Determination of Aerodynamic Characteristics of NACA 0012 Using ANSYS for High Subsonic Flow

2020 ◽  
Author(s):  
Kartik Agrawal ◽  
Mamta Patel ◽  
Vaibhav Shah ◽  
Jigar Sura
Keyword(s):  
Subsonic Flow ◽  
Aerodynamic Characteristics ◽  
Naca 0012 ◽  
High Subsonic Flow

Unsteady Aerodynamic Characteristics of Oscillating Cascade With Separation Bubble in High Subsonic Flow

2005 ◽  
Author(s):  
Toshinori Watanabe ◽  
Mizuho Aotsuka
Keyword(s):  
Subsonic Flow ◽  
Separation Bubble ◽  
Leading Edge ◽  
Aerodynamic Characteristics ◽  
Influence Coefficient ◽  
Unsteady Aerodynamic ◽  
Key Factor ◽  
Influence Coefficient Method ◽  
Airfoil Blades ◽  
High Subsonic Flow

Unsteady aerodynamic characteristics of an oscillating cascade composed of DCA (Double Circular Arc airfoil) blades were studied both experimentally and numerically. The test cascade was operated in high subsonic flow fields with incidence angles up to 5 degrees. Above 3 degrees of the incidence, a separation bubble was produced at the leading edge. The principal concern of the present study was placed on the influence of the separated region on the vibration instability of the cascade blades. The experiment was conducted in a linear cascade wind tunnel in which seven DCA blades were equipped. The central one could be oscillated in a pitching mode. The influence coefficient method was adopted for the measurement, where the unsteady aerodynamic moments were measured on the central blade and neighboring ones. For the numerical analysis, a quasi 3-D N-S code with k–ε turbulence model was developed. The experimental and numerical results complemented each other to obtain detailed understanding of the unsteady aerodynamic behavior of the cascade. It was found that the separation bubble at the leading edge governed the vibration characteristics of blades through the oscillation of the separation bubble itself on the blade surfaces. From the results of parametric studies, the phase shift of the oscillation of the separation bubble was found to be a key factor for determining the unsteady aerodynamic characteristics of the oscillating blades.

A Comparison of Two Integral Equation Methods for High Subsonic Lifting Flows

1975 ◽  
Vol 26 (1) ◽  
pp. 56-58 ◽  
Author(s):  
D Nixon
Keyword(s):  
Integral Equation ◽  
Unique Solution ◽  
Subsonic Flow ◽  
Integral Equation Methods ◽  
High Subsonic Flow

SummaryA comparison is made of two recently published integral equation methods for calculating the high subsonic flow around lifting and non-lifting aerofoils. It is shown that one method leads to a non-unique solution.

scholarly journals DETERMINATION OF THE AERODYNAMIC CHARACTERISTICS FOR AGRICULTURAL UAVS IN UNSTEADY FLOW

2015 ◽  
Vol 0 (11) ◽  
pp. 40-47
Author(s):  
Дмитрій Миколайович Зінченко ◽  
Олексій В. Седневець
Keyword(s):  
Unsteady Flow ◽  
Aerodynamic Characteristics

scholarly journals Numerical Analysis of the Effects of the Geometric and Weight Parameters on the Exterior Ballistics of a Designed Counterprojectile

2017 ◽  
Vol 8 (1) ◽  
pp. 89-100
Author(s):  
Jakub MICHALSKI ◽  
Zbigniew SURMA ◽  
Marta CZYŻEWSKA
Keyword(s):  
Aerodynamic Characteristics ◽  
Protection System ◽  
Software Environment ◽  
Active Protection ◽  
Protected Object ◽  
Motion Parameters ◽  
Exterior Ballistics ◽  
Technology Demonstrator ◽  
Selection Of

This paper presents a selection of deliverables of a research project intended to develop a technology demonstrator for an active protection system smart counterprojectile. Numerical simulations were completed to analyse the effects of geometry and weight of the counterprojectile warhead on the counterprojectile flight (motion) parameters. This paper investigates four variants of the counterprojectile warhead shape and three variants of the counterprojectile warhead weight. Given the investigated geometric and weight variants, the PRODAS software environment was used to develop geometric models of the counterprojectile warhead, followed by the determination of the model aerodynamic characteristics. The final deliverable of this work are the results of the numerical simulation of the counterprojectile motion along the initial flight path length. Given the required activation of the active protection system in direct proximity of the protected object, the analyses of counterprojectile motion parameters were restricted to a distance of ten-odd metres from the counterprojectile launching system.

