![]() ![]() Based on these methods, two subsonic stages of a 4.5-stage transonic research compressor are redesigned. Or, You can subscribe other items from ( Click here to see other items list. Together with the airfoil geometry, the database stores automatically calibrated correlations which describe the cascade performance in throughflow calculation. For Information regarding subscription please click here.įor a comprehensive list of other publications available on please click here Your current subscription does not entitle you to view this content or Abstract is unavailable, the access to full-text of this Article/Journal has been denied. Supersonic, Shock Wave, Cusped, Leading Edge, Aerodynamic Centre, Stalling. Usually the supersonic region of the flow is terminated by a shock wave, allowing the flow to slow down to subsonic speeds. Comparison of the stalling characteristics and the aerodynamic centre coordinates with the existing NACA supersonic airfoils validates our data. Airfoils and Wings 7.1 Introduction Transonic flow occurs when there is mixed sub- and supersonic local flow in the same flowfield (typically with freestream Mach numbers from M 0.6 or 0.7 to 1.2). For such values of angle of attack where the characteristics of C N vs α are linear, the aerodynamic centre is nearly independent of the angle of attack. Furthermore, the aerodynamic centre lies on the chord with varying coordinates along the chord with respect to angle of attack. The stalling characteristics as derived from lift to drag ratio have been found to occur at around α = 4° at M= 1.25, α = 6° at M=1.85 and α =6° at M = 2.13 which is in accordance with the designs of NACA supersonic airfoils. Different angles of attack given as α=4°, 8°, 12°, 16°, 24° and 30° are considered for the study. The constant value of Reynolds number is taken as 5x105 and the Mach numbers considered are 1.25, 1.85 and 2.13. focus of the present work is to find out the effects of variation of Mach number in supersonic regime, and angle of attack at a constant value of Reynolds number on the location of aerodynamic centre and stalling characteristics. The specific aerofoil geometry with a maximum thickness of 10-percent of chord located at 75percent of the chord is considered. The numerical investigation involves modelling the flow as two-dimensional unsteady, viscous and laminar compressible flow around a new design of cusped leading edge airfoil. In this paper we have analyzed one such design with cusped leading edge. Various designs of airfoils have been proposed to reduce the drag considerably in the supersonic flow regime by the mitigation of shock waves. Of Mechanical Engineering, Aligarh Muslim University, Aligarh, (UP) Determination of aerodynamic centre location and stalling characteristics of a new cusped leading edge airfoilīader Shujaut Hussain *, Akhtar Sharique, Azeem Faisalĭeptt. ![]()
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