Internal Flow Characteristics of a Rectangular Ramjet Air Intake

Moerel, J.L.P.A.; Veraar, R.G.; Halswijk, W.H.C.; Pimentel, Rogerio; Corriveau, D.; Hamel, Nicolas; Lesage, François; Vos, Jan B.

doi:10.2514/6.2009-5076

Cited by 15 publications

(6 citation statements)

References 2 publications

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“…Sixteen pitot with sixteen static pressure probes and four static pressure taps in the flow meter are used to measure the mass flow rate of the OICWI. The mass flow rate through the inlet was determined using a choked valve method which has small level of inaccuracies [9] .…”

Section: Design Of the Oicwimentioning

confidence: 99%

Progress in Waverider Inlet Integration Study

He¹

2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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A methodology has been devised for the design of Osulating Inward turning Cone Warerider forebody Inlet(OICWI). The integrated waverider foreboody inlet take advantages of both inward cone waverider and 3D compression inlet. The design method makes extensive use of Osculating Inward turning Cone and tip to tail inviscid streamline tracing techniques to generate a smoothly integrated three dimensional hypersonic waverider forebody inlet with no artificial modification in the compression surface from forebody leading edge to inlet throat. The integrated waverider forebody inlet has geometric contraction ratio 4.6 and inner contraction ratio 2.0 from cowl lip to throat. Wind-tunnel testing of the OICWI has been conducted at Mach 4.0, 3.5 and 3.0. The tests are performed to investigate the self-starting and backpressure limits of the OICWI well below its design point. Results show that the inlet can self-start from Mach number 3.5. The OICWI generates a static pressure compression ratio of 8.3, flow capture ratio of 0.73 and withstand maximum backpressure ratio of 35.8 relative to tunnel static pressure at Mach 4.0, AoA 0.

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Section: Design Of the Oicwimentioning

confidence: 99%

Progress in Waverider Inlet Integration Study

He¹

2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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“…-The total contraction ratio was 2.0, and the isolator had an expansion ratio of 1.2. -A 20 mm × 150 mm bleed block was used at the end of the isentropic ramp, and its design was based on reference [24], which improved M start from 2.2 to 1.88 and enhanced the back pressure resistance by 10% at M ∞ = 3 and H ∞ = 10 km. -A GO 2 /ethanol rocket was embedded in the strut and employed twin parallel rectangle nozzles.…”

Section: Inlet Configurationmentioning

confidence: 99%

“…A boundary layer bleed is commonly used in a supersonic inlet to improve the unstart characteristics of the inlet and to optimize the inlet flow field by sucking away the boundary layer flow that develops along the compression ramp. At the same time, the boundary layer bleed enhances the back pressure resistance, which acts as a shock stabilizer and prevents the normal shock from being expelled outside the inlet too easily [24]. As in a RBCC engine, the boundary layer bleed serves as a useful device in ramjet and scramjet modes [25][26][27][28].…”

Section: Introductionmentioning

confidence: 99%

Numerical Study of a Boundary Layer Bleedfor a Rocket-Based Combined-Cycle Inlet in Ejector Mode

Shi

Qin

et al. 2014

International Journal of Turbo &Amp; Jet-Engines

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Fully integrated numerical simulations were performed for a ready-made central strut-based rocketbased combined-cycle (RBCC) engine operating in ejector mode, and the applicability of using a boundary layer bleed in the RBCC inlet designed for supersonic speeds was investigated in detail. The operational mechanism of the boundary layer bleed and its effects on the RBCC inlet and the engine under different off-design conditions in ejector mode were determined. The boundary layer bleed played different roles in the RBCC inlet for different flight regimes. When the RBCC engine took off, some air was entrained into the inlet through the bleed block, thereby inducing significant flow separation and a low-speed vortex, which deteriorated the inner flow and reduced the entraining air mass flow rate: thus, the total pressure loss increased and extra drag was exerted on the inlet. In the low subsonic regime, the bleed block had almost no impact on the RBCC engine and its inlet. However, as the RBCC engine accelerated into a high subsonic flight regime, the boundary layer bleed had a clearly positive effect, comprehensively improving the performance of the RBCC inlet. A boundary layer bleed operation strategy for the RBCC inlet in ejector mode was also developed in this study.

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“…Wang Yufeng has researched the inner flow of ramjet engine [5]. The TNO Defence, Security and Safety and DRDC-Valcartier have worked on the improvement of modeling and simulation tools for the functioning of supersonic air intake for realistic ramjet engines of tactical missiles [6].…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation on Aerodynamics of Ramjet Projectiles

Zhang

Wang

Liu

2011

AMR

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Three-dimensional Reynolds-averaged Navier-Stokes simulations have been performed to explore the aerodynamic characteristics of ramjet projectiles. The turbulence model used is the RNG k-ε model. The numerical algorithms termed total variational diminishing (TVD) was adopted. The complex wave structures of ramjet projectiles with different architecture at different inflow Mach number were achieved by numerical simulation. The influence of inflow Mach number on aerodynamic characteristics and pressure center of ramjet projectiles were analyzed. Results show that lift coefficient and pressure center increase with the argument of inflow Mach number. Ramjet projectiles with different architecture have different drag coefficient trend.

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Internal Flow Characteristics of a Rectangular Ramjet Air Intake

Cited by 15 publications

References 2 publications

Progress in Waverider Inlet Integration Study

Progress in Waverider Inlet Integration Study

Numerical Study of a Boundary Layer Bleedfor a Rocket-Based Combined-Cycle Inlet in Ejector Mode

Numerical Simulation on Aerodynamics of Ramjet Projectiles

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