Abstract
In this research paper, investigations of counter flow (opposing) jet on the aerodynamic performance, and flight stability characteristics of an airfoil with blunt leading-edge in supersonic regime are performed. Unsteady Reynolds-Averaged Navier-Stokes ( U R A N S ) based solver is used to model the flow field. The effect of angle of attack ( α ), free-stream Mach number ( M ∞ ), and pressure ratio ( P R ) on aerodynamic performance of airfoil with and without jet are compared. The results indicate that the opposing jet reduces drag from 30 % to 70 % , improves the maximum lift-to-drag ratio from 2.5 to 4.0, and increases shock stand-off distance from 15 % to 35 % depending on flow conditions. The effect of opposing jet on longitudinal flight stability characteristics, studied for the first time, indicate improvement in dynamic stability coefficients ( C m q + C m α ˙ ) at low angles of attack. It is concluded that the opposing jet can help mitigate flight disturbances in supersonic regime.
Highlights
The typical objectives of commercial aeronautics research during the twentieth century were centered around achieving long range, high altitude and speed
The wave drag is a specific problem of a supersonic flight, which contributes more than half of the total drag and increases rapidly with increasing free stream Mach number
The purpose is to reduce the drag from the surface of airfoil (NACA 0012) and to improve the understanding of some fundamental phenomena like effects of pressure ratios, free stream flow Mach number and their combined effects with increasing angle of attack
Summary
The typical objectives of commercial aeronautics research during the twentieth century were centered around achieving long range, high altitude and speed. The wave drag is a specific problem of a supersonic flight, which contributes more than half of the total drag and increases rapidly with increasing free stream Mach number This increase in drag value builds up high temperature and pressure that may damage the leading edge of the blunt body and it must be prevented [3]. The purpose is to reduce the drag from the surface of airfoil (NACA 0012) and to improve the understanding of some fundamental phenomena like effects of pressure ratios, free stream flow Mach number and their combined effects with increasing angle of attack. These phenomena affect the ejection of opposing jet and stability parameters of airfoil.
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