The SCRAMSPACE I Scramjet Flight Design and Construction

Tirtey, Sandy; Boyce, Russell; Brown, Laurie M.; Creagh, Michael; Staden, Paul van; Dimitrijevic, Igor; Capra, Bianca R.

doi:10.2514/6.2012-5843

Cited by 10 publications

(9 citation statements)

References 6 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The SCRAMSPACE flight test [4,5], funded under the Australian Space Research Program, took place in September 2013. The scramjet used a conical inlet configuration.…”

Section: Introductionmentioning

confidence: 99%

Rugged, Scramjet Inlet Temperature and Velocity Sensor: Design and Ground Test

et al. 2016

View full text Add to dashboard Cite

The design and testing of a gas temperature and velocity scramjet engine inlet sensor based on tunable diode laser absorption spectroscopy of oxygen is discussed. The robustness and stability of the optical design necessitated by the dynamic vibrational and thermal environment were balanced against the need for compact size and very high signalto-noise ratio in a low-pressure, high-altitude flight regime. Test results demonstrated very good mechanical and thermal stability and an adequate signal-to-noise ratio for altitudes up to 30 km with predicted O 2 absorbance peaks greater than the signal standard deviation by a factor of more than 3. Nomenclature I, I 0 = signal intensity with and without sample gas (arbitrary units) T= I∕I 0 , sample gas transmittance

show abstract

“…The SCRAMSPACE flight test [4,5], funded under the Australian Space Research Program, took place in September 2013. The scramjet used a conical inlet configuration.…”

Section: Introductionmentioning

confidence: 99%

Rugged, Scramjet Inlet Temperature and Velocity Sensor: Design and Ground Test

et al. 2016

View full text Add to dashboard Cite

show abstract

“…The experiments by Antonov et al [7] demonstrated a high compression performance of the simplest internal-compression inlets in the form of a conical funnel at a hypersonic Mach number M = 11.5. There are recent considerations of funnel-shaped inlets of fully internal compression as applied to hypersonic scramjet-powered vehicles flying at Mach numbers M > 4, for example, Tirtey et al [8]. A numerical computation of a laminar flow in the simplest inlet with a funnel-shaped compression section at M = 4 presented by Bashkin and Egorov [9] is worth mentioning.…”

Section: Introductionmentioning

confidence: 99%

Patterns of steady axisymmetric supersonic compression flows with a Mach disk

Gounko

2016

Shock Waves

View full text Add to dashboard Cite

Results of a numerical simulation of steady axisymmetric supersonic flows in convergent conical ducts and in overexpanded jets are presented. The characteristic feature of these compression flows is the formation of an initial longitudinally curved shock wave with intensity increasing downstream and toward the flow axis, which is finalized by the generation of a central Mach disk. Computations have demonstrated patterns of an irregular interaction of these shocks followed by the formation of a triple-shock configuration, including a reflected shock and a shear layer with entropy varying across the layer. The formation of triple-shock configurations is analogous to the configurations known for the steady inviscid two-dimensional flows where the irregular reflection of a wedge-generated shock from a wall with Mach stem formation occurs. Either a single triple-shock Mach configuration occurs or a triple-shock configuration corresponding to the von Neumann paradox condition is formed at the considered flow Mach numbers and initial angles of deflection to the axis of the flow behind the longitudinally curved shock wave.

show abstract

“…The test conditions (Refer Table 4.5) were based on equivalent nominal Mach 8, 3.3MJkg -1 flight conditions, the design conditions for the SCRAMSPACE inlet-fuelled axisymmetric radical farming scramjet free flight experiment (Tirtey et al 2012) [129] and are similar to the conditions used in the ground based testing of the 1:1 scale model (Hunt 2014) [37]. In this Section an overview of the experimental conditions achieved during testing and how these conditions were derived is presented.…”

Section: Test Conditionsmentioning

confidence: 99%

“…Simulations of laminar boundary layers in the inlet of the SCRAMSPACE flowpath (Tirtey et al 2012) [129] have been conducted by Brown et al (2011) [132] using a RANS CFD technique in which a turbulence source terms off region is applied to a domain so that the boundary layer is laminar in the vicinity of any SWBLI (Reinartz 2006) [133]. This technique was employed to examine the effect of a laminar boundary in the inlet and to determine whether CFD could correctly reproduce the wall St. A simulation employing a turbulence source term off region in the domain extending from the inflow boundary condition to a location 0.102m 4 upstream of the combustion chamber entrance was conducted.…”

Section: Cfd Reconstructionsmentioning

confidence: 99%

“…The condition was an equivalent Mach 8 flight at an altitude of 28.5km (3.1 MJkg -1 ) with equivalence ratios of φ = 0.5 and 1.0 examined. The selection of this test condition was to have similar conditions to the SCRAMSPACE (Tirtey et al 2012) [129] nominal flight condition of 27.5km altitude whilst allowing for steady and stable flowfields to form in both the equivalence ratio cases examined 1 . The premixed inflow conditions are presented in Table 6.1.…”

Section: Premixed Axisymmetric Radical Farming Scramjet Flowfield 62mentioning

confidence: 99%

See 1 more Smart Citation

Geometric scaling studies of an inlet-fuelled axisymmetric radical farming scramjet engine

Oberg¹

View full text Add to dashboard Cite

Scramjet engine technology has the potential to transform commercial flight and mankinds' ability to access space. Major technology hurdles remain which must be investigated and resolved before the potential of the scramjet engine can be realised. The ability to scale a small geometric scale scientific test model to a large practical vehicle size with similar performance characteristics is one such challenge. In this study, the small scale geometric scaling characteristics of a scramjet engine, one such tool to aid in future experimental based investigations and overall scramjet development, is presented. The study specifically concentrates on investigating the similarity effects for a new type of scramjet engine, the axisymmetric inlet-fuelled radical farming scramjet engine, and is concerned with the Pressure-Length scaling laws in both plain air mediums and hypersonic shock tunnel facility test mediums.

show abstract

The SCRAMSPACE I Scramjet Flight Design and Construction

Cited by 10 publications

References 6 publications

Rugged, Scramjet Inlet Temperature and Velocity Sensor: Design and Ground Test

Rugged, Scramjet Inlet Temperature and Velocity Sensor: Design and Ground Test

Patterns of steady axisymmetric supersonic compression flows with a Mach disk

Geometric scaling studies of an inlet-fuelled axisymmetric radical farming scramjet engine

Contact Info

Product

Resources

About