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1: Force vectors on an airfoil The drag FD and lift FL are represented in terms of two dimensionless coefficients: the drag coefficient and Lift coefficient, defined as í µí° ¶ í µí°· = í µí°¹ í µí°·

1: Force vectors on an airfoil The drag FD and lift FL are represented in terms of two dimensionless coefficients: the drag coefficient and Lift coefficient, defined as í µí° ¶ í µí°· = í µí°¹ í µí°·

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Conference Paper
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The target of this work was to explore the lift and drag attributes of a NACA 0015 airfoil with a regressive confronting step. For a free stream speed of 30m/s, the purpose of partition was resolved through CFD investigation for an expanding approach. A backward-facing step was then acquainted only earlier with the purpose of detachment which stret...

Citations

... He showed by adding backward-facing steps in NACA-0012 the aerodynamics performance can be enhanced. Besides, NACA-0012, the idea of adding backward-facing steps was also studied using NACA-0015 by many researchers (Kabir, Chowdhury, et al. 2019). In 1975, Kasper first claimed to use the vortex generated glider called Kasper tailless glider and his research showed the possibility of an aircraft with safety, economy, stability, and STOL (Short Takeoff and landing) capability (Kasper 1975). ...
Article
Full-text available
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.
... He showed by adding backward-facing steps in NACA-0012 the aerodynamics performance can be enhanced. Besides, NACA-0012, the idea of adding backward-facing steps was also studied using NACA-0015 by many researchers (Kabir, Chowdhury, et al. 2019). In 1975, Kasper first claimed to use the vortex generated glider called Kasper tailless glider and his research showed the possibility of an aircraft with safety, economy, stability, and STOL (Short Takeoff and landing) capability (Kasper 1975). ...
Preprint
Full-text available
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.
... The information got by Zhak [8] has demonstrated the laminar-fierce stream progress inside a rectangular depression can happen by means of the particular system of the Taylor-Görtler insecurity. Other than Mahdi [9] and Asif [10,11] have all likewise utilized a wide scope of Reynolds numbers for the NACA arrangement airfoil. As wind currents over an indented surface treatment, for example, a dimple or depression, a perplexing stream design creates. ...
Conference Paper
Full-text available
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.
... There have also been works on the flow separations associated with airfoils and humps, resulting in low aerodynamic performances [10]. Voona et al. [11] and Asif et al. [12,13] present in a detailed study of a stepped airfoil with different configurations. Boroomand et al. [14] present a study on backward-facing step airfoil and its efficiency for a large Reynold number flow. ...
Conference Paper
Full-text available
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.
... The information gotten by Zhak [5] have demonstrated the laminar-tempestuous stream progress inside a rectangular depression can happen by means of the particular instrument of the Taylor-Görtler flimsiness. Other than Mahdi [6] and Asif [7,8] have all likewise utilized a wide scope of Reynolds numbers for NACA arrangement airfoil. As wind streams over an indented surface treatment, for example, a dimple or notch, an intricate stream example creates. ...
Conference Paper
Full-text available
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.
Conference Paper
Full-text available
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 effects of change in the physical parameter for the Double wedge airfoil for the different range of Mach number with varying angle of attack. Thermodynamic parameters are studied for two different Double wedge airfoils with half wedge angle 50 and 100 respectively. Double wedge airfoil is analyzed at different angles of attack (AOA). The analysis is done using ANSYS fluent and the k-ε turbulence modeling method is carried out. Numerical simulated data was generated by using Tecplot. From the simulated result, the coefficient of Lift and Drag has been seen to decrease with the increase in Mach number and decrease in AOA. For same Mach number, increase in half wedge angle increases shock and expansion waves at 00 AONA. And pressure coefficient (Cp) increases in the first half region and decreases in the second half region of the wedge with the increase in half wedge angle.