Abstract
In this paper, aerodynamic design of biplane airfoils in supersonic flight is discussed based on Computational Fluid Dynamics (CFD). In supersonic flight, airfoils generate strong sonic booms and wave drags accompanied by shock waves. We propose a significant reduction of them, especially wave drags using a biplane-airfoil concept. The background of this concept is originated from Busemann biplane and Licher type biplane concepts. In order to focus on the shock wave characteristics around biplane configuration, inviscid flow (Euler) analyses are performed (which is particularly suitable for wave drag analyses). Design Mach number is 1.7. The aerodynamic design is conducted using an iterative inverse design method that is newly implemented. A biplane configuration having a desired performance has been obtained. Having 0.102 of total maximum thickness ratio (t/c), it has the lift to wave drag ratio (L/D) of 21.7 at a desired lift condition for supersonic flight, lift coefficient (Cl)=0.115. At the range of lift coefficient more than 0.144 this designed biplane has lower wave drag than that of a (zero-thickness) single flat plate airfoil.
Published Version
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