Abstract
A 2D hypersonic vehicle shape with an idealized scramjet is designed at a cruise regime: Mach number (Ma) = 8.0, Angle of attack (AOA) = 0 deg and altitude ([Formula: see text]) = 30kms. Then a multi-objective design optimization of the 2D vehicle is carried out by using a Pareto Non-dominated Sorting Genetic Algorithm II (NSGA-II). In the optimization process, the flow around the air-breathing vehicle is simulated by inviscid Euler equations using FLUENT software and the combustion in the combustor is modeled by a methodology based on the well known combination effects of area-varying pipe flow and heat transfer pipe flow. Optimization results reveal tradeoffs among total pressure recovery coefficient of forebody, lift to drag ratio of vehicle, specific impulse of scramjet engine and the maximum temperature on the surface of vehicle.
Highlights
At present, hypersonic vehicle has been the hotspot of strategic and tactical competition of the world's major aviation and space powers for its high flight speed, good mobility, long-distance strike capacity, etc
In order to decrease the design cost and improve the design efficiency, the optimization model is designed in parallel pattern, that is, the optimization process is finished in a high performance computing environment of 24 cores and executes in parallel of 6 runs at one time
In this paper, a 2D hypersonic air-breathing vehicle shape with an idealized scramjet is designed at cruise regime: Mach number (Ma)=8.0, Angle of attack (AOA)=0 deg and H=30 km
Summary
Hypersonic vehicle has been the hotspot of strategic and tactical competition of the world's major aviation and space powers for its high flight speed, good mobility, long-distance strike capacity, etc. It is uncovered that the aerodynamic integrated design of scramjet is one of the most challenging tasks because the hypersonic propulsion system is strongly coupled with the vehicle airframe, and the three basic components of a scramjet, i.e. inlet, combustor, and nozzle, interact and influence each other. The preliminary design of hypersonic vehicle requires an integrated design that includes some crucial target This is an Open Access article published by World Scientific Publishing Company. Under the specified cruise regime, given a constant height of vehicle H0, for a group vehicle shape design variables x=[ , , , sp, Lsp, aft]T, the configuration of hypersonic vehicle can be determined with a cruise fuel/gas ratio fcruise. The full view pressure contour of one sample is shown in Fig.[5], the result reveals that the developed integrated design methodology can meet the design requirements well
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