fling Motion at Re of ~104

2018 ◽  
Author(s):  
Jong-Seob Han ◽  
Jae-Hung Han
Keyword(s):  
Aerodynamic Force ◽  
Force Production ◽  
Micro Air Vehicles ◽  
Aerodynamic Characteristics ◽  
Flapping Wing ◽  
Flapping Wings ◽  
Water Tank ◽  
Cross Sectional ◽  
Robotic Arms ◽  
Tip Vortices

In this paper, aerodynamic characteristics of two flapping wings in clap-and-fling motion at Re of ∼104, which corresponds to the flight regime of flapping-wing micro air vehicles, was investigated. The test employing dynamically scaled-up robotic arms installed on a water tank revealed that the wingbeat motion at such high Re in1duced the fully developed wake within two wingbeat cycles. This wake widely influenced the lift production covering the entire wingbeat period; the wings earned the additional lift during the entire downstroke, and lost the lift during the upstroke. Chordwise cross-sectional DPIV showed the massive downwash with enlarged tip vortices, when the wake was fully developed. The wake blew down the headwind and reduced the effective angles of attack. In the case of the clap-and-fling motion, the wake was leaned toward the dorsal part, in which the wings created the clap-and-fling motion, causing the global fluctuation of the aerodynamic force production.

scholarly journals Nonlinear Characteristics of Helicopter Rotor Blade Airfoils: An Analytical Evaluation

2013 ◽  
Vol 2013 ◽  
pp. 1-9 ◽  
Author(s):  
Constantin Rotaru
Keyword(s):  
Aerodynamic Characteristics ◽  
Rotor Blades ◽  
Helicopter Rotor ◽  
Apparent Mass ◽  
Nonlinear Characteristics ◽  
Helicopter Rotor Blades ◽  
Helicopter Rotor Blade ◽  
Attached Flow ◽  
Unsteady Effects ◽  
Physical Features

Some results are presented about the study of airloads of the helicopter rotor blades, the aerodynamic characteristics of airfoil sections, the physical features, and the techniques for modeling the unsteady effects found on airfoil operating under nominally attached flow conditions away from stall. The unsteady problem was approached on the basis of Theodorsen's theory, where the aerodynamic response (lift and pitching moment) is considered as a sum of noncirculatory and circulatory parts. The noncirculatory or apparent mass accounts for the pressure forces required to accelerate the fluid in the vicinity of the airfoil. The apparent mass contributions to the forces and pitching moments, which are proportional to the instantaneous motion, are included as part of the quasi-steady result.

Comparison between Methods of Generation of Waveriders Derived from Streamline Tracing and Simplified Method

2013 ◽  
Vol 390 ◽  
pp. 134-140
Author(s):  
Feng Ding ◽  
Jun Liu ◽  
Liang Jin ◽  
Shi Bin Luo
Keyword(s):  
Aerodynamic Characteristics ◽  
Aerodynamic Performance ◽  
High Lift ◽  
Shape Factors ◽  
Simplified Method ◽  
Streamline Tracing ◽  
Simulation Results ◽  
Drag Ratio ◽  
Lift To Drag Ratio ◽  
Tracing Method

Waverider with a high lift-to-drag ratio has drawn an ever increasing attention. Usually, waverider is obtained by tracing streamline. A simplified generation method of waverider is introduced in the present paper named geometric relations method. Three groups of cone-derived waverider configuration, respectively, based on the geometric relations method and the streamline tracing method are generated for the comparisons of the shape factors, inviscid aerodynamic characteristics, and flow field structures by investigating the numerical simulation results. The results show that the effect of the Mach number and the shock angle on the differences caused by the two methods are not significantly different. While the volumetric efficiency of the waverider configuration based on the geometric relations method is larger than those based on the streamline tracing, the inviscid lift-to-drag ratio of the former is less than the latter. Although the geometric relations method is much easier than the streamline tracing method, the simplified method reduces the aerodynamic performance of the waverider configuration.

