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The aerodynamic analysis primarily focusses on choosing airfoil shapes to obtain better physical performance. Various shapes of the airfoil are being studied to attain a better and safer flight with the highest possible performance. On them, double wedge airfoils have different types of shocks at higher speeds. This paper aims to present the effect...
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... shows calm standard impacts at subsonic paces, however, at higher rates, DWA results in various types of stuns and sharp changes with a little change in physical parameters which makes this streamlined investigation fascinating. Fig 3 demonstrates that qualities to pursue the pattern. Stuns and unsettling influences raise incredible arrangements of significance in supersonic velocities, it is basic to think about on various types of airfoil form to get an airfoil with higher and productive execution and with less unfriendly impacts like shocks. ...
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... There are many different types of airfoils such as symmetric, nonsymmetrical airfoils, blade twist, wedge shape airfoils, stepped, etc. and they have different use depending on their shape. For example, a double wedge shape airfoil is used for space programs because it can produce a higher Mach number in the hypersonic range (Kabir, Hossain, et al. 2019). ...
This research predominantly centers on the streamlined qualities of Kline-Fogleman modified (KFm) airfoil. KFm arrangement airfoil family shows improved strength and low stalling which has made it quite popular for low weight conveying flight. Some of the major streamlined attributes like lift coefficient, drag coefficient, etc. of KFm-1, KFm-2, and KFm-3 have been explored and a correlation is made with the NACA 4415 airfoil. Spalart-Allmaras disturbance model is applied to the ANSYS Fluent commercial software. The setup is analyzed at a different angle of attack (AOA) methodologies stretching out from 0˚ to 15˚ and for a variety of Mach numbers ranging from 0.3 to 0.6. The Reynolds number was 3.18 ×10 5. The purpose of this division was to reduce computational costs while utilizing CFD software. Computational assessments were coordinated to explore the streamlined presentation of the airfoil. The results highlighted that a steady and gradual increase in lift is possible by introducing the backward step. The overall aim of this assessment was to numerically inspect whether the streamlined execution of an airfoil can be improved by introducing a backward-facing step on the upper surface of the airfoil.
... There are many different types of airfoils such as symmetric, nonsymmetrical airfoils, blade twist, wedge shape airfoils, stepped, etc. and they have different use depending on their shape. For example, a double wedge shape airfoil is used for space programs because it can produce a higher Mach number in the hypersonic range (Kabir, Hossain, et al. 2019). ...
This research predominantly centers on the streamlined qualities of Kline-Fogleman modified (KFm) airfoil. KFm arrangement airfoil family shows improved strength and low stalling which has made it quite popular for low weight conveying flight. Some of the major streamlined attributes like lift coefficient, drag coefficient, etc. of KFm-1, KFm-2, and KFm-3 have been explored and a correlation is made with the NACA 4415 airfoil. Spalart-Allmaras disturbance model is applied to the ANSYS Fluent commercial software. The setup is analyzed at a different angle of attack (AOA) methodologies stretching out from 0˚ to 15˚ and for a variety of Mach numbers ranging from 0.3 to 0.6. The Reynolds number was 3.18 ×10 5. The purpose of this division was to reduce computational costs while utilizing CFD software. Computational assessments were coordinated to explore the streamlined presentation of the airfoil. The results highlighted that a steady and gradual increase in lift is possible by introducing the backward step. The overall aim of this assessment was to numerically inspect whether the streamlined execution of an airfoil can be improved by introducing a backward-facing step on the upper surface of the airfoil.
... Hence, the KFm airfoil has the potential design to maneuver over a long range of flight. To reach a higher Mach number like hypersonic region researchers used a double wedge airfoil [7]. NACA airfoil series is very popular among others to check to stall [8,9]. ...
This article presents the aerodynamic characteristics of Kline-Fogleman modified (KFm) airfoil. KFm series airfoil family has better stability and low stalling effects which have made its use for low weight carrying flight. Aerodynamic characteristics have been investigated for KFm-1, KFm-2, and KFm-3 followed by a comparison with NACA 4412 airfoil. Spalart-Allmaras turbulence model is employed on the ANSYS Fluent environment due to the transonic flow condition. The numerical simulation was carried out with varying angle of attacks ranging from 0˚to0˚to 15˚. For a variation of mach number extending from 0.3 to 0.6, the point of separation was resolved to employ CFD analysis. Computational examinations were directed to upgrade the aerodynamic performance of the airfoil. The analyzed results demonstrate the aerodynamic performances in terms of drag and lift coefficients, pressure coefficients, static temperature for the various angle of attacks and mach numbers. Moreover, the numerical result of the lift coefficient is compared to the available experimental result in order to validate the carried out numerical simulation. Prevalently the objective of this examination was to numerically decide whether or not the aerodynamic performance of an airfoil can be improved by presenting a retrogressive confronting step on the upper surface of the airfoil.
