Air Intake Development for Supersonic Missiles

Abstract

For super- and hypersonic air-breathing propulsion, the air intake can be regarded as the key component which is responsible for the performance of the propulsion sub-system (PSS). Here, performance means the achievable thrust (via captured air mass flow and total pressure recovery), distance from buzz and/or backflow (i.e.: stability of the system represented by its ability to allow “a certain amount” of so called sub-critical spillage), and its drag, namely in the below shock-on-lip Mach number regime and, especially, in the transition regime where missile switches from the booster driven acceleration phase to the air-breathing propulsion system powered sustain phase. For this purpose, Bayern-Chemie has developed a wide range of air-intakes which cover all applications of supersonic air-breathing missile propulsion, ranging from air-to-ground, anti-radar missile, and ship-to-ship applications up to advanced, highly maneuverable beyond visual range air-to-air missiles. The types and configurations of air-intakes cover a broad design Mach number range (shock-on-lip Mach number) as well as various types of rotational-symmetric and two-dimensional air intakes, mounted to the fuselage of the missile in various positions (inverted, radial, perpendicular), and so-called chin-inlets, shrouding the missile fore-body (conical section of ogive-shaped nose) to a certain amount. On the base of the experiences gained, this article will present the results of various airintake development programs and the resulting findings with respect to performance (isolated and integrated), stability, and spillage and bleed drag.