Research On Airframe/Propulsion Integrated Aerodynamic Performance And Optimization For Hypersonic Vehicle

Hypersonic aircraft has become one of the attractive technologies of advanced countries ofstrategic and tactical competition. In order to obtain a more completed of integration aerodynamicperformance of this aircraft, the article studies the aerodynamic performance of the hypersonic vehicleand the TBCC engine through methods of engine performance simulation, CFD analysis andnumerical optimization, which is based on a class of over/under TBCC powered hypersonic aircraftunder the program of aircraft/engine integration.First, this article obtains the model of a dual flowpath propulsion system with respect to theoverall performance calculation and analysis of the TBCC engine. It also establishes hypersonicvehicle model and the install method of TBCC engine based on aircraft mission demand. Meanwhile,the article studies the aerodynamic performance of the hypersonic vehicle and the TBCC engine undertypical operating state, which is based on the integration model.Based on this aircraft/propulsion integrated model, aerodynamic performances of uninstalled andinstalled models under the turbojet mode is investigated. The results show, under the samebackpressure conditions, the flowrate coefficients and total pressure recovery of the stalled modelhave been improved; total pressure recovery raise about9%, thrust per massflow of the engine lossesabout20%. The forebody drags of uninstalled and installed cases are all great a bit, account to about69%and58%of the total drag of the vehicle.Next, under the single turbojet mode, the article has a research on the aerodynamic performanceof the engine installation and uninstallation. The results show that after installed, the flow coefficientand the total pressure recovery coefficient of the inlet have increased on the same backpressurecondition, where the total pressure recovery coefficient has an increase of9%; after the engineinstallation, the specific thrust of the engine has a larger decrease and a loss of20%. The drag of theaircraft forebody with the engine installation and not installation is larger, and has a69%and58%oftheir total drag of the aircraft respectively.Under the ramjet mode, the article has a research on the aerodynamic performance of the engineinstallation and not installation. The results show that the flow coefficient and the total pressurerecovery coefficient of the inlet have increased on the same backpressure condition, where the flowcoefficient has an increase of12%, the total pressure recovery has an increase of3.6%, and thespecific thrust of the engine has a decrease of5.4%. The installation effects on the propulsion systems of the ramjet mode is little than the single turbojet mode.Then, the article has studied the integrated installation aerodynamic performance of the threeengines under the pure turbojet mode. The results show that compared with the single engineinstallation, the all specific thrust of the engine have an increase, where the thrust of the engines havean increase of3.2%on the two sides; but the drag of the forebody has a decrease of6.5%; the totalpressure recovery of all the inlets of the three engines installation is larger than the total pressurerecovery of the inlet of the single engine installation, where the middle inlet has an increase of3.5%and the inlets of the two sides have an increase of0.4%; because of the interference of the threeengines, the flow coefficient of the all inlets of three engines installation has a decrease; the specificthrust of the engines on the two sides has an increase of2.9%than the engine in the middle; theinternal total pressure recovery of the nozzles remains basically unchanged.Last, the article has studied the integrated installation aerodynamic performance of the threeengines under the pure ramjet mode. The results show that because of the interference of the threeengines, the total thrust of three engines is not just the multiply of the thrust of the single engine.