Calculating Method Of Aerodynamic Heating For Hypersonic Aircrafts

Research on the calculating method of aerodynamic heating for hypersonic aircrafts, usinginviscid outflow solution combined with engineering method. Considering the high temperaturechemical non-equilibrium effect and the structure heating coupling effect, this calculating method canapply to rapid compute aerodynamic heating for hypersonic aircraft, giving the aerodynamic heatingheatflux distribution and the heat-protect surface layer temperature distribution. Research results canprovide technicial support for hypersonic aircraft design about the thermal characteristics ofaerodynamic heating.At present, aerodynamic heating calculating basically have two basic method.It is respectivelythe flowfield numerical simulation technology and engineering method. Numerical simulation methodis by solving Navier-Stokes equation and all kinds of simplified form to calculate aircraft surfaceheatflux, but if coupled heat-transfer structure calculation, then the numerical calculation is hugelyexpensive, and the development cycle is very long. Engineering method for the aerodynamic heatingprocess is very simple, and very efficient, so develop very quickly. But engineering method also hasits limitations, such as calculating the outer boundary layer parameters based on experiencecalculation, calculating complex aircraft appearance (such as crack, bulges, irregular shape.etc) andthe results of the correction also need a lot of engineering experience for the foundation.Therefore, integrated computation efficiency and precision, this paper developed a new approachwhich coupled numerical simulation technology and engineering method.This approach can calculatehypersonic vehicle surface heatflux distribution combining with the structure heat transfer，and can beused for ballistic or unsteady aircraft aerodynamic heat calculating and analysis.So this methodcombines the numerical simulation and engineering method with the high efficiency and precision,which can be used for the complex ballistic and complicated appearance aircraft design.The calculation results show that this new approach can meet the design requirement for thehypersonic aircraft design, can be used for hypersonic vehicle aerodynamic heating scheme selectiondesign and thermal characteristic analysis research.