Waverider Configuration Design、Optimization And Numerical Simulation Of Aerospace Plane

The pursuit of much higher, much faster, much further to the vehicle has beencontinuing to encourage those astronautic scientists make further study. In the newcentury, the need of military, civil aviation has put forward the aerospacetechnology to a much higher level of request. It is difficult to meet the needs ofaerospace because of the traditional shuttle’s high cost, bad reusability, complexsystem and other factors. In order to save costs, improve the vehicle can be reused,greatly reduces the cost of the satellite launch, in order to adapt to the new centuryand the requirement of the military, aerospace plane concept emerges as the timesrequire. It is a collection of aviation and spaceflight advantage， becomes thefuture direction of the development of aerospace technology, aerospace powercaused each attention, and gradually carry out research work.Due to the very high speed of the space flight, the mach number reaches to5~25, so it is very important that the aerodynamic configuration has thecharacteristic of lower drag, higher lift. This paper focused on the study ofhypersonic waverider configuration, and on the basis of the configuration, thepaper did some analysis work.Firstly, in the paper, the typical aerodynamic characteristics of thosehypersonic aerodynamic configurations, including the lifting body configuration,BWB configuration and waverider configuration. The change of the aerodynamiccharacteristics such as the lift coefficient, drag coefficient and L/D were analyzed.Secondly, based on the waverider configuration, combined with therequirements of aerospace vehicle, the aerodynamic configuration was designed. Itincluded the method of waverider configuration design, the design of scramjetengine and the fuselage design. And the specific size of the preliminaryconfiguration of the vehicle was designed finally.Finally, it carried out a local optimization on the design of the aerodynamiclayout, using the SIMPLEX optimization method, and the2-D numerical simulationof the design of waverider configuration was implemented. the design shape of thevehicle was generated by the CATIA software, and imported the file into thesoftware of the GAMBIT and make the grid file, including set the boundary conditions and save the file as “.mesh”, finally imported the “.mesh” file into theFLUENT—a flow field calculation software for numerical simulation. Thesimulation included two cases, the engine entrance opened and the engine entranceclosed. Finished the calculation, it obtained the development relationship of theaerodynamic configuration and the contours of pressure force, velocity magnitudeand static temperature. It concluded from the paper that:1) When the Mach number changed from5to10, the shock wave generatedfrom the head of the vehicle, the front of the engine and the front of the verticalwing, in those places, the local pressure and the temperature is very high, themaximum of the temperature raised with the increase of the Mach number.2) In the case of the same angle of attack, with the increase of the Machnumber, the lift coefficient and the drag coefficient increased, in the mean time, thelift coefficient increased much faster than the drag coefficient.3) With the angle of attack increased, the L/D increased nonlinearly, when theangle of attack reached30degree, the L/D reached the maximum value, in the caseof the engine entrance opened, the maximum value was3.9, in the case of theengine entrance shut, the maximum value was3.0, and the L/D did not changealong with the Mach number.