Determination of an oblique wing aircraft's aerodynamic characteristics

1980 ◽  
Author(s):  
R. TRAVASSOS ◽  
N. GUPTA ◽  
K. ILIFF ◽  
R. MAINE
Keyword(s):  
Aerodynamic Characteristics

Computational Analysis of Airfoil Merging and its Effect on Performance of Lift Based Vertical Axis Wind Turbine

2016 ◽  
Author(s):  
Akshay Basavaraj
Keyword(s):  
Reynolds Number ◽  
Wind Turbine ◽  
Lift Coefficient ◽  
Turbine Blades ◽  
Vertical Axis ◽  
Aerodynamic Characteristics ◽  
Vertical Axis Wind Turbine ◽  
Low Wind Speed ◽  
Naca 0012 ◽  
Selection Of

In regions of low wind speed, overcoming the starting torque of a Vertical Axis Wind Turbine (VAWT) becomes a challenge aspect. In order to overcome this adversity, careful selection of airfoils for the turbine blades becomes a priority. This paper tries to address the issue utilizing an approach wherein by observing the effect of merging two airfoils. Two airfoils which are of varying camber and thickness are merged and their aerodynamic characteristics are evaluated using the software XFOIL 6.96. For a variation in angle of attack from 0 to 90°, aerodynamic analysis is done in order to observe the behavior of one quarter of the entire VAWT cycle. An objective function is developed so as to observe the maximum possible torque generated by these airfoils at Reynolds number varying from 15,000–120,000. Due to change in the value of CL observed at Low Reynolds Number using commercial CFD softwares, multiple objective functions are utilized to observe the behavior over a range of Reynolds number. An experimental co-relation between the cut-in velocity and the lift-coefficient of the airfoils is developed in order to predict the cut-in velocity of the interpolated airfoils. The airfoils used for this paper are NACA 0012, NACA 0018, FX 66 S196, Clark Y (smooth), PT 40, SD 7032, A 18, SD 7080, SG 6043 and SG 6040.

Experimental Study on Aerodynamic Characteristics for Missile Configuration With Grid Fins in Subsonic Flow

2021 ◽  
Vol 49 (9) ◽  
pp. 721-727
Author(s):  
Yeongbin Lee ◽  
Changgu Lee ◽  
Jonggeon Lee ◽  
Sungcheol Kim ◽  
Namgyun Kim
Keyword(s):  
Experimental Study ◽  
Subsonic Flow ◽  
Aerodynamic Characteristics

Experimental analysis of cell pattern on grid fin aerodynamics in subsonic flow

2019 ◽  
Vol 234 (3) ◽  
pp. 537-562
Author(s):  
Manish Tripathi ◽  
Mahesh M Sucheendran ◽  
Ajay Misra
Keyword(s):  
Subsonic Flow ◽  
Lift Coefficient ◽  
Aerodynamic Performance ◽  
Aerodynamic Efficiency ◽  
Grid Fin ◽  
Stall Angle ◽  
The Individual ◽  
The Impact ◽  
Control Surfaces

Grid fins consisting of a lattice of high aspect ratio planar members encompassed by an outer frame are unconventional control surfaces used on numerous missiles and bombs due to their enhanced lifting characteristics at high angles of attack and across wider Mach number regimes. The current paper accomplishes and compares the effect of different grid fin patterns on subsonic flow aerodynamics of grid fins by virtue of the determination of their respective aerodynamic forces. Furthermore, this study deliberates the impact of gap variation on aerodynamics of different patterns. Results enunciate enhanced aerodynamic efficiency, and lift slope for web-fin cells and single diamond patterns compared to the baseline model. Moreover, the study indicates improved aerodynamic performance for diamond patterns with higher gaps by providing elevated maximum lift coefficient, delayed stall angle, and comparable drag at lower angles. The study established the presence of an additional effect termed as the inclination effect alongside the cascade effect leading to deviations with respect to lift, stall, and aerodynamic efficiency amongst different gap variants of the individual patterns. Thus, optimization based on the aerodynamic efficiency, stall angle requirements, and construction cost by optimum pattern and gap selection can be carried out through this analysis, which can lead to elevated aerodynamic performance for grid fins.

scholarly journals The study of the aerodynamic characteristics of dust particles in the air of roadside areas

2019 ◽  
Vol 126 ◽  
pp. 00071
Author(s):  
Anatoly Vasiliev ◽  
Igor Stefanenko ◽  
Valery Azarov ◽  
Denis Nikolenko
Keyword(s):  
Aerodynamic Characteristics ◽  
Dust Particles

The article addresses issues, which are related to the determination of aerodynamic characteristics of dust particles in roadside air areas. Was studied dustiness of Volgograd roadside areas.

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