A simplified method of emulsion coating and development for quantitative electron microscopic radioautography

1978 ◽  
Vol 36 (2) ◽  
pp. 64-65
Author(s):  
K. Yoshida ◽  
F. Murata ◽  
S. Ohno ◽  
T. Nagata
Keyword(s):  
Mass Production ◽  
Identical Condition ◽  
Microscopic Level ◽  
Electron Microscopic Level ◽  
Electron Microscopic ◽  
Simplified Method ◽  
Complicated Process ◽  
Critical Problems ◽  
Electron Microscopic Radioautography ◽  
Quantitative Radioautography

IntroductionSeveral methods of mounting emulsion for radioautography at the electron microscopic level have been reported. From the viewpoint of quantitative radioautography, however, there are many critical problems in the procedure to produce radioautographs. For example, it is necessary to apply and develop emulsions in several experimental groups under an identical condition. Moreover, it is necessary to treat a lot of grids at the same time in the dark room for statistical analysis. Since the complicated process and technical difficulties in these procedures are inadequate to conduct a quantitative analysis of many radioautographs at once, many factors may bring about unexpected results. In order to improve these complicated procedures, a simplified dropping method for mass production of radioautographs under an identical condition was previously reported. However, this procedure was not completely satisfactory from the viewpoint of emulsion homogeneity. This paper reports another improved procedure employing wire loops.

Video Graphics and High-Voltage Electron Microscopy For Analysis of Microtubule Distributions In Fixed Cells

1990 ◽  
Vol 48 (1) ◽  
pp. 524-525
Author(s):  
Richard Mcintosh ◽  
David Mastronarde ◽  
Kent McDonald ◽  
Rubai Ding
Keyword(s):  
Electron Microscopy ◽  
Cross Sections ◽  
Cell Shape ◽  
Video Camera ◽  
Computer Memory ◽  
High Voltage Electron Microscopy ◽  
Thin Sections ◽  
Voltage Electron ◽  
Morphogenetic Event ◽  
Set Of Points

Microtubules (MTs) are cytoplasmic polymers whose dynamics have an influence on cell shape and motility. MTs influence cell behavior both through their growth and disassembly and through the binding of enzymes to their surfaces. In either case, the positions of the MTs change over time as cells grow and develop. We are working on methods to determine where MTs are at different times during either the cell cycle or a morphogenetic event, using thin and thick sections for electron microscopy and computer graphics to model MT distributions.One approach is to track MTs through serial thin sections cut transverse to the MT axis. This work uses a video camera to digitize electron micrographs of cross sections through a MT system and create image files in computer memory. These are aligned and corrected for relative distortions by using the positions of 8 - 10 MTs on adjacent sections to define a general linear transformation that will align and warp adjacent images to an optimum fit. Two hundred MT images are then used to calculate an “average MT”, and this is cross-correlated with each micrograph in the serial set to locate points likely to correspond to MT centers. This set of points is refined through a discriminate analysis that explores each cross correlogram in the neighborhood of every point with a high correlation score.

Rate of Sublimation of Ice by Radiative Heating in Freeze-Etching

1980 ◽  
Vol 38 ◽  
pp. 618-619
Author(s):  
Yeshayahu Talmon
Keyword(s):  
Heat Flux ◽  
Freeze Fracture ◽  
Constant Heat Flux ◽  
Radiative Heating ◽  
Constant Heat ◽  
Entire Sample ◽  
Simplified Method ◽  
Freeze Etching ◽  
Sublimation Rates ◽  
Fractured Surface

To bring out details in the fractured surface of a frozen sample in the freeze fracture/freeze-etch technique,the sample or part of it is warmed to enhance water sublimation.One way to do this is to raise the temperature of the entire sample to about -100°C to -90°C. In this case sublimation rates can be calculated by using plots such as Fig.1 (Talmon and Thomas),or by simplified formulae such as that given by Menold and Liittge. To achieve higher rates of sublimation without heating the entire sample a radiative heater can be used (Echlin et al.). In the present paper a simplified method for the calculation of the rates of sublimation under a constant heat flux F [W/m2] at the surface of the sample from a heater placed directly above the sample is described.

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