Numerical Study on Combustor Flow-Path Design for a Scramjet Flight Experiment

抄録

A flight-ground test comparison program is undergoing at JAXA to reveal so-called facility effects on hypersonic aerodynamics and combustion phenomena. The flight vehicle will mount a combustor duct along its centerline, with so-called alligator type inlet with side-spillage to attain good starting characteristics. The incoming flow condition was estimated with 3D-CFD, and one-dimensional chemical kinetic calculation was conducted to settle design guideline of combustor which could enhance so-called vitiation effects on combustion. The design guideline was further evaluated by 3D-CFD with fine chemical reaction model, showing possible difference in combustion efficiency and resulting pressure level.