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Fundamental features of aerodynamic interference and integration of airframes and air-breathing jet engines for high-speed flight vehicles are studied within the framework of supersonic small perturbation theory. Both the influence of airframe components on air intakes performance and influence of intakes on vehicle external aerodynamics are under consideration. Analytical relations and specific examples show that significant favorable interference between airframes and air intakes can be realized by using preliminary compression of the flow in front of intakes at flight Mach numbers exceeding approximately 3.

The influence of flow spillage before air intake on external aerodynamic characteristics of an aircraft with air-breathing jet engine is studied using CFD tools based on NavierStokes and Euler models. Geometry of the considering vehicle corresponds to one of the versions of the experimental flight test vehicle (EFTV) derived from the LAPCAT-MR2 high-speed passenger cruiser. Research has been performed for Mach number range from 5 to 8 and angles-of-attack from -2° to 8°. It has been shown that the impact of flow spillage on vehicle aerodynamics is significant, and it worth taking into account at the stage of choosing aerodynamic configuration and control system.mass flow rate coefficient 1 = vector of flow momentum at an intake entry 2 = vector of flow momentum at a nozzle exit ∞ = initial vector of momentum of a stream-tube passing through an engine I ∞ = absolute value of the vector I ∞ L = length of a vehicle M ∞ = free-stream Mach number M Σ = resultant aerodynamic moment acting on a vehicle n 1 = unit normal vector to the surface S 1 (directed inwards) n 2 = unit normal vector to the surface S 2 (directed outwards) n w = unit normal vector to the surface S w (directed outwards) Re = Reynolds number p = static pressure p ∞ = static pressure in the free stream R A = external aerodynamic force R Σ = resultant aerodynamic force acting on a vehicle S 0 = intake capture area S 1 = control surface at an intake entry S 2 = control surface at a nozzle exit S w = external surface of a vehicle r = vector from CoG of a vehicle to the considering point T = engine thrust u = flow velocity component in the x direction U ∞ = absolute value of a free-stream flow velocity V = vector of flow velocity1 Head of department, Aerodynamics, anatoly.gubanov@tsagi.ru, not a member of the AIAA. 2 Researcher, Aerodynamics, dmitriy.ivanushkin@tsagi.ru, not a member of the AIAA. 3 Head of sector, Aerodynamics, nina.voevodenko@tsagi.ru, not a member of the AIAA. Downloaded by UNIVERSITY OF ILLINOIS on October 1, 2015 | http://arc.aiaa.org | 2 x = longitudinal direction along the reference axis of a vehicle x a = longitudinal direction along the free stream z a = vertical direction (upwards, normally to the free stream)  = angle-of-attack τ w = local vector of skin friction stress