Performance measurements in a shock tunnel of a fuelled scramjet vehicle generating lift, thrust and pitching moment
This paper reports the results from experiments to measure the lift, thrust/drag and pitching moment on a hydrogen-fuelled scramjet model. The experiments were performed in the T4 shock tunnel at The University of Queensland on an asymmetric scramjet model. A three-component stress-wave force-balance was used to measure the overall aerodynamic forces on the scramjet, with and without fuel injection and combustion, during test flows of approximately 4 ms duration. At an equivalent flight Mach number of 8, the lift and thrust forces varied approximately linearly with equivalence ratio. The lift force increased by approximately 40% and the centre of pressure changed by approximately 10% of the chord of the vehicle when the equivalence ratio was increased from zero to one. The thrust produced by combustion of the fuel was just insufficient to overcome the drag at the highest equivalence ratio tested when fuel was injected on the intake.
KeywordsCombustion Chamber Equivalence Ratio Lift Force Thrust Force Fuel Injection
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