... This results in a littler wake region and a decrement in the weight drag. Other than a twofold wedge airfoil [7], Mach number was in the supersonic run. ...
This exploration predominantly centers around the streamlined attributes of Kline-Fogleman adjusted (KFm) airfoil. KFm arrangement airfoil family has better dependability and low slowing down which has made its utilization for low weight conveying flight. We have researched some streamlined attributes like lift coefficient, drag coefficient, and so on of KFm-2, and KFm-3 and made an examination with NACA 4412 airfoil. Spalart-Allmaras choppiness model is utilized on the ANSYS Fluent condition as the stream is in the transonic system. This recreation is analyzed at different methodologies like the angle of attack (AOA) reaching out from 0˚to0˚to 15˚. For a variety of Mach numbers reaching out from 0.3 to 0.6, the purpose of partition was made plans to utilize CFD examination. Computational assessments were coordinated to redesign the streamlined exhibition of the airfoil. The results made show that as much as the decrease in drag is possible by introducing the progression. But then, a tad of decrease in the lift was furthermore viewed. Commonly the target of this assessment was to numerically choose whether or not the streamlined execution of an airfoil can be improved by introducing a retrogressive standing up to step on the upper surface of the airfoil.
... This result in a littler wake territory and a decrement in the weight drag. Other than for a twofold wedge airfoil [14], Mach number was in supersonic range. ...
This research portrays a numerical investigation of various aerodynamic properties of Kline-Fogleman airfoils. This type of airfoils is mainly used for designing Unmanned Aerial Vehicles (UAV) which generally operates at low Reynold's number. The objective of this work comprises two geometrically similar airfoils namely NACA-4415 and KFm-2 (Kline-Fogleman modified) based NACA-4415. This research was conducted using the ANSYS Fluent environment under the Spalart-Allmaras turbulence model. The lift to drag ratio was not that kind of satisfactorily improved using the NACA-4415 based KFm-2 model in contrast to just NACA-4415. For a Mach number of 0.6, the point of separation was determined via CFD analysis. Computational studies were led to improve the aerodynamic performance of the airfoil. The results produced show that as much as a 24% reduction in drag is possible by introducing the step. But at the same time, about 11% reduction in the lift was also observed. Predominantly the goal of this research is to numerically determine whether or not the aerodynamic performance of an airfoil can be enhanced by introducing a modified KFm-2 airfoil.
This paper is mainly focused on Supersonic Laminar Flow at Mach 3 for biconvex and double wedge airfoils. The coefficient of lift (Cl), coefficient of drag (Cd), and coefficient of moment along the respective airfoils are being analysed. The geometry of these is generated using the Designmodeler of ANSYS. Further, meshing is also achieved by ANSYS with around 50000 nodes which is satisfactory for the current flow analysis. The total number of iterations being set for the particular simulation is 1000. This article covers the approach of the Kutta-Joukowski theorem, from which we know that flow circulation impacts the lift of the airfoil and how it changes for biconvex and double wedge airfoils. Decisively, this paper delivers provides pressure, heat transfer, and velocity distribution for both the airfoils. This paper gives a comparative study of both the double wedge and the biconvex airfoils at MACH 3, zero angle of attack. The study will be analysing both the airfoils in 3D as well as in 2D.
A Double Wedge airfoil is an airfoil for supersonic blades and wings, with a wedge like tapered sharp leading and trailing edges. The shock waves and the expansion waves govern the supersonic characteristics of the double wedge airfoil. The present work is based on the design and aerodynamic analysis of double wedge airfoil at supersonic regime and shape modification of the airfoil for subsonic regime. The flow analysis is carried out using ANSYS Fluent, which is CFD based software. The supersonic analysis is performed for Mach number of 2.0. The airfoil was modified for subsonic applications and the analysis was performed for Mach number 0.7. Blowing technique was incorporated to further improve the aerodynamic performance of the modified double wedge airfoil. From the simulated results, it was found that the co-efficient of drag of double wedge airfoil at Mach number of 2.0 agreed with the manual calculations. The modified airfoil gave optimum performance with the addition of a blowing stream at subsonic speeds.
